NANOSATELLITE & CUBESAT DATABASE
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| Mission name | Organisation | Organisation type | Nation | Type (U/mass) | Launch date | Status | Mission description | Photo |
|---|---|---|---|---|---|---|---|---|
| TUBSAT-N | Technische Universität Berlin | University | Germany | 8.5 kg | 1998-07-07 | Reentry 2002-04-22. Was operational until 2000-XX-XX. More than two years of operation. | Demonstration of low-cost access to space without performance reduction. Bidirectional data transfer between autonomous environmental stations and the satellite. Tracking of medium-sized and large mammals. The main payload are two communication transceivers for store and forward communication with a baud-rate of 1200 and 2400 baud. Reaction wheel performance. Store and forward communication." |  |
| TUBSAT-N1 | Technische Universität Berlin | University | Germany | 3 kg | 1998-07-07 | Reentry 2000-10-20. Was operational until 1999-XX-XX. About 1 year operation | Demonstration of low-cost access to space without performance reduction. Bidirectional data transfer between autonomous stations and the satellite. Tracking of medium-sized and large mammals. The main payload are two communication transceivers for store and forward communication with a baud-rate of 1200 and 2400 baud. |  |
| Artemis JAK (MASat, Picosat 5) | Santa Clara University | University | US | 0.2 kg | 2000-01-27 | No signal | Simple beacon transmitter to test the ground reception ability of spaceborne picosat broadcasts. |  |
| Artemis Louise (Lightning, Picosat 8) | Santa Clara University | University | US | 0.895 kg | 2000-01-27 | No signal | Research the effects of lightning on the outer ionosphere. Lightning discharges and the effects on the Earth's near space environment can be recorded with the VLF receiver. Receive frequency range is 0.1-12 kHz, with 5 kHz typcal of a lightning strike. Measurements are taken by both picosatellites. Comparison of the data permits the extraction of the occurrence and amplitudes of horizontal and vertical lightning. |  |
| Artemis Thelma (Thunder, Picosat 7) | Santa Clara University | University | US | 0.6 kg | 2000-01-27 | No signal | The objective is to research the effects of lightning on the outer ionosphere. Lightning discharges and the effects on the Earth's near space environment can be recorded with the VLF receiver. Receive frequency range is 0.1-12 kHz, with 5 kHz typcal of a lightning strike. Measurements are taken by both picosatellites. Comparison of the data permits the extraction of the occurrence and amplitudes of horizontal and vertical lightning. | |
| ASUSat 1 (Arizona State University Satellite) | Arizona State University | University | US | 6 kg | 2000-01-27 | Was operational until 2000-01-28. 14 hours. Problem in power system prevented the solar arrays from supplying power. | Its primary mission was Earth imaging, with several secondary missions including orbit determination, amateur-radio communications, passive stabilization techniques, attitude detection, and composite-material research. |  |
| MEMS 1A (Pico 21, PICOSAT-1) | DARPA | Military | US | 0.275 kg | 2000-01-27 | Reentry 2000-XX-XX. Was operational until 2000-02-09. Battery power decayed | To demonstrate the basic functional elements of a low-power LEO “swarm” or formation PICOSAT array. To communicate from space using node-type radios and to report the results of MEMS-switched tests. Validate MEMS radio frequency switches. The two orbiting picosats are to be tethered because they will communicate via micropower radios. The tether will keep them within range of each other for crosslink purposes. |  |
| MEMS 1B (Pico 23, Picosat 1) | DARPA | Military | US | 0.275 kg | 2000-01-27 | Reentry 2000-XX-XX. Was operational until 2000-02-09. Battery power decayed | To demonstrate the basic functional elements of a low-power LEO “swarm” or formation PICOSAT array. To communicate from space using node-type radios and to report the results of MEMS-switched tests. Validate MEMS radio frequency switches. The two orbiting picosats are to be tethered because they will communicate via micropower radios. The tether will keep them within range of each other for crosslink purposes. |  |
| StenSat (Picosat 6) | Stensat Group | Company | US | 0.2 kg | 2000-01-27 | No signal | Amateur radio operators world wide and was to operate as a single channel mode "J" FM voice repeater. |  |
| MEMS 2A (Pico 20, PICOSAT 7) | DARPA | Military | US | 0.275 kg | 2000-07-19 | Reentry 2002-07-11. No signal? | To demonstrate the basic functional elements of a low-power LEO “swarm” or formation PICOSAT array. To communicate from space using node-type radios and to report the results of MEMS-switched tests. Validate MEMS radio frequency switches. The two orbiting picosats are to be tethered because they will communicate via micropower radios. The tether will keep them within range of each other for crosslink purposes. |  |
| MEMS 2B (Pico 22, PICOSAT 8) | DARPA | Military | US | 0.275 kg | 2000-07-19 | Reentry 2002-07-11. No signal? | To demonstrate the basic functional elements of a low-power LEO “swarm” or formation PICOSAT array. To communicate from space using node-type radios and to report the results of MEMS-switched tests. Validate MEMS radio frequency switches. The two orbiting picosats are to be tethered because they will communicate via micropower radios. The tether will keep them within range of each other for crosslink purposes. |  |
| Munin | Swedish Institute of Space Physics | Institute | Sweden | 6 kg | 2000-11-21 | Was operational until 2001-02-21, Likely to boot PROM failure after manual CPU reset. | Collect data on the auroral activity on both the northern and southern hemispheres, such that a global picture of the current state of activity can be made available on-line. The data acquired by Munin will then serve as an input to the prediction of space weather. Collect data on the auroral activity on both the northern and southern hemispheres. Combined electron and ion spectrometer, an instrument first to be flown on the Swedish Astrid-2 mission. In addition it will measure high energy particles with a solid state detector, and image the aurora with a miniature CCD camera. |  |
| MEPSI 1A (MEMS-based PicoSat Inspector) | DARPA | Military | US | 0.8 kg | 2002-11-23 | Reentry 2003-01-31. Was operational? | Demonstrate the capability of deploying an onboard miniature autonomous inspector, tasked to conduct visual inspection of the host satellite. Pair is connected with 15.2 m tether. Cold gas propulsion system, with 0.1N thrust with 5 thrusters. This propulsion system includes MEMS pressure transducers. |  |
| MEPSI 1B (MEMS-based PicoSat Inspector) | DARPA | Military | US | 0.8 kg | 2002-11-23 | Reentry 2003-01-31. Was operational? | Demonstrate the capability of deploying an onboard miniature autonomous inspector, tasked to conduct visual inspection of the host satellite. Pair is connected with 15.2 m tether. Cold gas propulsion system, with 0.1N thrust with 5 thrusters. This propulsion system includes MEMS pressure transducers. |  |
| AAUSAT 1 (AAU-CubeSat, AAU CubeSat) | Aalborg University | University | Denmark | 1U | 2003-03-30 | Was operational until 2003-09-22. Battery problems. | * Sudents have achieved some useful knowledge of space technology. * That communication is established with the satellite and housekeeping information is retrieved. * Test ACS performance. * Take pictures of certain locations on earth. Imaging Earth with CMOS camera. Attitude control with coils. |  |
| CanX-1 | Space Flight Laboratory (SFL) | Institute | Canada | 1U | 2003-03-30 | No signal | Its mission is to evaluate several novel technologies in space, including a low-cost CMOS horizon sensor and star-tracker, active three-axis magnetic stabilization, GPS-based position determination, and an ARM7 central computer. |  |
| CUTE-I (Cubical Tokyo Tech Engineering Satellite-I) | Tokyo Institute of Technology | University | Japan | 1U | 2003-03-30 | Operational (Last DK3WN report 2018-05-07) | Communication, sensing and deployment mechanism missions. CW-transmitter and FM-transmitter. FM-telemetry by two different protocol (Ax.25 and TITech original. Broadcasting service of CW-telemetry data and FM-telemetry data on WWW. Deploy the solar battery paddle by command uplink. |  |
| DTUSat-1 | Technical University of Denmark | University | Denmark | 1U | 2003-03-30 | No signal | The main payload is an 450 m long electrodynamic tether for dumping the satellite. The tether is deployed using a novel yo-yo system, greatly simplifying construction and deployment. A calibrated test transmitter is flown as secondary payload. |  |
| QuakeSat | Stanford University | University | US | 3U | 2003-03-30 | Was operational until 2004-12-XX. | * To detect, record, and downlink earthquake ELF emission data. * Demonstrate that the CubeSat Nano-Sat design is a cost-effective platform for conducting significant space science research experiments. * Demonstrate the feasibility of utilizing commercially-off-the-shelf (COTS) parts to construct a reliable, short mission micro-satellite. To detect Earthquake ELF emission data. |  |
| XI-IV | University of Tokyo | University | Japan | 1U | 2003-03-30 | Operational (Last DK3WN telemetry 2018-02-19) | The objective is to demonstrate and to validate a picosatellite bus system and the space use of commercial-of-the-shelf (COTS) parts. CMOS camera. |  |
| UNOSAT 1 (Undergraduate Orbital Student Satellite) | Universidade Norte do Paraná | University | Brazil | 8.83 kg | 2003-08-22 | Launch failure | Transmit in regular intervals a message of voice and one packet of telemetry. | .jpg){kind=small} |
| TNS-0 (TEKh-42, Technologicesky Nanosputnik) | Moscow Russian Scientific Research Institute | Institute | Russia | 4.5 kg | 2005-02-28 | Reentry 2005-08-30. Was operational until 2005-07-15. Batteries were empty and burnt in atmosphere couple of months later. | Working out the principles of small satellites control using global telecommunication systems, as well as receiving by COSPAS/SARSAT system beacon of the flight qualification. Serviceability verification of the global satellite system (GLOBALSTAR) subscribers’ equipment for transmission of the command and program information to the satellite and for transmission of the telemetry information from the satellite. |  |
| nCube-2 | Norwegian University of Technology and Science (NTNU), Narvik University College (HiN) and the Agricultural University of Norway (NLH) | University | Norway | 1U | 2005-10-27 | Deployment failure from SSETI Express. | Hands-on experience with a real satellite mission. Multidisciplinary collaboration. Space project experience. AIS receiver to demonstrate the capability of tracking ships from space. |  |
| UWE-1 | University of Würzburg | University | Germany | 1U | 2005-10-27 | Was operational until 2006-06-XX. | Experiments on “Internet Protocols in space”, as well as to miniaturization technology demonstrations. This second objective included characterization of triple junction GaAs solar cells from European sources, which were tested first time in space. Analye the applicability of TCP / IP transmission techniques for telemetry and remote controlled data taking into account typical problems of space, such as delays and disorders. Implementation of a ground station and their insertion into an international network of CubeSat users over the Internet. Eventual testing of micro-system components for position determination (Gyro, determination of declination / inclination) |  |
| XI-V | University of Tokyo | University | Japan | 1U | 2005-10-27 | Was operational until 2016-04-XX? (Last DK3WN report 2016-04-01) | Its mission is to evaluate several novel technologies in space, including a low-cost CMOS horizon sensor and star-tracker, active three-axis magnetic stabilization, GPS-based position determination, and an ARM7 central computer. CMOS camera. Backup to XI-IV. Verification of newly developed solar cells. |  |
| CUTE-1.7+APD | Tokyo Institute of Technology | University | Japan | 2U | 2006-02-21 | Reentry 2009-10-25. Was operational until 2006-03-16. Stopped receiving commands, beacon functioned until deorbit. | Demonstration of PDA (Personal Digital Assistant) as an onboard computer. Attitude control experiment using magnetic torquer. Amateur radio service - digital repeater (digipeater). Demonstration of APD (Avalanche Photo Diode) sensor. Tether deployment experiment. |  |
| AeroCube-1 | The Aerospace Corporation | Non-profit | US | 1U | 2006-07-26 | Launch failure | Mission is to test a communication system and the system bus plus a suite of CMOS cameras done by Harvey Mudd College. An omnidirectional patch antenna is used. |  |
| CP1 | California Polytechnic University | University | US | 1U | 2006-07-26 | Launch failure | Testing of a sun sensor donated by Optical Energy technoloies, as well as the use of a sungle magnetic torquer embedded within a side panel. |  |
| CP2 | California Polytechnic University | University | US | 1U | 2006-07-26 | Launch failure | Energy dissipation experiment as well as a field-test of what we have dubbed the CP Bus. CP2 marks our first attempt at “standardizing” a CubeSat bus to enable easier integration of a wide variety of payloads. |  |
| HAUSat-1 (Hannuri-1, Hankuk Aviation University SATellite-1) | Korea Aerospace University (Hankuk Aviation University) | University | South Korea | 1U | 2006-07-26 | Launch failure | Development, launch, and operation of CubeSat. Space qualification of space components. Develop core satellite system technology. Establish satellite system development infrastructure. Cultivate professionals in field of satellite systems. Accomplish national-first purely student managed program. Space-borne GPS Receiver. Verification of home-made Sun Sensor. Verification of Solar Panel Deployment Mechanism. |  |
| ICECube 1 (Ionospheric sCintillation Experimental CubeSat) | Cornell University | University | US | 1U | 2006-07-26 | Launch failure | First, to qualify the concept of small satellites as useful instruments for science and engineering, to lower the cost of space utilization and exploration; Second, to educate students in all major aspects of the design, construction, and launch of space satellite systems. Perform GPS scintillation science by measuring fluctuations in the signals that the GPS satellites emit when the signals pass through the ionosphere. |  |
| ICECube 2 (Ionospheric sCintillation Experimental CubeSat) | Cornell University | University | US | 1U | 2006-07-26 | Launch failure | First, to qualify the concept of small satellites as useful instruments for science and engineering, to lower the cost of space utilization and exploration; Second, to educate students in all major aspects of the design, construction, and launch of space satellite systems. Perform GPS scintillation science by measuring fluctuations in the signals that the GPS satellites emit when the signals pass through the ionosphere. |  |
| ION | University of Illinois | University | US | 2U | 2006-07-26 | Launch failure | Measuring Oxygen airglow emissions from the Earth’s mesosphere. Tests a new MicroVacuum Arc Thruster (µVAT) with high dynamic range. tests a new SID processor board. Small CMOS camera for Earth imaging. Measuring molecular Oxygen airglow emissions from the Earth’s mesosphere using a 760nm photometer. Oxygen chemistry at this 90km altitude emits a dim glow of light. Learn how energy transfers across large spatial regions contributing to knowledge of upper atmospheric dynamics. This airglow emission is absorbed by the Earth’s lower atmosphere preventing study with Earth-based sensors. |  |
| KUTESat | University of Kansas | University | US | 1U | 2006-07-26 | Launch failure | Develop and operate a simple pico- satellite in low Earth orbit (LEO). Measure the radiation in LEO and take photographs with an onboard camera. |  |
| Mea Huaka (Voyager) | University of Hawaii | University | US | 1U | 2006-07-26 | Launch failure | Set of temperature sensors to verify UH-designed thermal modeling software, but the actual mission was just learning to build a bus. Active antenna - test a 5.8-GHz active antenna (grid oscillator) for high bandwidth communication. Grid oscillators do not require deployment, are tolerant to single-point failures, and facilitate long-link communications at microwave frequencies. |  |
| MEROPE (Montana Earth-Orbiting Pico-Explorer) | Montana State University | University | US | 1U | 2006-07-26 | Launch failure | Measure the radiation of the Van Allen radiation belts, first discovered by Explorer-1 under the direction of Professor James Van Allen's group of the State University of Iowa (now The University of Iowa). |  |
| nCube-1 | Norwegian University of Technology and Science (NTNU), Narvik University College (HiN) and the Agricultural University of Norway (NLH) | University | Norway | 1U | 2006-07-26 | Launch failure | Hands-on experience with a real satellite mission. Multidisciplinary collaboration. Space project experience. AIS receiver to demonstrate the capability of tracking ships from space. |  |
| PicPoT (Small Satellite of Politecnico di Torino) | Polytechnic University of Turin | University | Italy | 2.5 kg | 2006-07-26 | Launch failure | Educational. Camera. |  |
| RinCon 1 | University of Arizona | University | US | 1U | 2006-07-26 | Launch failure | Low-power beacon system, which provides a redundant means of relaying sensor data in analog form if the primary (digital) transmitter fails. Sophisticated, low-power beacon board that was produced by Rincon and provides a redundant means of relaying sensor data in analog form. The beacon operates autonomous of all other satellite systems except for the power and the sensor electronics. |  |
| SACRED (AlcatelSat) | University of Arizona | University | US | 1U | 2006-07-26 | Launch failure | Measure the total amount of high-energy radiation over a two-year span and will test the radiation properties of four commercial integrated circuits The payload for this satellite was produced by Montpelier University and Alcatel and provides a valuable scientific/commercial application. The electronics board for this payload will measure the total amount of high-energy radiation over a two-year span and will test four commercial integrated circuit components for their radiation hardness, functionality and annealing properties. |  |
| SEEDS | Nihon University | University | Japan | 1U | 2006-07-26 | Launch failure | Communication with the amateur ground stations, the sensing of the satellite housekeeping data, and the analysis of its orbit and attitude. Each mission has many sub-missions. Contains a gyro sensor for accurate determination of attitude motion. |  |
| HIT-Sat | Hokkaido Institute of Technology | University | Japan | 2.7 kg | 2006-09-22 | Reentry 2008-06-18. Was operational until 2007-02-03, afterwards beacon intermittently. | Demonstrate the performance of the HIT-Sat bus system on orbit. HIT-Sat is an engineering test CubeSat, which is being used as a scale model for a future “Hokkaido microsatellite” . |  |
| RAFT1 | US Naval Academy Satellite Lab | University | US | 4 kg | 2006-10-12 | Reentry 2007-05-30. Was operational. | Provide a cubesat in a cluster which has an on-board transponder capable of identifying itself via the NSS satellite Radar Tracking system to help locate the Cubesats. Secondly, RAFT will have a separate 217 MHz NSSS radar transmitter and receiver, which can help with calibration tests of the separate NSSS transmit and receive antenna beams. Part of RAFT mission. The satellites will be the first of their size with the ability to be tracked by the Navy Space Surveillance (NSSS) radar fence. The satellites will also function as amateur radio transponders. |  |
| MARScom | US Naval Academy Satellite Lab | University | US | 3 kg | 2006-12-09 | Reentry 2007-05-06. No signal. | The mission of MARScom is to explore and demonstrate a very low cost yet viable communications capability for education and training of both Midshipmen and the large numbers of Navy Marine Corps communications cadre personnel. Part of RAFT mission. The satellites will be the first of their size with the ability to be tracked by the Navy Space Surveillance (NSSS) radar fence. The satellites will also function as amateur radio transponders. |  |
| MEPSI 2A | DARPA | Military | US | 1.1 kg | 2006-12-09 | Reentry 2007-03-08. Was operational, but short lived. | Pair is tethered. Cold gas propulsion system, with 0.1N thrust with 5 thrusters. This propulsion system includes MEMS pressure transducers |  |
| MEPSI 2B | DARPA | Military | US | 1.4 kg | 2006-12-09 | Reentry 2007-03-08. Was operational, but short lived. | Pair is tethered. Cold gas propulsion system, with 0.1N thrust with 5 thrusters. This propulsion system includes MEMS pressure transducers |  |
| GeneSat-1 | NASA/Santa Clara University | Agency | US | 3U | 2006-12-16 | Reentry 2010-08-04. Was operational. | Perform experiment on E. Coli bacteria in space, first cubesat to carry a biological experiment. |  |
| PehuenSat 1 | National University of Comahue | University | Argentina | 6 kg | 2007-01-10 | Was operational until 2007-02-01. Reports end during that time. | Build and operate a small satellite whose mission is educational, technological and scientific. This satellite will allow the participants to gain an important experience for future projects as part of the Pehuensat Program, with more complex missions. | .jpg){kind=small} |
| AeroCube-2 | The Aerospace Corporation | Non-profit | US | 1U | 2007-04-17 | Was operational until 2007-04-18. Failed almost immediately | Similar to AeroCube-1, except added charging system for the Lithium batteries. |  |
| CAPE-1 | University of Louisiana at Lafayette | University | US | 1U | 2007-04-17 | Was operational, unknown time. | To gain basic knowledge and skillset of developing and launching a picosatellite to pave the way for future projects. |  |
| CP3 | California Polytechnic University | University | US | 1U | 2007-04-17 | No signal | Implement an attitude control system using only magnetic torquers embedded within the side panels. Three-axis magnetorquing experiment |  |
| CP4 | California Polytechnic University | University | US | 1U | 2007-04-17 | Was operational? Unkown time, C&DH processor lock-up issue. | Energy dissipation experiment as well as a field-test of what the team has dubbed the CP Bus. CP2 marks our first attempt at “standardizing” a CubeSat bus to enable easier integration of a wide variety of payloads. |  |
| CSTB-1 (CubeSat TestBed 1) | Boeing | Company | US | 1U | 2007-04-17 | Was operational until 2009-11-XX. Retired. | Testbed for components for future Boeing small-sat missions. Accelerate the maturity of CubeSat related componets and subsystems, as well as accelerate the general infrastructure and operations of this class of spacecraft. Mature and evaluate commercial low power processors, CMOS ultra low power imagers, and associated software algorthms in the space environment, and to provide validations of using integrated attitude determination sensors as part of the multifunctional side panels. Redundant radios, deployable antenna, various non-disclosed sensors. |  |
| Libertad-1 | Sergio Arboleda University | University | Colombia | 1U | 2007-04-17 | Was operational until 2007-05-07? Batteries were empty. Some reports in Wiki that it was working over 2 years? | Camera and transmission of one stanza of the Colombian national anthem. |  |
| MAST | Tethers Unlimited | Company | US | 3U | 2007-04-17 | Was semi-operational, communication was achieved with one of three picosats. | Perform investigations of the dynamics of tethered formations of spacecraft and to investigate the survivability of tethers in the harsh space environment. 3 tethered cubesats with 1 km tether. The middle picosatellite, called "Gadget", will then slowly crawl up and down the tether, taking pictures of the tether as it goes. Determine how quickly the tether experiences damage due to impacts by micrometeoroids and orbital debris, as well as due to erosion by atomic oxygen and UV light. In addition, all three picosatellites contain GPS receivers. |  |
| MEMS-Pico (ZDPS-1, Zheda Pixing) | Zhejiang University | University | China | 1 kg | 2007-05-25 | No signal, because ZDPS-1A was considered as the first successfully operated Chinese nanosatellite. | Solar-panel-covered rhombicuboctahedron containing a MEMS infrared sensor, an S-band transceiver and a CMOS camera. |  |
| AAUSAT2 (AAUSat-2, AAUSAT-II) | Aalborg University | University | Denmark | 1U | 2008-04-28 | Operational (Last DK3WN report 2018-05-23) | Education. By participating in the project students gets involved in the complicated process of building a complex system like a satellite. This teaches the student to work together in small groups and, at the same time, coordinate their actions with other groups. The primary "technical" mission is to get one-way communication with the satellite, and next is establish two-way communication. The satellite caries two science experiments, an ADCS system and a gamma ray detector, that will be activated when two-way communication is established. The primary goal for the ADCS system is to detumble the satellite, but it can also actively control of the satellites attitude in space, utilizing coils and momentum wheels. The gamma ray detector is made by DSRI and it will detect gamma ray bursts from outer space. |  |
| CanX-2 | Space Flight Laboratory (SFL) | Institute | Canada | 3U | 2008-04-28 | Operational | GPS radio occultation experiment to characterize the upper atmosphere (University of Calgary), an atmospheric spectrometer to measure greenhouse gases (York University), and a space materials experiment to evaluate the effects of atomic oxygen on a protective coating (University of Toronto). The technologies that have been successfully tested include a novel propulsion system (Nanosatellite Propulsion System, or “NANOPS”), custom UHF and S-band radios, innovative attitude sensors and actuators, and a modified commercial GPS receiver. |  |
| CanX-6 | Space Flight Laboratory (SFL) | Institute | Canada | 6.5 kg | 2008-04-28 | Operational (https://www.utias-sfl.net/?page_id=205) | Automatic Identification System (AIS) receiver developed by COM DEV for detection of signals transmitted by maritime vessels. |  |
| Compass-1 | Aachen University of Applied Sciences | University | Germany | 1U | 2008-04-28 | Was operational until 2012-04-14. | To take color images of the earth at a resolution of 640x480 pixels, to validate (test) a Phoenix GPS receiver from DLR in orbit, to test three-axis attitude control (based on magnetic actuation), and to verify the functionality of the spacecraft in space (technology demonstration). |  |
| CUTE-1.7+APD-2 (CUTE1.7+APD-II) | Tokyo Institute of Technology | University | Japan | 3 kg | 2008-04-28 | Operational (Last DK3WN report 2018-04-16) | Follow-on satellite to the Cute-1.7 + APD Many improvements in particular, for amateur communications system, camera system, APD sensor, based on the experiences acquired in the development and operation of Cute-1.7 + APD. Redesigned satellite structure for increased solar cell area. |  |
| Delfi-C3 | Delft University of Technology | University | Netherlands | 3U | 2008-04-28 | Operational (Last DK3WN report 2018-07-08) | Hands-on education & training of students on a real spacecraft project. A Radio Amateur Platform (RAP) from TU Delft, comprising a linear transponder. Development of a modular nanosatellite spacecraft bus and a distributed ground segment. Demonstration of four arrays of Thin Film Solar Cells (TFSC) from Dutch Space. Demonstration of two Autonomous Wireless Sun Sensors (AWSS) from TNO. |  |
| SEEDS-2 (SEEDS-II, Space Engineering EDucation Satellite-2) | Nihon University | University | Japan | 1U | 2008-04-28 | Operational (Personal contact 2018-08-07, last DK3WN report 2017-03-17) | - |  |
| NanoSail-D | NASA/ Ames Research Center | Agency | US | 3U | 2008-08-03 | Launch failure | Establish ARC-MSFC collaborative relationship for future small satellite initiatives. Deploy a 10 m² solar sail leveraging work by MSFC approved under the SMD In-Space Propulsion Program. Demo Orbital Debris Mitigation technology – drag sail. Ground Imaging to reduce spacecraft instrumentation. Add to flight experience – ARC Bus "light" experience. The sail is made of an ultra-thin reflective polymer called CP-1. It is 7.5 microns thick and has a surface area of approximately 10 square meters. The sail is wound tightly around a central hub. When the sail deploys, four booms spring out to unfurl the sail and support its structure. The booms are each 2.2 meters long when fully deployed. The nine-pound sail subsystem was provided by ManTech/NeXolve in Huntsville, Ala. |  |
| PreSat (PharmaSat Risk Evaluation Satellite) | NASA Ames Research Center | Agency | US | 3U | 2008-08-03 | Launch failure | Demonstrate / Validate Performance of NASA-Ames 2nd Generation Modular Triple CubeSat Nanosatellite Platform. PRESat will demonstrate its ability to create a stable, space science laboratory using innovative environment control techniques, and to monitor the levels of pressure, temperature and acceleration. RESat contains a micro-laboratory with a controlled environment packed with sensors and optical systems that can detect the growth, density and health of yeast cells. |  |
| PSSC (PSSCT, Pico Satellite Solar Cell Testbed) | The Aerospace Corporation | Military | US | 6.5 kg | 2008-11-29 | Reentry 2010-02-17. Was operational until 2009-03-19. | Monitor accelerated radiation degradation of triple-junction solar cells in a high radiation environment. |  |
| KKS-1 (Kouku Kosen Satellite-1, KISEKI) | Tokyo Metropolitan College of Industrial Technology | University | Japan | 3.17 kg | 2009-01-23 | Semi-operational? (According to list of JE9PEL) | KKS-1 is an educational satellite that has been developed by the students and teaching staffs of Tokyo Metropolitan College of Industrial Technology as MONOZUKURI education of aerospace engineering. Micro propulsion system onboard which is 1st space-demonstration experiment of laser ignition thruster. Attitude controls by Small Reaction Wheel. Photographs by a CMOS camera（320×240 pixel color). KKS-1 carries messages from supporters to space. |  |
| PRISM (Picosatellite for Remote¿sensing and Innovative Space Missions) | University of Tokyo | University | Japan | 8.5 kg | 2009-01-23 | Was operational until 2018-02-XX? (Last SatNOGS report 2018-02-19) | Demonstration of Imaging Technology by using "Extensible Boom" as a Telescope. Demonstration of COTS-oriented Components for Nano-satellites. Advanced Amateur Radio Service. "Refraction-type" telescope, focuses light with a lens. The advantage of this approach is that the optical system can be rather resistant to structure alteration. In order to utilize this point, we designed and developed a flexible and extensible boom as a telescope. Could accomplish the 30m ground resolution. |  |
| STARS-1 Daughter (KUKAI, KAI, Space Tethered autonomous Robotic Satellite 1) | Kagawa University | University | Japan | 3.8 kg | 2009-01-23 | Reentry 2018-03-03. Was operational until? | The primary objective of KUKAI is technical verification of a tethered space robot. Two satellite system, mother and daughter; becomes a 5m tethered system on orbit at the maximum; the daughter satellite is a tethered space robot, whose attitude can be controlled by its own arm link motion. |  |
| STARS-1 Mother (STARS-C, KUKAI, KU, Space Tethered autonomous Robotic Satellite 1) | Kagawa University | University | Japan | 4.2 kg | 2009-01-23 | Reentry 2018-03-03. Was operational? | "The primary objective of KUKAI is teehnical verification of a tethered space robot. Two satellite system, mother and daughter; becomes a 5m tethered system on orbit at the maximum; the daughter satellite is a tethered space robot, whose attitude can be controlled by its own arm link motion." |  |
| AeroCube-3 | The Aerospace Corporation | Non-profit | US | 1U | 2009-05-19 | Reentry 2011-01-06. Was operational until 2009-12-10. Semi-operational without 2-way communication until reentry. | After launch, AeroCube-3 will remain attached to the upper stage of its carrier rocket by means of a 61-meter (200 ft) tether. Experiments will be conducted to determine the satellite's flight dynamics. A wide-angle camera will be used to image the upper stage. The satellite will also reel in the tether, moving closer to the upper stage. The primary systems demonstrated were a two-axis solar tracker and an Earth tracker, which could be used in the guidance systems of future satellites. It also carried a 0.6-meter (2 ft 0 in) balloon used for tracking tests and to increase drag, increasing the satellite's rate of orbital decay after its mission was completed. |  |
| CP6 (Polysat) | California Polytechnic University | University | US | 1U | 2009-05-19 | Reentry 2011-10-06. Was operational. | Implement an attitude control system using only magnetic torquers embedded within the side panels.Once the primary objectives have been met, a command will be sent to deploy the secondary payload that consists of a series of spring steel tapes. The data will be used to guide the future design of an electrodynamic tether. Attitude determination is performed using two-axis magnetometers on each side panel as well as observation imagers on the payload face. |  |
| HawkSat I | Hawk Institute of Space Sciences | Company | US | 1U | 2009-05-19 | Reentry 2011-09-04. No signal. | Its primary function is to act as a proof of concept vehicle for future satellites to be developed by the Hawk Institute for Space Sciences. Also carries a customer payload developed by a major aerospace firm. This experiment contains an external payload board which exposes newly developed materials to the radiation and temperatures encountered in the space environment. |  |
| PharmaSat 1 (GeneSat-2) | Santa Clara University, NASA Ames Small Spacecraft Division | Agency | US | 3U | 2009-05-19 | Reentry 2012-08-14. Was operational until 2009-06-15. Beacon was turned off and lost S-band contact before. | Contains a controlled environment micro-laboratory packed with sensors and optical systems that can detect the growth, density and health of yeast cells and transmit that data to scientists for analysis on Earth. Optical sensor system to detect the health and size of the yeast populations; a microfluidics system consisting of an eight-by-four inch plastic card with 48 small holes, or “fluidics microwells,” which house four separate sample groups of yeast, and a network of small tubes to feed the yeast simple sugars and dose them with an antifungal agent; and a miniature environmental control and power control system. |  |
| Aggiesat-2 (Dragonsat 2) | Texas A&M University | University | US | 3.2 kg | 2009-07-15 | Reentry 2010-03-17. Was operational for 230 days. | Promote space engineering education as well as research into novel, low-cost autonomous rendezvous and proximity operations techniques. The first-mission requirements were to operate the Global Positioning System (GPS) receiver built by NASA JSC called DRAGON (Dual RF Astrodynamic GPS Orbital Navigator). |  |
| BEVO 1 (DragonSat 1) | University of Texas at Austin | University | US | 3.5 kg | 2009-07-15 | Reentry 2010-03-17. No signal. Failed to separate from Aggiesat-2. | Promote space engineering education as well as research into novel, low-cost autonomous rendezvous and proximity operations techniques. The first-mission requirements were to operate the Global Positioning System (GPS) receiver built by NASA JSC called DRAGON (Dual RF Astrodynamic GPS Orbital Navigator). |  |
| BEESAT-1 | Berlin Technical University | University | Germany | 1U | 2009-09-23 | Was operational? (Last DK3WN report 2018-09-23) | Verification of miniaturized reaction wheels in the space environment. Test of a novel satellite bus system. Power scope improvement of pico- and nanosatellites |  |
| ITUpSAT-1 | Istanbul Technical University | University | Turkey | 1U | 2009-09-23 | Operational (Last DK3WN report 2018-05-11) | The overall objectives are to provide a hands-on project environment for the students at ITU under faculty guidance. ´The mission goals are to capture imagery of the CMOS payload and to study the behavior of the passive stabilization system of the CubeSat. |  |
| SwissCube | Swiss Federal Institute of Technology (EPFL) | University | Switzerland | 1U | 2009-09-23 | Operational, but some problems since 2017 (Last SatNOGS report 2018-07-22) | The main objective is educational and to show the students how to build a complex engineering system from A to Z like a satellite. Carries a small telescope which will allow to obtain images of the nightglow, a luminescence phenomena occurring at 100 km of height above the Earth surface. Since the nightglow takes place in a very limited region in the high layer of the atmosphere and at well-know locations, it might be possible from the measurements to retrieve the direction towards the centre of the Earth and therefore enabling the design of a new generation of Earth sensor. |  |
| UWE-2 | University of Würzburg | University | Germany | 1U | 2009-09-23 | Was operational, unknown time. | Demonstration of the newly developed Attitude Determination System (ADS). Equipped with a number of new sensors to be able to accurately determine the orientation in space. Demonstrate and verify the use of the new ADS. Further experiments on the topic of "IP in space". The successful experiments with Internet protocols in space of UWE-1 to continue with the UWE-2 satellite. |  |
| KSat (Hayato, Kagoshima Satellite, K-Sat) | Kagoshima University | University | Japan | 1U | 2010-05-20 | Reentry 2010-07-14. Was operational but communication happened rarely due to tracking problems. | Research That Aims to Predict the Torrential Rain and Rornadoes. On-orbit demonstration of original observation method of atmospheric water vapor using satellite. Take Earth Live Images from Space and download single shot in a few seconds using the Ku-band high-speed communication function. |  |
| Negai (Negai-Star) | Soka University | University | Japan | 1U | 2010-05-20 | Reentry 2010-06-26. Was operational. | Commercial FPGA for advanced information processing system. Camera for outreach purposes. |  |
| Waseda-Sat2 | Waseda University | University | Japan | 1U | 2010-05-20 | Reentry 2010-07-12. No signal. | Earth observation and technology demonstration. It will test the use of extendible paddles to provide attitude control. |  |
| AISSat-1 | Norwegian Space Centre | Agency | Norway | 7 kg | 2010-07-12 | Operational (Mentioned in public news) | Its primary mission is to demonstrate the feasibility and performance of space-based Automatic Identification System (AIS) detection from low-Earth orbit as a means of tracking maritime assets, and the integration of space-based AIS data into a national maritime tracking information system. |  |
| StudSat-1 (Student Satellite-1) | Nitte Meenakshi Institute of Technology | University | India | 1U | 2010-07-12 | Was semi-operational until 2010-08-12. Beacon was heard for about one month. | Promote space technology in educational institutions and encourage research and development in miniaturized satellites; introduce students at undergraduate level to space technology, demonstrate a successful inter-state, interuniversity, inter-disciplinary and interdepartmental participation in a single project, develop leadership qualities and scientific temperament among students. As a payload STUDSAT consists of a CMOS panchromatic camera. The entire architecture of the satellite was centred on the payload. The objective of this system was to obtain a monochrome image of the Earth with resolution of 90 meters covering a swath of 65 km x 45 km. |  |
| TISAT-1 | University of Applied Sciences of Southern Switzerland (SUPSI) | University | Switzerland | 1U | 2010-07-12 | Semi-operational? Fell silent 2015-03-15, but came back? (Last DK3WN report 2018-06-11) | Monitoring of the durability of exposed thin bonding wires, PCB tracks and lines (Atomic Oxygen effects). Verification of the system fault tolerance scheme. Acquisition of spacecraft environment and operating data. All firmware, in house developped baseband modulation schemes. |  |
| ZDPS 1A 01 (Zheda Pixing) | Zhejiang University | University | China | 3.5 kg | 2010-09-22 | Was operational until? | Platform verification. The functionality, performance and space environmental adaption of the satellites and their subsystems were to be validated in space via on-orbit testing and operation. Experimentation of miniaturized parts. Micro panoramic camera. Momentum wheel is employed to offer gyro stiffness stability in the pitch | .jpg){kind=small} |
| ZDPS 1A 02 (Zheda Pixing) | Zhejiang University | University | China | 3.5 kg | 2010-09-22 | Was operational until? | Platform verification. The space environmental adaption and application of the various parts including the miniaturized commercial-off-the-shelf (COTS) MEMS accelerometers and gyroscopes, the in-house-developed panoramic CMOS camera and the novel tri-junction solar cells were to be experimented. Attitude determination and control experimentation. The correctness and effectiveness of the attitude determination and control scheme were to be evaluated via attitude de-tumbling and stabilizing experiments. Micro panoramic camera. Momentum wheel is employed to offer gyro stiffness stability in the pitch. Miniaturized COTS MEMS accelerometers and gyroscopes, the in-house-developed panoramic CMOS camera and the novel tri-junction solar cells were to be experimented. The correctness and effectiveness of the attitude determination and control scheme were to be evaluated via attitude de-tumbling and stabilizing experiments. | .jpg){kind=small} |
| NanoSail-D2 | NASA Ames Research Center | Agency | US | 3U | 2010-11-20 | Was operational until 2011-01-21. Batteries were empty. | Establish ARC-MSFC collaborative relationship for future small satellite initiatives. Deploy a 10 m² solar sail leveraging work by MSFC approved under the SMD In-Space Propulsion Program. Demo Orbital Debris Mitigation technology – drag sail. Ground Imaging to reduce spacecraft instrumentation. Add to flight experience – ARC Bus "light" experience. The sail is made of an ultra-thin reflective polymer called CP-1. It is 7.5 microns thick and has a surface area of approximately 10 square meters. The sail is wound tightly around a central hub. When the sail deploys, four booms spring out to unfurl the sail and support its structure. The booms are each 2.2 meters long when fully deployed. The nine-pound sail subsystem was provided by ManTech/NeXolve in Huntsville, Ala. |  |
| O/OREOS | NASA Ames Research Center | Agency | US | 3U | 2010-11-20 | Was operational until 2016-11-27? (Last SatNOGS report 2016-11-27) | Organism/Organic Exposure to Orbital Stresses. An Astrobiology Technology Demonstration. | .jpg){kind=small} |
| RAX (Radio Aurora eXplorer) | University of Michigan | University | US | 3U | 2010-11-20 | Was operational until 2011-01-19. Solar panel degradation. | Investigate causes of upper atmospheric/ionospheric plasma turbulence. Study large plasma formations in the ionosphere, the highest region of our atmosphere. These plasma instabilities are known to spawn magnetic field-aligned irregularities (FAI), or dense plasma clouds known to disrupt communication between Earth and orbiting spacecraft. Will utilize a large incoherent scatter radar in Poker Flats, Alaska (known as PFISR). PFISR will transmit powerful radio signals into the plasma instabilities that will be scattered into space and RAX will be recording the scatter signals with an onboard receiver. |  |
| Caerus-Mayflower | Northrop Grumman, | Company | US | 3U | 2010-12-08 | Reentry 2010-12-22. Was operational. | Test next generation CubeSat subsystems. Demonstrate Northrop Grumman rapid repsonse space satellite technology configuration, build and integration capability. Workforce training. Propulsion that has eight Pumpkin deployable solar panels unfurled into two arrays. |  |
| Perseus 000 | Los Alamos National Laboratory | Institute | US | 1.5U | 2010-12-08 | Reentry 2010-12-30. Was operational. | Demonstrating the ability to build and launch a useful satellite quickly and at low cost, gaining CubeSat build and orbital experience, and validating the LANL design methodology. The satellites were designed and built in less than six months entirely at LANL at very low cost. |  |
| Perseus 001 | Los Alamos National Laboratory | Institute | US | 1.5U | 2010-12-08 | Reentry 2010-12-31. Was operational. | Demonstrating the ability to build and launch a useful satellite quickly and at low cost, gaining CubeSat build and orbital experience, and validating the LANL design methodology. The satellites were designed and built in less than six months entirely at LANL at very low cost. | |
| Perseus 002 | Los Alamos National Laboratory | Institute | US | 1.5U | 2010-12-08 | Reentry 2010-12-30. Was operational. | Demonstrating the ability to build and launch a useful satellite quickly and at low cost, gaining CubeSat build and orbital experience, and validating the LANL design methodology. The satellites were designed and built in less than six months entirely at LANL at very low cost. | |
| Perseus 003 | Los Alamos National Laboratory | Institute | US | 1.5U | 2010-12-08 | Reentry 2010-12-31. Was operational. | Demonstrating the ability to build and launch a useful satellite quickly and at low cost, gaining CubeSat build and orbital experience, and validating the LANL design methodology. The satellites were designed and built in less than six months entirely at LANL at very low cost. | |
| QbX-1 | NRL Naval Center for Space for NRO | Military | US | 3U | 2010-12-08 | Reentry 2011-01-06. Was operational. | For the first two QbX satellites, flight software, antennas, and the TTC radio were built and integrated by the Naval Center for Space, as was the developmental communications payload. The payload consisted of an extendible antenna, a modem, and a radio. The payload featured custom built BIB (Bus to Payload Interface Card ), a custom-built, half-duplex TT&C radio, and experimental LRM (Low Rate Modem) used for the primary communications experiments, and a custom-build deployable dual-antenna with a central UHF (TT&C) monopole surrounded by a quadrifiler helix antenna. |  |
| QbX-2 | NRL Naval Center for Space for NRO | Military | US | 3U | 2010-12-08 | Reentry 2011-01-16. Was operational. | For the first two QbX satellites, flight software, antennas, and the TTC radio were built and integrated by the Naval Center for Space, as was the developmental communications payload. The payload consisted of an extendible antenna, a modem, and a radio. The payload featured custom built BIB (Bus to Payload Interface Card ), a custom-built, half-duplex TT&C radio, and experimental LRM (Low Rate Modem) used for the primary communications experiments, and a custom-build deployable dual-antenna with a central UHF (TT&C) monopole surrounded by a quadrifiler helix antenna. | |
| SMDC-ONE 1 (Space & Missile Defense Command-Operational Nanosatellite Effect) | US Army Space and Missile Defense Command | Military | US | 3U | 2010-12-08 | Reentry 2011-01-12. Was operational. | Demonstrate the ability to rapidly design and develop militarily relevant low cost spacecraft. Receive packetized data from multiple Unattended Ground Sensors (UGS). Transmit that data to ground stations within the SMDC-ONE ground track. Provide real time voice and text message data relay to and from field deployed tactical radio systems. Demonstrate SMDC-ONE operational life time of 12 months or longer. |  |
| Hermes | University of Colorado in Boulder | University | US | 1U | 2011-03-04 | Launch failure | Improve CubeSat communications through the on-orbit testing of a high data-rate communication system that will allow the downlink of large quantities of data, making CubeSat imaging or high-data quantity science easily feasible. Another objective of the project is to create a reproducible and extensible spacecraft bus in the support of future missions. The final specified mission objective is to characterize the typical CubeSat environment. This will occur through the gathering of temperature and magnetic field data throughout the flight. |  |
| HRBE (Explorer-1 Prime, Hiscock Radiation Belt Explorer) | Montana State University | University | US | 1U | 2011-03-04 | Launch failure | Detect the Van Allen radiation belts in honor of the 50th anniversary of Explorer-1. Also demonstrates software technology developed at SSEL that uses a popular chip radio to close a digital data link with standard ham radio hardware allowing people around the world to contact the satellite and download science and housekeeping data. Detect Van Allen radiation belts using a miniature Geiger tube donated by Dr. Van alen to measure the intensity and variability of these electrons in low Earth orbit. |  |
| KySat-1 | Kentucky universities | University | US | 1U | 2011-03-04 | Launch failure | The primary mission objective for KySat-1 is educational outreach. Can be commanded via mobile ground stations using HAM frequencies. These mobile ground stations will be taken to schools around the state for children to have their first direct interaction with a satellite. The goal is to stimulate young minds by bringing aerospace technology to them. Children will be able to upload/download images and audio files, and will also have the capability to command the satellite to take photos using ground station software developed by SSL. A secondary objective for KySat-1 is proof of concept. |  |
| PSSC-2 (Pico Satellite Solar Cell Testbed-2, PSSC Testbed-2, PSSCT-2) | The Aerospace Corporation | Military | US | 3.7 kg | 2011-07-20 | Reentry 2011-12-08. Was operational. | Low cost risk reduction for the upcoming SENSE and Compact Total Electron Content Sensor (CTECS) that characterizes the ionosphere by measurement of the occultation of GPS signals - a precursor of an instrument with the same function on SENSE. PSSC2 also carries over the task from PSSC1 of characterizing the performance of advanced solar cells from Spectrolab and Emcore. Finally, PSSC2 again hosts an upgraded Miniature Tracking Vehicle payload, similar to that flown on PSSC1 that will serve as an orbiting reference for ground tracking systems. |  |
| Jugnu | Indian Institute of Technology Kanpur | University | India | 3U | 2011-10-12 | Was operational until 2013-07-XX. | To develop competence in design, fabrication and usage of micro satellites. Complement the development efforts of the country's satellite application requirements through technology development and validation at the micro satellite level. Development and training of human resources. Strengthen activities in MEMS sensor based technology applications. Micro Imaging System. GPS receiver for locating the position of satellite in the orbit. MEMS based IMU (Inertial Measurement Unit). " |  |
| SRMSat (Sri Ramaswamy Memorial) | SRM University | University | India | 10 kg | 2011-10-12 | Was operational until 2014-XX-XX? (Last DK3WN report 2014-02-11) | The science objective of the mission is to monitor greenhouse gases (GHG), mainly carbon dioxide (CO2) in the atmosphere. Monitor GHG - mainly carbon dioxide (CO2) - in the atmosphere in the near infrared region (900 nm to 1700 nm). A grating spectrometer is employed for monitoring earth-based sources and sinks of anthropogenic and natural sources of GHG. |  |
| AubieSat-1 | Auburn University | University | US | 1U | 2011-10-28 | Was operational until 2013-12-31? | Science mission is to measure average density of ionospheric electrons along line of sight between AubieSat and ground station. Method is to use Faraday rotation effect. Measure rotation of linear polarization angle of EM wave between satellite and ground. Dipole antenna produces linearly polarized wave at satellite.Its mission was to test two different types of solar panel encapsulation for degradation over time. |  |
| DICE-1 (Dynamic Ionosphere CubeSat Experiment, DICE-E) | Utah State University | University | US | 1.5U | 2011-10-28 | Operational? (No recent public news found) | Mapping geomagnetic Storm Enhanced Density (SED) plasma bulge and plume formations in Earth’s ionosphere. Two identical spinning spacecraft measure plasma density and electric fields to determine the how and why of variations in ionospheric plasma density that affect the performance of communications, surveillance, and navigation systems on earth and in space. Each spacecraft carries an electric field probe, two Langmuir probes, and science-grade magnetometer. These instruments perform co-located measurements of plasma density and the electric field to trace the formation and evolutions of SEDS. |  |
| DICE-2 (Dynamic Ionosphere CubeSat Experiment, DICE-Y) | Utah State University | University | US | 1.5U | 2011-10-28 | Operational? (No recent public news found) | Mapping geomagnetic Storm Enhanced Density (SED) plasma bulge and plume formations in Earth’s ionosphere. Two identical spinning spacecraft measure plasma density and electric fields to determine the how and why of variations in ionospheric plasma density that affect the performance of communications, surveillance, and navigation systems on earth and in space. Each spacecraft carries an electric field probe, two Langmuir probes, and science-grade magnetometer. These instruments perform co-located measurements of plasma density and the electric field to trace the formation and evolutions of SEDS. |  |
| E1P U2 (HRBE , Explorer-1' U2, William A. Hiscock Radiation Belt Explorer) | Montana State University | University | US | 1U | 2011-10-28 | Operational (Last DK3WN report 2018-07-27) | Detect Van Allen radiation belts using a miniature Geiger tube donated by Dr. Van Allen to measure the intensity and variability of these electrons in low Earth orbit. |  |
| M-Cubed (COVE, MCUBED) | University of Michigan | University | US | 1U | 2011-10-28 | Was semi-operational. Became conjoined with HBRE and could not receive signals, but transmitted beacon. | Obtain a mid resolution image to date of Earth with at least 60% land mass and a maximum of 20% cloud coverage from a single cubesat platform. MCubed bus with the intention of making it a heritage design, thus allowing for future missions to be flown on the same bus. |  |
| RAX-2 (Radio Aurora Explorer-2) | University of Michigan | University | US | 3U | 2011-10-28 | Was operational until 2013-04-20. | Investigate causes of upper atmospheric/ionospheric plasma turbulence. Study large plasma formations in the ionosphere, the highest region of our atmosphere. These plasma instabilities are known to spawn magnetic field-aligned irregularities (FAI), or dense plasma clouds known to disrupt communication between Earth and orbiting spacecraft. |  |
| e-st@r | Polytechnic University of Turin | University | Italy | 1U | 2012-02-13 | Reentry 2015-01-16. Was operational until 2012-12, communication problems? | Demonstrate the capability of autonomous determination, control and manoeuver, through the development and test in orbit of an A-ADCS entirely designed and manufactured by students. Test in orbit COTS technology and self-made hardware. |  |
| Goliat | University of Bucharest | University | Romania | 1U | 2012-02-13 | Reentry 2014-12-31. No signal? | Obtain a multidisciplinary team of students which, by the end of the project, shall be able to design, integrate and operate a full nanosatellite mission. Developing, integrating, testing, launching and operating a CubeSat type satellite and its components; Designing, developing and integrating a specific satellite payload; Designing and constructing the ground station infrastructure. From a scientific point of view, the Romanian CubeSat will integrate three experiments in LEO: Dose-N – determining the total dose of radiation in orbit; SAMIS – micrometeorites detection in orbit; CICLOP – 3MP digital camera equipped with a custom lens mount. |  |
| MaSat-1 | Budapest University of Technology and Economics | University | Hungary | 1U | 2012-02-13 | Reentry 2015-01-09. Was operational. | Design and implement the basic subsystems of a custom-built satellite. Gain experience in the leadership, logistics, testing and launch arrangement aspects of a complex space project, which are all essential to proceed to the next step. VGA camera. |  |
| PW-Sat | Warsaw University of Technology | University | Poland | 1U | 2012-02-13 | Reentry 2014-10-28. Was operational until 2012-12-23. Power budget problems. | Develop an inexpensive and reliable method of satellite deorbitation by using an expandable structure - SMA (Shape Memory Alloy) based sail. |  |
| ROBUSTA-1A | ROBUSTA | University | France | 1U | 2012-02-13 | Reentry 2015-01-28. No signal. Faint signals for few days, battery charging problems. | Measure the radiation induced degradation of electronic devices. |  |
| UNICubeSat-GG (Gravity Gradient) | Sapienza University of Rome | University | Italy | 1U | 2012-02-13 | Reentry 2015-02-06. Was operational until 2012-02-20. | Study of the gravity gradient enhanced by the presence of a deployable boom. The end faces of the boom are equipped with solar panels for added power generation. The initial mission objective of “in situ atmospheric neutral density measurements in the thermosphere using the Broglio drag balance instrument as payload” was changed in favor of a boom implementation involving the study of a passive attitude control technique, based on gravity gradient stabilization. |  |
| Xatcobeo (Dieste) | University of Vigo | University | Spain | 1U | 2012-02-13 | Reentry 2013-08-31. Was operational. | Main objective of the mission is the deployment of XaTcobeo, a standard based 1U CubeSAT (10 cm x 10 cm x 10 cm) in the space, together with a ground segment. Two payloads: a software defined reconfigurable radio (SRAD) and a system for measuring the amount of ionizing radiation (RDS). There is also an experimental solar panel deployment system (PDM). |  |
| HORYU-2 | Kyushu Institute of Technology | University | Japan | 7.1 kg | 2012-05-17 | Was operational until 2014-07-XX. | 300V photovoltaic power generation in LEO. Demonstration of solar array discharge suppression technologies at 300V. Demonstration of electron emission film (ELF). Demonstration of Commercial-Off-The-Shelf surface potential monitor. Demonstration of debris sensor. Taking photograph of the Earth and distribution of the image for outreach. |  |
| F-1 | FPT University | University | Vietnam | 1U | 2012-07-21 | Reentry 2013-05-09. Was operational? | Educational pico-satellite, carrying a low-resolution camera, a 3-axis magnetometer and several temperature sensors. |  |
| FITSat-1 (NIWAKA) | Fukuoka Institute of Technology | University | Japan | 1U | 2012-07-21 | Reentry 2013-07-04. Was operational. | The main mission is the high-speed transmission of pictures by microwave of 5.8 GHz and the demonstration experiment of low-light-level optical communication by the LED between FITSAT-1 and the ground. | .jpg){kind=small} |
| RAIKO | Tohoku University | University | Japan | 2U | 2012-07-21 | Reentry 2013-08-06. Was semi-operational until 2013-07-15. Command link could not be established. | Demonstration of new electronics or mechanism usable for 50-kg microsatellites, which are CMOS color sensor, CCD color sensor, CCD star sensor, and film deployment mechanism. |  |
| TechEdSat (Technological and Educational Nanosatellite) | NASA Ames Research Center | Agency | US | 1U | 2012-07-21 | Reentry 2013-05-05. Was operational. | TechEdSat demonstrates two new technologies: the first being the Space Plug-and-Play Architecture (SPA) by AAC Microtec, which has the goal of rapidly advancing, reconfigured Nanosatellite technologies based on miniaturized avionics components; and the second, which utilizes two different tracking and communication modules. Photo of earth by Wide Field CCD sensor (WFC). Photo of ISS or earth by Panoramic Color CMOS sensor (PCC). Photo of star by High-sensitive CCD Star Sensor. Demonstration of De-Orbit Mechanism (DOM). Demonstration of Ku-band 13GHz transmitter. |  |
| We Wish (We-Wish) | Meisei Electric | Company | Japan | 1U | 2012-07-21 | Reentry 2013-03-11. Was operational. | Built by members of the Meisei Amateur Radio Club. Carried an infrared camera for environmental studies. The 320 by 256 pixels images of the Earth’s surface were transmitted in approx 110 secs using SSTV. Deployable solar panels. |  |
| TT 1 (TianTuo 1, Tiantuo Yihao Weixing) | National University of Defense Technology | University | China | 9.3 kg | 2012-09-08 | Reentry 2014-11-03. Was operational. | Validation of single-board nano-satellite architecture. On-orbit demonstration of the AIS component. Components/module experiment. Optical earth imaging. Space environment detection experiment. | .jpg){kind=small} |
| AENEAS | University of Southern California | University | US | 3U | 2012-09-13 | Was operational until 2018-05-XX. Batteries didn't hold in eclipse. (Last JA0CAW report 2018-04-028) | Tracking cargo containers over the open ocean with a 1-watt WiFi-like transceiver. This mission uses a custom-built deployable mesh antenna, and stretches the attitude control and power generation capabilities of the Colony I bus to its limits. |  |
| AeroCube-4A (AeroCube 4.5A) | The Aerospace Corporation | Non-profit | US | 1U | 2012-09-13 | Was operational until 2012-11-30. Lost contact. | Solar panel wings that close and open to tune the ballistic coefficient enabling efficient formation flying, three-axis attitude control to 1º absolute accuracy. Launch vehicle environment data logger, which measures launch vibration in-situ, and contains a deorbit drag device that will be deployed at the end of its primary mission (size of 0.3 m2). |  |
| AeroCube-4B (AeroCube 4.5B) | The Aerospace Corporation | Non-profit | US | 1U | 2012-09-13 | Operational? (No recent public news found) | Solar panel wings that close and open to tune the ballistic coefficient enabling efficient formation flying, three-axis attitude control to 1º absolute accuracy. | |
| AeroCube-4C | The Aerospace Corporation | Non-profit | US | 1U | 2012-09-13 | Operational? (No recent public news found) | Solar panel wings that close and open to tune the ballistic coefficient enabling efficient formation flying, three-axis attitude control to 1º absolute accuracy. | |
| CINEMA (CubeSat for Ions, Neutrals, Electrons, & MAgnetic fields) | University of California | University | US | 3U | 2012-09-13 | Was operational until? (No recent news found) | Stereo imaging of magnetospheric energetic neutral atom, multi-point measurements of suprathermal electrons and ions associated with auroral acceleration as well as electron microbursts, and complementary measurements of magnetic fields for particle data. Each satellite is equipped with a SupraThermal Electron, Ion, Neutral (STEIN) instrument covering the energy range ~2-200 keV, and a 3-axis magnetometer of magnetoresistive sensors. |  |
| CP5 | California Polytechnic University | University | US | 1U | 2012-09-13 | Was operational for a short time. Deployed solar sail. | De-orbiting experiment using a thin-film deployable mechanism. The main goal is to identify whether the mechanism can feasibly become a practical solution for mitigating space debris on future small satellites. |  |
| CSSWE (Colorado Student Space Weather Experiment) | University of Colorado | University | US | 3U | 2012-09-13 | Was operational until 2014-12-22. Battery degradation. | Measure the directional differential flux of Solar Energetic Protons (SEPs) and Earth’s radiation belt electrons. |  |
| CXBN (Cosmic X-ray Background Nanosatellite) | Morehead State University/Kentucky Space | University | US | 2U | 2012-09-13 | Was operational until 2013-01-XX. Too weak signal since the beginning for science mission. | Increase the precision of measurements of the Cosmic X-Ray Background (CXRB) in the 30-50 keV range. Constrain models that explain the relative contribution of cosmic X-Ray sources to the CXRB. Produce data that will lend insight into the underlyng physics of the Diffuse X-Ray Background. Provide flight heritage for CXT-based X-Ray gamma-ray detectors and CubeSat technologies. |  |
| Re (STARE A, Space-based Telescopes for the Actionable Refinement of Ephemeris) | Lawrence Livermore National Laboratory | Institute | US | 3U | 2012-09-13 | Semi-operational, some problems with communication. | Observe objects that are predicted to pass close to a valuable space asset based on conjunction analysis using the AFSPC (Air Force Space Command) catalog. Transmit images and positions of observations to the ground. Refinement of orbital parameters of space objects to reduce uncertainty in position estimation and improve accuracy of conjunction analysis. Cassegrain telescope and an attitude control capability limited to torque coils. |  |
| SMDC-ONE 2.1 (Able) | US Army Space and Missile Defense Command | Military | US | 3U | 2012-09-13 | Operational? (No public news found) | Demonstrate the ability to rapidly design and develop militarily relevant low cost spacecraft. Receive packetized data from multiple Unattended Ground Sensors (UGS). Transmit that data to ground stations within the SMDC-ONE ground track. Provide real time voice and text message data relay to and from field deployed tactical radio systems. Demonstrate SMDC-ONE operational life time of 12 months or longer. |  |
| SMDC-ONE 2.2 (Baker) | US Army Space and Missile Defense Command | Military | US | 3U | 2012-09-13 | Operational? (No public news found) | Demonstrate the ability to rapidly design and develop militarily relevant low cost spacecraft. Receive packetized data from multiple Unattended Ground Sensors (UGS). Transmit that data to ground stations within the SMDC-ONE ground track. Provide real time voice and text message data relay to and from field deployed tactical radio systems. Demonstrate SMDC-ONE operational life time of 12 months or longer. |  |
| AAUSAT3 (AAUSAT-3) | Aalborg University | University | Denmark | 1U | 2013-02-25 | Was operational until 2014-10-01. Power production gradually decreased until it was too low. | The AAUSAT3 mission is to test two AIS receivers developed by students. Proof of concept of our very strict modular design with no central OBC/CDH managing the satellite. |  |
| STRaND-1 (Surrey Training, Research and Nanosatellite Demonstrator) | Surrey Satellite Technology | Company | UK | 3U | 2013-02-25 | Operational (Last DK3WN report 2018-06-02). Went silent 2013-03-30, but came back 2013-07-23. | Technology path finding for future commercial operations. Modern Commercial Off The Shelf (COTS) Android smartphone as a payload. BPS (Butane Propulsion Subsystem), PPT (Pulsed plasma Thruster). |  |
| TUGSat 1 (Technische Universität Graz Satellit), BRITE-Austria (BRIght-star Target Explorer - Austria, BRITE-A, CanX 3B) | Graz University of Technology | University | Austria | 7 kg | 2013-02-25 | Operational (http://www.tugsat.tugraz.at/) | Investigation of the brightness oscillations of massive luminous stars by differential photometry. The scientific instrument is an optical camera with a high-resolution CCD to take images from distant stars with magnitude of 3.5. |  |
| UniBRITE-1 (BRITE-U, CanX 3A) | University of Vienna | University | Austria | 7 kg | 2013-02-25 | Operational (http://www.tugsat.tugraz.at/) | Investigation of the brightness oscillations of massive luminous stars by differential photometry. The scientific instrument is an optical camera with a high-resolution CCD to take images from distant stars with magnitude of 3.5. | |
| BEESAT-2 | Berlin Technical University | University | Germany | 1U | 2013-04-19 | Was operational? (Last DK3WN report 2017-02-04) | The primary mission objective is the technical testing of miniaturized reaction wheels for attitude stabilization of a pico using a camera for Earth observation as an exemplary payload. The secondary mission objective is to embed the satellite operation in the courses of the subject area. |  |
| BEESAT-3 | Berlin Technical University | University | Germany | 1U | 2013-04-19 | Operational since 2018-01-17? No signal for years. (Last DK3WN report 2018-03-18) | Primary objective is the practical training of students. Secondary mission objective is the verification of S-band transmitter HISPICO ( H ighly I ntegrated S band link for PICO and nano satellites) in orbit. |  |
| Dove-2 | Planet Labs | Company | US | 3U | 2013-04-19 | Operational | Build a low-cost imaging satellite with non-space, COTS components. Demonstrate the ability to design, produce and operate satellites on short schedules and low cost. Show that a bus constrained to the 3U cubesat form factor can viably host a small camera payload. |  |
| OSSI-1 | Open Source Satellite Initiative | Individual | South Korea | 1U | 2013-04-19 | Reentry 2013-07-08. No signal. | Open Source Satellite Initiative. |  |
| SOMP (Students Oxygen Measurement Project) | Dresden University of Technology | University | Germany | 1U | 2013-04-19 | Operational (Last DK3WN report 2018-05-23) | Measuring atomic oxygen using an oxygen electrolyte sensor. Testing of flexible thin film solar cells |  |
| Dove-1 | Planet Labs | Company | US | 3U | 2013-04-21 | Reentry 2013-04-27. Was operational. | Build a low-cost imaging satellite with non-space, COTS components. Demonstrate the ability to design, produce and operate satellites on short schedules and low cost. Show that a bus constrained to the 3U cubesat form factor can viably host a small camera payload. | |
| PhoneSat 1.0a (Graham) | NASA Ames | Agency | US | 1U | 2013-04-21 | Reentry 2013-04-27. Was operational. | Off-the-shelf commercial smartphone as the control system for the satellite and used a UHF radio beacon to transmit data and images to the ground. The technology objective was to demonstrate the application of consumer electronics as the basis of an extremely low-cost satellite bus. 12 lithium-ion batteries, a Nexus One running the Android 2.3.3 and a StenSat radio at 437.425 MHz. Has an accelerometer and a magnetometer. On day 1, Bell and Graham transmitted health data (battery levels, temperatures, magnetometer sensors, accelerometer sensors). On day 2 (and beyond) Bell and Graham took 100 pictures. | .jpg){kind=small} |
| PhoneSat 1.0b (Bell) | NASA Ames | Agency | US | 1U | 2013-04-21 | Reentry 2013-04-27. Was operational. | Off-the-shelf commercial smartphone as the control system for the satellite and used a UHF radio beacon to transmit data and images to the ground. The technology objective was to demonstrate the application of consumer electronics as the basis of an extremely low-cost satellite bus. 12 lithium-ion batteries, a Nexus One running the Android 2.3.3 and a StenSat radio at 437.425 MHz. Has an accelerometer and a magnetometer. On day 1, Bell and Graham transmitted health data (battery levels, temperatures, magnetometer sensors, accelerometer sensors). On day 2 (and beyond) Bell and Graham took 100 pictures. | .jpg){kind=small} |
| PhoneSat 2.0a (Alexander) | NASA Ames | Agency | US | 1U | 2013-04-21 | Reentry 2013-04-27. Was operational. | Alexander's mission includes charging its batteries, turning on its systems, and sending sensor data. Mission controllers may try to de-tumble the satellite and reduce its spinning rate to less than 5deg/sec using the magnetic torquers. A newer phone (Nexus S) running the Android 2.3.3 operating system, 4 Li-Ion batteries, solar panels, a router, and magnetic torquers that are used to de-tumble the satellite. Alexander has an accelerometer, a magnetometer, a gyroscope and a StenSat radio operating at 437.425 MHz. | .jpg){kind=small} |
| CubeBug-1 (Capitán Beto) | Satellogic | Company | Argentina | 2U | 2013-04-26 | Was operational until? | Open Nano-Satellite platform, first technology demonstration satellite. An ARM based on-board computer, a nano-reaction wheel with its driver circuit and a low resolution camera to image stars, all based on COTS components. |  |
| NEE-01 Pegaso | Ecuadorian Space Agency | Agency | Ecuador | 1U | 2013-04-26 | Was semi-operational until 2017-11-XX. Collided with Tsyklon debris, but was heard through NEE-02. (Personal contact 2018-08-07) | Survive the LEO space environment and transmit telemetry for at least a year. Transmit live video feed from orbit and On-Screen telemetry. Test the Space Environment Attenuation Manifold NEMEA. Test the passive release/deploy technology on multi phase nano solar arrays. Test the high energy generation technology for small spacecrafts. Test the ARGOS-MINOTAUR hyper amplification matrix. |  |
| TURKSAT-3USAT | ITU (Istanbul Technical University | University | Turkey | 3U | 2013-04-26 | Was operational until 2013-04-27. Became silent after a day. | Build Turkey’s first communication CubeSat. The 3USAT includes many sensors and a camera for taking pictures, as well. The main payload of the 3USAT is a linear transponder operating in VHF/UHF. |  |
| ESTCube-1 | University of Tartu | University | Estonia | 1U | 2013-05-07 | Was operational until 2015-05-19. Solar panel degradation lead to negative power production state and batteries were completely depleted. No more signals heard after that. Probably the command to silence the satellite went through. | Test the deployment of a 10 m tether, which is an integral part of the electric solar wind sail development. Take picture of the Earth and, if possible Estonia. The project will also be used to build Estonian infrastructure for future space projects and to educate space engineers. |  |
| ArduSat | Spire (Nanosatisfi) | Company | US | 1U | 2013-08-03 | Reentry 2014-04-16. Was operational. | Mission is to provide a platform on which students and DIY space enthusiasts may design and run their own space-based Arduino experiments. Identical with ArduSat-X. The Arduino processors may sample data from the satellite’s imaging payload, a 1.3 megapixel optical CMOS camera module, and / or any of the satellite’s onboard sensors, which includes photolux sensor, IR temperature, PCB temperature, 3-axis magnetometer, Geiger counter, 6-DOF IMU, and MEMS gyros. |  |
| ArduSat-X | Spire (Nanosatisfi) | Company | US | 1U | 2013-08-03 | Reentry 2014-04-15. Was operational. | Mission is to provide a platform on which students and DIY space enthusiasts may design and run their own space-based Arduino experiments. Identical with ArduSat-1. The Arduino processors may sample data from the satellite’s imaging payload, a 1.3 megapixel optical CMOS camera module, and / or any of the satellite’s onboard sensors, which includes photolux sensor, IR temperature, PCB temperature, 3-axis magnetometer, Geiger counter, 6-DOF IMU, and MEMS gyros. |  |
| Pico Dragon (Picodragon) | Vietnam National Satellite Center | Agency | Vietnam | 1U | 2013-08-03 | Reentry 2014-02-28. Was operational. | Taking pictures of the Earth. Collecting the environment data by sensors which are equipped on the satellite. Communicating and exchanging the data with the ground station. |  |
| TechEdSat-3p | NASA Ames Research Center | Agency | US | 3U | 2013-08-03 | Reentry 2014-01-16. Was operational. | Demonstrate two new technologies. The first is a passive deorbiting system that uses a uniquely designed drag device (Exo-Brake) to perform a rapid de-orbit and re-entry. The second will demonstrate the use of an Iridium modem combined with a GPS receiver to communicate accurate positional and de-orbit information. Eventually, these will be combined to provide controlled sample return capability from the ISS or other orbiting platforms. |  |
| POPACS (Polar Orbiting Passive Atmospheric Calibration Sphere) | Utah State University | University | US | 3U | 2013-09-29 | Passive spheres. No signal. | 3 spheres. Assess changes in the density of the upper atmosphere in response to heightened solar activity. Will remain in orbit for approximately 10, 12.5 and 15 years. Three 10 cm spheres whose external appearances are identical. However, they differ in their masses. The three masses are 1 kg, 1.5 kg, and 2 kg. In their launch configuration, the three spheres are separated by a set of two spacers and two end plates. |  |
| Black Knight 1 (BK 1) | West Point Military Academy | University | US | 1U | 2013-11-20 | Reentry 2015-07-16. No signal | Develop a low cost experimental spacecraft with experimental and operational significance. Educate future Army leaders on a wide range of space related topics in order to develop more "space savvy" junior leaders. Build a solid foundation for satelltie development at West Point in order to expand into more advanced spacecraft projects in the future. Test a passive two-axis attitude control system as well as an Earth imaging camera. |  |
| CAPE-2 | University of Louisiana at Lafayette | University | US | 1U | 2013-11-20 | Reentry 2014-10-23. Was semi-operational? Batteries dead and only works in sunlight. | To develop a cutting-edge Cubesat communication platform. Secondary Missions: Local Educational Outreach, Deployable Solar Panels, using UHF Radio and VHF Radio. Payloads: Voice Repeater, Text to Speech, Tweeting, Digipeater, File Storage and Transfers, DTMF Query |  |
| ChargerSat-1 (ChargerSat 1.2) | University of Alabama in Huntsville | University | US | 1U | 2013-11-20 | Reentry 2016-03-19. No signal. | Improve communications for picosatellite operations. Demonstrate passive nadir axis stabilization for picosatellite attitude control. Improve solar power collection for picosatellite operations. |  |
| COPPER (Close Orbiting Propellant Plume and Elemental Recognition) | Saint Louis University | University | US | 1U | 2013-11-20 | Reentry 2016-02-04. No signal. | Imaging mission: Flight-test the abilities of a commercially available compact uncooled microbolometer array to take infrared images of Earth’s oceans and atmosphere. Radiation mission: Improve the predictive performance modeling of radiation effects on small, modern space electronics devices by collecting radiation particle collision data from electronics monitoring experiments and relaying the data to the ground. The FLIR Tau 320 Microbolometer Array, with a custom-built interface board (giving us greater control over the imager and allowing us to store 14-bit images at 30 frames per second). A pathfinder payload provided by Vanderbilt University, in preparation for the Argus mission. The Commodore payload will demonstrate basic interfaces and functionality of their radiation-effects monitoring payload controller |  |
| DragonSat 1 | Drexel University | University | US | 1U | 2013-11-20 | Reentry 2016-08-31. No signal. | Educate undergraduate students and to provide hands-on experience in space system development. Take pictures of aurora (northern and southern lights) to observe the radiation dissipation intensity during the solar events, and to perform technology demonstration of boom deployment mechanism in space. The payload of the DragonSat-1 will consist of a package of various sensors, including one µCam camera, one HMC2003 magnetometer, one MMA7260QT accelerometer, and seven LM335 temperature sensors. |  |
| Firefly | NASA Goddard Space Flight Center | Agency | US | 3U | 2013-11-20 | Reentry 2017-11-01. Was operational. | Investigate Terrestrial Gamma-ray Flashes (TGFs). How are TGFs produced? Current evidence suggests production deep in the atmosphere, near the tops of thunderclouds. Another possibility, which may occur at the same time, is high-altitude production in the 30-80 km altitude range. What types of lightning produce TGFs, and how do they differ from non-TGF lightning? How common ar the TFGs? How large an area do they cover? What effect do they have on the upper atmosphere and near-Earth space? To what extent do they represent a source of energetic electrons for the inner radiation belt? |  |
| Ho‘oponopono 2 (H2) | University of Hawaii at Manoa | University | US | 3U | 2013-11-20 | No signal | Continue a long-existing radar calibration service, provided currently with a microsatellite (RADCAL) and with a payload suite on a meteorological mission (DMSP-15). Demonstrate the collection of accurate (< 5 m) ephemeris data. Provide radar calibration information at an average rate of five radar ranges every day for 1 year. | .png){kind=small} |
| Horus (STARE B, Space-Based Telescopes for Actionable Refinement of Ephemeris)) | Lawrence Livermore National Laboratory | Institute | US | 3U | 2013-11-20 | Reentry 2018-04-26. Was semi-operational? | Observe objects that are predicted to pass close to a valuable space asset based on conjunction analysis using the AFSPC (Air Force Space Command ) catalog. Refinement of orbital parameters of space objects to reduce uncertainty in position estimation and improve accuracy of conjunction analysis. Full set of reaction wheels for attitude control and a more sensitive imager |  |
| KYSAT II (KySat-2) | Kentucky universities | University | US | 1U | 2013-11-20 | Reentry 2015-02-12. Was operational, but batteries dead. | The primary objective is proof of concept. Will demonstrate key technologies developed by University of Kentucky and Morehead University students. These include a distributed network computing architecture, power and radio systems, and a “stellar gyroscope” for attitude determination. 5 megapixel digital camera, a temperature sensor, a 3-axis MEMS rate gyroscope, a 3-axis magnetometer, and a “stellar gyroscope” which was developed by University of Kentucky students. |  |
| NPS-SCAT (Naval Postgraduate School Solar Cell Array Tester) | Naval Postgraduate School | University | US | 1U | 2013-11-20 | Reentry 2015-10-28. Was operational until 2014-11-21? First beacon heard | Solar Cell Measurement System (SMS), as its payload. This experiment measures the characteristics of a solar cell to gain an understanding of how the experimental solar cells degrade over time due to interactions with the space environment. |  |
| ORS Tech 1 | John Hopkins University | University | US | 3U | 2013-11-20 | Reentry 2015-03-23. Was operational. | Created a flexible and modular, Multi-Mission Nanosatellite (MMN) spacecraft architecture for low-cost execution of critical missions. |  |
| ORS Tech 2 | John Hopkins University | University | US | 3U | 2013-11-20 | Reentry 2015-04-03. Was operational. | Created a flexible and modular, Multi-Mission Nanosatellite (MMN) spacecraft architecture for low-cost execution of critical missions. | |
| ORSES (ORS 1) | Space & Missile Defense Command | Military | US | 3U | 2013-11-20 | Reentry 2016-01-03. Was operational until 2013-11-25. | Provide communications and data capabilities for underserved tactical users. Based on the SMDC-ONE satellite that flew in December 2010 and on the OUTSat mission with an upgraded communication radio and encryption. |  |
| PhoneSat 2.4a | NASA Ames Research Center | Agency | US | 1U | 2013-11-20 | Reentry 2017-01-31. Was operational. | Test the smartphone's capability as communication technology for nanosatellites and as hardware to manage pointing, taking images and software execution. Several improvements over the previous mission, including a two-way radio to enable command of the satellite from the ground, solar arrays to enable it to be operational for up to a year, and a system for attitude control. |  |
| Prometheus 1-1 | Los Alamos National Laboratory | Military | US | 1.5U | 2013-11-20 | Reentry 2015-12-12. Was operational. | Dual objective of evaluating new low-cost development and operations methodologies while also assessing the operational utility that can be provided with CubeSat technology. |  |
| Prometheus 1-2 | Los Alamos National Laboratory | Military | US | 1.5U | 2013-11-20 | Reentry 2015-12-10. Was operational. | Dual objective of evaluating new low-cost development and operations methodologies while also assessing the operational utility that can be provided with CubeSat technology. Tested for their ability to transmit audio, video and data from remote field units to ground stations using over-the-horizon SATCOM. | |
| Prometheus 1-3 | Los Alamos National Laboratory | Military | US | 1.5U | 2013-11-20 | Reentry 2015-12-08. Was operational. | Dual objective of evaluating new low-cost development and operations methodologies while also assessing the operational utility that can be provided with CubeSat technology. | |
| Prometheus 1-4 | Los Alamos National Laboratory | Military | US | 1.5U | 2013-11-20 | Reentry 2015-12-13. Was operational. | Dual objective of evaluating new low-cost development and operations methodologies while also assessing the operational utility that can be provided with CubeSat technology. | |
| Prometheus 1-5 | Los Alamos National Laboratory | Military | US | 1.5U | 2013-11-20 | Reentry 2015-11-29. Was operational. | Dual objective of evaluating new low-cost development and operations methodologies while also assessing the operational utility that can be provided with CubeSat technology. | |
| Prometheus 1-6 | Los Alamos National Laboratory | Military | US | 1.5U | 2013-11-20 | Reentry 2015-12-10. Was operational. | Dual objective of evaluating new low-cost development and operations methodologies while also assessing the operational utility that can be provided with CubeSat technology. | |
| Prometheus 1-7 | Los Alamos National Laboratory | Military | US | 1.5U | 2013-11-20 | Reentry 2015-12-05. Was operational. | Dual objective of evaluating new low-cost development and operations methodologies while also assessing the operational utility that can be provided with CubeSat technology. | |
| Prometheus 1-8 | Los Alamos National Laboratory | Military | US | 1.5U | 2013-11-20 | Reentry 2015-12-01. Was operational. | Dual objective of evaluating new low-cost development and operations methodologies while also assessing the operational utility that can be provided with CubeSat technology. | |
| SENSE SV1 (Space Environmental NanoSat Experiment) | US Air Force | Military | US | 3U | 2013-11-20 | Reentry 2015-03-21. Was semi-operational. | Develop best practices for operational CubeSat/NanoSat procurement, development, test, and operations. To mature CubeSat bus and sensor component technology readiness levels and to demonstrate the operational utility of CubeSat measurements by flowing validated, low-latency data into operational space weather models. 3-axis stabilized with star cameras for attitude determination and are equipped with a Compact Total Electron Density Sensor (CTECS) to provide radio occultation measurements of total electron content and L-band scintillation. One satellite has a Cubesat Tiny Ionospheric Photometer (CTIP) monitoring 135.6 nm photons produced by the recombination of O+ ions and electrons. |  |
| SENSE SV2 (Space Environmental NanoSat Experiment) | US Air Force | Military | US | 3U | 2013-11-20 | Was operational until 2015-04-30. | Develop best practices for operational CubeSat/NanoSat procurement, development, test, and operations. To mature CubeSat bus and sensor component technology readiness levels and to demonstrate the operational utility of CubeSat measurements by flowing validated, low-latency data into operational space weather models. The other satellite has a Wind Ion Neutral Composite Suite (WINCS) to acquire simultaneous co-located, in situ measurements of atmospheric and ionospheric density, composition, temperature and winds/drifts. Mission data will be used to improve current and future space weather models and demonstrate the utility of data from CubeSats for operational weather requirements. |  |
| SwampSat | University of Florida | University | US | 1U | 2013-11-20 | Reentry 2015-12-13. No signal. | Demonstrate on orbit precision three axis attitude control using a pyramidal configuration of control moment gyroscopes. |  |
| TJ3sat | Thomas Jefferson High School for Science and Technology | School | US | 1U | 2013-11-20 | Reentry 2015-09-17. No signal. | Provide educational resources to other K-12 education institutions to foster interest in aerospace through the successful design and flight of a CubeSat. Educational and TextSpeak module, which converts serial data into spoken voice. |  |
| Trailblazer (SPA-1 Trailblazer) | University of New Mexico | University | US | 1U | 2013-11-20 | Reentry 2016-05-22. No signal. | Proof-of-concept flight for an AFRL (Air Force Research Laboratory) sponsored bus design called SPA (Space Plug-and-play Architecture). The PnP (Plug-and-Play) type architecture is a capability that will allow for rapid development and delivery of satellite and defense systems. |  |
| Vermont Lunar Cubesat | Vermont Technical College/ University of Vermont | University | US | 1U | 2013-11-20 | Reentry 2015-11-21. Was operational. | Explore the technologies required for building a viable CubeSat device that can orbit and/or land on the moon. Test the navigation components to go to the Moon. |  |
| $50Sat (50-Dollarsat, Eagle 2, Morehead-OSCAR-76) | Morehead State University | University | US | PocketQube 1.5p | 2013-11-21 | Reentry 2018-05-19. Was operational until 2015-07-19. http://amsat-uk.org/2015/08/30/50sat-falls-silent/ | Demonstrate that very low cost satellites are viable in low Earth orbit. The low build cost of $50SAT (less than $250 in parts) means that Engineering models are readily affordable by schools and colleges. The PocketQube chassis has no precision mechanical parts and can be built from locally obtained sheet metal. |  |
| BRITE-PL-1 Lem (CanX 3C) | The Space Research Centre of the Polish Academy of Sciences | Institute | Poland | 6 kg | 2013-11-21 | Operational (http://www.tugsat.tugraz.at/) | Investigation of the brightness oscillations of massive luminous stars by differential photometry. The scientific instrument is an optical camera with a high-resolution CCD to take images from distant stars with magnitude of 3.5. |  |
| CINEMA 2 (TRIO 2, KHUSAT 1) | Kyung Hee University | University | South Korea | 3U | 2013-11-21 | Was semi-operational until 2014-11-28? | Stereo imaging of magnetospheric energetic neutral atom, multi-point measurements of suprathermal electrons and ions associated with auroral acceleration as well as electron microbursts, and complementary measurements of magnetic fields for particle data. MAGIC (MAGnetometer from Imperial College). STEIN (SupraThermal Electrons Ions & Neutrals) particle detector. |  |
| CINEMA 3 (TRIO 3, KHUSAT 2) | Kyung Hee University | University | South Korea | 3U | 2013-11-21 | No signal | Stereo imaging of magnetospheric energetic neutral atom, multi-point measurements of suprathermal electrons and ions associated with auroral acceleration as well as electron microbursts, and complementary measurements of magnetic fields for particle data. MAGIC (MAGnetometer from Imperial College). STEIN (SupraThermal Electrons Ions & Neutrals) particle detector. |  |
| CubeBug-2 (Manolito) | Satellogic | Company | Argentina | 2U | 2013-11-21 | Operational (Last DK3WN report 2018-05-31) | Open Nano-Satellite platform, first technology demonstration satellite. As payload on this first mission, some custom designed components will be tested: an ARM based on-board computer, a nano-reaction wheel with its driver circuit and a low resolution camera to image stars, all based on COTS components. It will carry an amateur radio AX.25 packet radio digipeater. As payload on this second mission, some custom designed components will be tested: an antenna, solar panels, and an on-board computer, a camera, a GPS transceiver and a software defined radio based on COTS components. |  |
| Delfi-n3Xt | Delft University of Technology | University | Netherlands | 3U | 2013-11-21 | Was operational until 2014-02-21. Contact lost. | Education, technology demonstration and nanosatellite bus advancement. Cold gas mircopropulsion. The experimental ISIS Transceiver (ITRX). |  |
| Dove-3 | Planet Labs | Company | US | 3U | 2013-11-21 | Operational | Build a low-cost imaging satellite with non-space, COTS components. Demonstrate the ability to design, produce and operate satellites on short schedules and low cost. Show that a bus constrained to the 3U cubesat form factor can viably host a small camera payload. |  |
| Dove-4 | Planet Labs | Company | US | 3U | 2013-11-21 | Deployment failure. Failed to separate or never deployed from Unisat-5. | Build a low-cost imaging satellite with non-space, COTS components. Demonstrate the ability to design, produce and operate satellites on short schedules and low cost. Show that a bus constrained to the 3U cubesat form factor can viably host a small camera payload. | |
| FUNcube-1 (AO-73) | AMSAT-UK | Non-profit | UK | 1U | 2013-11-21 | Operational (Last DK3WN report 2018-07-27) | Goal of enthusing and educating young people about radio, space, physics and electronics. 435 to 145 MHz Linear Transponder for SSB/CW operation. Carries a materials science experiment, from which the school students can receive telemetry data and which they can compare to the results they obtained from similar reference experiments in the classroom. This experiment resembles the Leslie's Cube experiment. |  |
| GOMX-1 (GATOSS, Global Air Traffic Awareness and Optimizing through Spaceborne Surveillance) | GomSpace | Company | Denmark | 2U | 2013-11-21 | Operational, but ADS-B payload stopped working on 2014-05-07. (Last DK3WN report 2018-05-24) | Perform research and experimentation in space related to Software Defined Radio (SDR) with emphasis on receiving ADS-B signal from commercial aircraft over oceanic areas. As a secondary payload the satellite flies a NanoCam C1U colour camera for Earth observation experimentation. Track trans-oceanic flights by reception of the ADS-B signal signal emitted by aircraft. |  |
| HiNCube | Narvik University College | University | Norway | 1U | 2013-11-21 | No signal | Create a satellite platform for future scientific missions as well as increase the interest for science and space technology in Norway. Take pictures of the Earth from a Low Earth Orbit (LEO) and provide the students with experience in managing and working in a big multidisciplinary project. |  |
| HumSat-D | University of Vigo | University | Spain | 1U | 2013-11-21 | Was operational until 2015-02--XX? | Satellite-based system for connecting a set of users with a network of worldwide distributed sensors which they have previously deployed. Educational objectives such as: provide hands-on-project experience on a space project to engineering/science students, promote international cooperation among universities about space technology, transfer technology to universities from developing countries. Sensors will be responsible for acquiring user data and for transmitting it to the satellites through an standard radio interface. Users will be able to define their own sensors, for monitoring different types of parameters; for example, water temperature or wind speed. Once data has been transported by HumSAT satellites, authorized users will be able to access it through an Internet connection. |  |
| ICUBE-1 | Islamabad Institute of Science and Technology | Institute | Pakistan | 1U | 2013-11-21 | Was operational until 2014-01-08? | Provide students the skills and experiences required to build pico and nano satellites. The primary mission objective of ICUBE is to design, develop, integrate and launch picosatellite standard CubeSat. The secondary objectives are the communication, in-orbit operation and collection of the payload data. Imaging payload with a small low resolution CMOS sensor. The C3188A imaging module uses Omnivision’s CMOS image sensor OV7620. The camera will be mounted on the Z+ face of the ICUBE and can take continental scale images. |  |
| MOVE (First-MOVE, Munich Orbital Verification Experiment) | Technical University of München | University | Germany | 1U | 2013-11-21 | Was operational until 2013-12-21. On-Board Computer damaged and only name is sent. | Test triple junction GaAs / Ge Solar Cells (EADS Astrium). |  |
| NEE-02 Krysaor | Ecuadorian Space Agency | Agency | Ecuador | 1U | 2013-11-21 | Operational. In hibernation, but expected to wake up at the end of year (Personal contact 2018-08-07) | Serving education and also acting as orbital sentinels watching for possible threats from small NEOs in last phase of atmospheric entry and helping to catalog orbital debris. Also it has the latest advances in active deployment of its solar arrays, high speed digital transmission and a higher resolution video camera. |  |
| OPTOS (Optical Nanosatellite) | National Institute of Aerospace Technology | Agency | Spain | 3U | 2013-11-21 | Was operational? (No recent public news found) | Demonstrate new technologies. Distributed OBDH (On-Board Data Handling) subsystem based on FPGAs (Floating Point Gate Arrays), and CPLDs (Complex Programmable Logic Devices), an optical wireless communication system (OBCom) with a reduced CAN (Controller Area Network) protocol is implemented, internal structure is based on composite materials. |  |
| Pocket-PUCP (PUCP-Pocket) | Pontifical Catholic University of Peru | University | Peru | 0.127 kg | 2013-11-21 | Was operational until? | Transmit temperature measurements. |  |
| PUCPSat-1 | Pontifical Catholic University of Peru | University | Peru | 1U | 2013-11-21 | Was operational until? | Deploy PUCP-Pocket and test ADCS system with custom micro wheels and research thermal design for future satellites. |  |
| QubeScout 1 | Maryland State University | University | US | PocketQube 2.5p | 2013-11-21 | Was operational? | Test a micro sun-sensor that can be used to find and point instruments toward the sun |  |
| T-LogoQube (BeakerSat 1, MagPocketQube, Eagle-1) | Sonoma State University | University | US | PocketQube 2.5p | 2013-11-21 | Was operational until? | T-LogoQube is measuring the Earth's magnetic field in order to determine the satellite's pointing direction. |  |
| Triton-1 | ISIS (Innovative Solutions In Space) | Company | Netherlands | 3U | 2013-11-21 | Was operational until 2016? | Test a highly innovative payload for ocean traffic monitoring developed by ISIS, AIS receiver, which is major step towards realizing a commercial constellation that will provide global shipping information to customers worldwide. |  |
| UWE-3 | University of Würzburg | University | Germany | 1U | 2013-11-21 | Operational (Last DK3WN report 2018-06-19) | Demonstrate the use of a real-time miniature attitude determination and control system on-board the satellite, using a variety of sensors, magnetic torques and one reaction wheel. An advanced modular and flexible architecture of the pico-satellite bus, in order to increase robustness, reduce mass and add reliability to the overall system. |  |
| VELOX-P2 (VELOX-PII) | Nanyang Technological University | University | Singapore | 1U | 2013-11-21 | Was operational? (No recent news found) | Train engineers to support the Singapore space industry. Technology demonstration platform and a design validation for NTU future satellite missions. The mission objective is to qualify several in-house built hardware and software components, such as the fault tolerant power system, attitude determination & control algorithms, fine sun sensor, solar panel. |  |
| WNISAT 1 (Weather News Inc. Satellite 1) | Weather News Inc. | Company | Japan | 10 kg | 2013-11-21 | Operational (Personal contact 2018-08-07, no public news found) | Observation of sea ice in the Arctic waters. Monitoring of the Northern sea routes and of the CO2 content of the atmosphere. |  |
| Wren | STADOKO UG | Company | Germany | PocketQube 1p | 2013-11-21 | Was operational until 2013-11-24. Failed after a short time. | Crowd-funded femto-satellite by start-up company STADOKO to test miniaturized thrusters, 3-axis control and a new image based navigation system. It is equipped with a camera system to take pictures of the Earth, Sun and Deep Space. In addition to the conventional gyro- and magnetic field attitude sensors, those three components will constitute an adaptive feedback guidance system. Camera and 4 pulsed plasma thrusters. A 3 axis reaction wheel and a colour camera. |  |
| ZACUBE-1 (TshepisoSat) | Cape Peninsula University of Technology | University | South Africa | 1U | 2013-11-21 | Operational (Last DK3WN report 2018-06-26) | Training of post-graduate students in Satellite Systems Engineering. Earth observation using a visible band matrix imager payload and an S-Band payload data transmitter (2.4 to 2.45 GHz). UHF Store & Forward system (70 cm amateur band). Experimental 115200 bps L-Band to S-band data transponder. HF beacon payload for characterization of Hermanus Magnetic Observatory’s Dual Auroral Radar Network antenna at SANAE base in Antarctica (14 MHz). Space-weather experiment to take measurements in the ionosphere. High frequency (HF) beacon transmitter that will be used to help characterize the Earth’s ionosphere and to calibrate SANSA's (South African National Space Agency) auroral radar installation at the SANAE base in Antarctica |  |
| AeroCube-5A | The Aerospace Corporation | Non-profit | US | 1.5U | 2013-12-06 | Operational? (No recent public news found) | Demonstrate new technologies for pointing and tracking between two identical CubeSats and to demonstrate a deorbit device. |  |
| AeroCube-5B | The Aerospace Corporation | Non-profit | US | 1.5U | 2013-12-06 | Operational? (No recent public news found) | Demonstrate new technologies for pointing and tracking between two identical CubeSats and to demonstrate a deorbit device. |  |
| ALICE (AFIT LEO iMESA CNT Experiment) | Air Force Institute of Technology | University | US | 3U | 2013-12-06 | Operational? (No public news found) | The satellite carries the iMESA (Integrated Miniaturized Electrostatic Analyzer) and the CNT (Carbon Nano-Tube) experiments. The carbon nanotube array on ALICE represents a significant enhancement in small satellite propulsion. iMESA (Integrated Miniaturized Electrostatic Analyzer) and the CNT (Carbon Nano-Tube) experiments. Georgia Tech manufactured the carbon nanotube array and AFIT built the payload and assembled and tested the satellite. Performance of the carbon nanotube array will be done using custom built integrated miniaturized electrostatic analyzer (iMESA) sensors, based on designs provided by the U.S. Air Force Academy. |  |
| CUNYSAT 1 | City University of New York (CUNY) | University | US | 1U | 2013-12-06 | No signal | Design, assemble and test a basic pathfinder with mostly commericial-off-the-shelf components, 2: provide workforce experiences for undergraduate students and 3. to build capacity for faculty research. Gather information on battery and solar cell efficiencies as well as satellite spin. The original science objective was an investigation of ionospheric disturbances but this was de-scoped due to power constraints and postponed for another CubeSat mission. |  |
| FIREBIRD A (FU1, Focused Investigations of Relativistic Electron Burst, Intensity, Range, and Dynamics) | Montana State University/ University of New Hampshire | University | US | 1.5U | 2013-12-06 | Was operational, awakened 2014-04-12 and operated until 2014-09-15. | Space weather Cubesat mission to resolve the spatial scale size and energy dependence of electron microbursts in the Van Allen radiation belts. |  |
| FIREBIRD B (FU2, Focused Investigations of Relativistic Electron Burst, Intensity, Range, and Dynamics) | Montana State University/ University of New Hampshire | University | US | 1.5U | 2013-12-06 | Was operational until 2014-01-21, latched up. Occasional beacons afterwards. | Space weather Cubesat mission to resolve the spatial scale size and energy dependence of electron microbursts in the Van Allen radiation belts. |  |
| IPEX (CP8, Intelligent Payload Experiment) | California Polytechnic State University | University | US | 1U | 2013-12-06 | Was operational until 2015-01-30. | Validate onboard instrument processing and autonomous payload operations for the proposed NASA HYperSPectral Infra-Red Instrument (HyspIRI) mission. PEX carries several low-resolution (3 mega pixels) Omnivision OV3642 cameras as a stand in for actual science instruments on future NASA missions. These cameras are capable of acquiring many images (several per minute) over the mission lifetime providing data to validate onboard processing. |  |
| M-Cubed 2 (MCUBED-2) | University of Michigan | University | US | 1U | 2013-12-06 | Operational (Last DK3WN report 2018-06-26) | Flight evaluation of a NASA JPL image processing FPGA called COVE. Our spacecraft provides pictures of Earth for processing, power, and data handling. M-Cubed2 is a re-flight of the COVE experiment with updated avionics after the original M-Cubed accidentally docked with another cubesat shortly after launch, losing the ability to transmit in the process. |  |
| SMDC-ONE 3.1 (Charlie) | US Army Space and Missile Defense Command | Military | US | 3U | 2013-12-06 | Operational? (No public news found) | Demonstrate the ability to rapidly design and develop militarily relevant low cost spacecraft. Receive packetized data from multiple Unattended Ground Sensors (UGS). Transmit that data to ground stations within the SMDC-ONE ground track. Provide real time voice and text message data relay to and from field deployed tactical radio systems. Demonstrate SMDC-ONE operational life time of 12 months or longer. |  |
| SMDC-ONE 3.2 (David) | US Army Space and Missile Defense Command | Military | US | 3U | 2013-12-06 | Operational? (No public news found) | Demonstrate the ability to rapidly design and develop militarily relevant low cost spacecraft. Receive packetized data from multiple Unattended Ground Sensors (UGS). Transmit that data to ground stations within the SMDC-ONE ground track. Provide real time voice and text message data relay to and from field deployed tactical radio systems. Demonstrate SMDC-ONE operational life time of 12 months or longer. |  |
| SNAP (SNAP-3) | US Army Space and Missile Defense Command | Military | US | 3U | 2013-12-06 | Operational? (No public news found) | Related to the SMDC NAnosatellite Program (SNaP) - Joint Capabilities Technology Demonstrations. |  |
| TacSat-6 | Space & Missile Defense Command | Military | US | 3U | 2013-12-06 | Operational? (No public news found) | The mission will demonstrate nanosatellite communication capabilities. | |
| ArduSat 2 | Spire (Nanosatisfi) | Company | US | 2U | 2014-01-09 | Reentry 2014-07-01. No signal? | Mission is to provide a platform on which students and DIY space enthusiasts may design and run their own space-based Arduino experiments. Improved version of ArduSat 1. The satellite’s primary payload is bank of Arduino processors on which student / DIY code may run. The Arduino processors may sample data from the satellite’s imaging payload, a 1.3 megapixel optical CMOS camera module, and / or any of the satellite’s onboard sensors, which includes photolux sensor, IR temperature, PCB temperature, 3-axis magnetometer, Geiger counter, 6-DOF IMU, and MEMS gyros. |  |
| Flock-1 Dove-1 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-09. Was operational. | Constellation for optical Earth observation with 3-5m resolution |  |
| Flock-1 Dove-2 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-05-24. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-3 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-05-15. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-4 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-18. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-5 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-02. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-6 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-15. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-7 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-05. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-8 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-05-25. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-9 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-07-06. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-10 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-14. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-11 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-13. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-12 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-10-26. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-13 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-07-02. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-14 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-20. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-15 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-05-20. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-16 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-20. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-17 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-05-19. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-18 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-10-29. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-19 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-02. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-20 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2015-10-09. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-21 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-05-25. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-22 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-04. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-23 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-07-10. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-24 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-16. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-25 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-24. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-26 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-10. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-27 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-05-03. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1 Dove-28 | Planet Labs | Company | US | 3U | 2014-01-09 | Reentry 2014-06-03. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| LitSat-1 | Kaunas University of Technology | Institute | Lithuania | 1U | 2014-01-09 | Reentry 2014-05-23. Was operational. | Scientific platform for the future scientific experiments with piezo motors in space. |  |
| LituanicaSAT-1 | Kaunas University of Technology | University | Lithuania | 1U | 2014-01-09 | Reentry 2014-07-28. Was operational. | Launch into Earth orbit satellite, the first Lithuanian. Perform the first Lithuanian space exploration. Lithuanian designed to test space technology. Space to test alternative energy sources. Create new business opportunities. Organizing Lithuanians scientists from around the world. Capture the first Lithuanian pictures from space. Locally manufactured primary and secondary flight computers which control the payload consisting of an onboard VGA photo camera and FM Mode V/U Voice Repeater, designed and built by Lithuanian radio-amateurs. Satellite’s external solar panels were specially built and donated by Lithuanian based R&D company „Precizika-MET SC“. One of the mission secondary goals is also to test under space environment different micro-controller designs and MEMS sensors that are integrated into on-board computers. |  |
| SkyCube | Southern Stars Group, LLC | Company | US | 1U | 2014-01-09 | Reentry 2014-11-08. No signal. Only one response month after deployment. Electronics worked for at least a month but solar panels and antennas did not deploy. | Crowdfunded on Kickstarter. Has camera and tweets names from space. |  |
| UAPSAT-1 | Alas Peruanas University | University | Peru | 1U | 2014-01-09 | Reentry 2014-05-22. Was operational? | Studies meteorological phenomena from space. The picosatellite was designed and programmed at the university, serving educational and research efforts in Peru. The investigation verifies the students' design methods and tests various electronics, orientation and stabilization instruments, and temperature sensing instruments designed to measure meteorological impacts on Earth. |  |
| Chasqui-I | Peru National University of Engineering | University | Peru | 1U | 2014-02-05 | Reentry 2015-01-15. No signal. | Improving UNI's capacities in satellite technology through the design, analysis, assembly, integration, test, launch and operation of a CubeSat technology nanosatellite. The Chasqui I satellite will take pictures of the Earth and transmit them to the ground station. Two cameras, one in the visible range and one in the infra-red range. Also, it includes its own attitude control and determination system, communication in the amateur radio band mechanisms, as well as power and thermal control mechanisms based on solar cells of high eficiency and an embedded control and information management system for all the components of the satellite. |  |
| ARTSAT1: Invader (INteractiVe satellite for Art and Design Experimental Research) | Tama Art University | University | Japan | 1U | 2014-02-27 | Reentry 2014-09-02. Was operational. | Art use of satellite data (telemetry). Platform for implementation of satellite data utilization. Production of interactive works and media satellite. Expansion of outreach through work of art. |  |
| ITF-1 (YUI, Imagine The Future-1, IFT) | University of Tsukuba | University | Japan | 1U | 2014-02-27 | Reentry 2014-06-29. No signal. | Construction of networks using small satellite. Demonstration in outer space of new microcomputer. Demonstration of ultra-compact antenna. |  |
| KSAT2 (Hayato, KSAT-2) | Kagoshima University | University | Japan | 1U | 2014-02-27 | Reentry 2014-05-18. Was operational. | Study on Forcast of Localied Downpour and Tornado. In-orbit experiments of an original observation method of atmospheric water vapor. Take Earth Live Images from Space. Ku-band high-speed data transmission, one shot / a few seconds.Messages of Encourgement from Space to Japan. Hand-lettered messages and heart warm pictures, especially from children responsible for the future. Basic Experiments for LEO Positioning Satellites. Frequency and phase synchronization between a ground-base system and a satellite. Orbit Determination Experiments with Radio Interferometer. Satellite Traking Experiment at Very Low Earth Orbit. Evaluation of Earth's atmosphere to the satellite. Verification of Pantograph-type Extending Boom in Space. The boom was originally designed and is fit for compact satellites. |  |
| OPUSAT (CosMoz) | Osaka Prefecture University | University | Japan | 1U | 2014-02-27 | Reentry 2014-07-24. Was operational. | Demonstration of anti-space environment performance of lithium ion capacitor. Realization of high-efficiency power storage technology using MPPT control. Sun-oriented control using magnetic Toluca, Solar Arra |  |
| STARS-II (Gennai, Mother) | Kagawa University | University | Japan | 9kg | 2014-02-27 | Reentry 2014-04-26. Was operational? | Electro Dynamic Tether (EDT) deployment by gravity gradient. EDT is deployed by initial velocity applied by the deployment springs, after stabilization of MS and DS attitude under the docking condition. And then, whole systemcan be stabilized by gravity gradient. Electrical current gathered by EDT. Electrons in space plasma are gathered by EDT which is a bare tether, and they are emitted from DS. As a result, electrical current is passed through EDT. Attitude control by arm link motion based on tether tension due to gravity gradient. DS controls its attitude by arm link motion using tether tension (on EDT), which is applied by gravity gradient. Tether deployment and retrieval by tether tension control. EDT is connected to Kevlar tether at its end. By tension control of Kevlar tether by the reel, relative positions of MS and DS can be controlled. |  |
| ALL-STAR/THEIA (Agile Low-cost Laboratory for Space Technology Acceleration and Research) | University of Colorado at Boulder | University | US | 3U | 2014-04-18 | Reentry 2014-05-26. Was semi-operational. No 2-way comms. | Create a reproducible modular bus. Capable enough to be used for a variety of small research and technology based based payloads. Built within six months of request after initial delivery in Spring 2012. Earth-imaging optical telescope payload built to test the capabilities of the ALLSTAR-1 Bus. |  |
| KickSat | Cornell University | University | US | 3U | 2014-04-18 | Reentry 2014-05-15. Was semi-operational. Sent signals, but could not receive commands and failed to deploy Sprites due to timer reset. | Carry and deploy 200 Sprites. A 1U avionics bus will provide power, communications, and command and data handling functions. A 2U deployer has been developed to house the Sprites. 104 Sprites will be stacked atop a spring-loaded pusher and secured by a nichrome burn wire system. |  |
| PhoneSat-2.5 | NASA Ames | Agency | US | 1U | 2014-04-18 | Reentry 2014-05-15. Was operational. | Active attitude determination and control system utilizing reaction wheels to provide three-axis control and precise pointing capability. This will serve as a demonstration to determine whether small satellites could be used to carry scientific instruments that require precise pointing to fulfill their function. Equipped with a higher-gain S-Band antenna, which serves as a pathfinder for future NASA missions, including the EDSN mission. PhoneSat 2.5’s smartphone camera will attempt to transmit photographs to the ground station at Santa Clara University in California to gather information for future low-cost star trackers. |  |
| SporeSat | NASA Ames, Purdue University, Santa Clara University | University | US | 3U | 2014-04-18 | Reentry 2014-06-04. Was operational. | The primary goal of the SporeSat Project is to utilize an autonomous, free-flying spacecraft to conduct scientific experiments to gain a deeper knowledge of the mechanism of plant cell gravity sensing. The project’s approach allows for realtime measurement of calcium signaling and maintenance of variable gravity treatments during the flight experiment. Technical objectives focus on refining current lab-on-a-chip sensor system in the development of a new CEL-C Advanced bioCD designed for the micro-satellite platform. Space biology science experiment project to investigate biophysical mechanisms of plant gravity sensing using “labon- a-chip” experiment approach. Utilize flight proven spacecraft technologies demonstrated on prior missions such as PharmaSat and O/OREOS. Serve as a technology platform to evaluate new microsensor technologies for enabling future fundamental biology missions. |  |
| TSAT (TSat3, Testsat-Lite, Taylor Satellite) | Taylor University | University | US | 2U | 2014-04-18 | Reentry 2014-05-28. Was operational. | Validating and characterizing the commercial Globalstar link capacity and coverage. Making new low-altitude ELEO measurements. Making plasma density measurements using a Langmuir Probe and educating future workforce in STEM fields. |  |
| SPROUT | Nihon University | University | Japan | 6.7 kg | 2014-05-24 | Was operational until 2016-09-XX? | Verification of design methods and the space demonstration of deploying of the inflatable membrane structurre. Demonstration of the attitude determination and control technology of nano-satellite. Prediction of orbit descent rate change by the inflatable membrane structure. Operation of satellite by a ham radio operator. |  |
| AeroCube-6A | The Aerospace Corporation | Non-profit | US | 0.5U | 2014-06-19 | Operational? (No recent public news found) | Number of system upgrades, including a continuously operated, spin-stabilized attitude control system as well as the space-saving consolidation of the spacecraft’s master flight computer, GPS system, and radio onto a single circuit board. A secondary payload of novel solar cells will also be characterized. The CubeSats are equipped with a suite of miniaturized radiation dosimeters that will take identical measurements of the radiation environment as the spacecraft travel in low Earth orbit. Since the two satellites will measure the same radiation fields within only a few minutes – or seconds – of each other, Aerospace scientists will be able to gather significant information about time-related radiation variations in LEO. |  |
| AeroCube-6B | The Aerospace Corporation | Non-profit | US | 0.5U | 2014-06-19 | Operational? (No recent public news found) | Number of system upgrades, including a continuously operated, spin-stabilized attitude control system as well as the space-saving consolidation of the spacecraft’s master flight computer, GPS system, and radio onto a single circuit board. A secondary payload of novel solar cells will also be characterized. The CubeSats are equipped with a suite of miniaturized radiation dosimeters that will take identical measurements of the radiation environment as the spacecraft travel in low Earth orbit. Since the two satellites will measure the same radiation fields within only a few minutes – or seconds – of each other, Aerospace scientists will be able to gather significant information about time-related radiation variations in LEO. |  |
| Antelsat | University of the Republic | University | Uruguay | 2U | 2014-06-19 | Was operational until 2016-XX-XX? (Last DK3WN report 2016-03-10) | Open source satellite to encourage students, engineers and technicians, to learn and develop space technology. UHF telemetry, VHF telecommand, S-Band download data from color & infrared cameras. |  |
| BRITE-CA 1 (BRITE-Toronto, CanX-3E) | Canadian Space Agency (CSA) | Agency | Canada | 10 kg | 2014-06-19 | Operational (http://www.tugsat.tugraz.at/) | Investigation of the brightness oscillations of massive luminous stars by differential photometry. The scientific instrument is an optical camera with a high-resolution CCD to take images from distant stars with magnitude of 3.5. | |
| BRITE-CA 2 (BRITE-Montreak, CanX-3F) | Canadian Space Agency (CSA) | Agency | Canada | 10 kg | 2014-06-19 | Deployment failure | Investigation of the brightness oscillations of massive luminous stars by differential photometry. The scientific instrument is an optical camera with a high-resolution CCD to take images from distant stars with magnitude of 3.5. | |
| DTUSat-2 | Technical University of Denmark | University | Denmark | 1U | 2014-06-19 | Was semi-operational. No two way communications established due to power and GS problems? | Satellite-based radio-tracking system capable of locating small birds with intercontinental migrations anywhere along the route. The system will use a receiver mounted on the satellite DTUsat for tracking small radio-transmitters mounted on birds, henceforth referred to as bird transmitters. The tracking system will be used for tracking cuckoos on their migration from Europe to Africa and to track the movements of birds that have been displaced from Denmark. Tracking displaced birds holds great promise to help solving some of the true mysteries of bird migration: how do inexperienced, young migratory birds manage to find their way to unknown wintering quarters on their own, thousands of kilometres from were they were born. |  |
| Duchifat-1 | Herzliya Science Centre | School | Israel | 1U | 2014-06-19 | Operational (Last DK3WN report 2018-07-03) | Transmit real-time information via radioamateur packets from a Low Earth Orbit (LEO) using the Automatic Position Reporting System (APRS) protocol. Will allow remote traveler's to access the satellite for worldwide position/status reporting and messaging even in the case of using simple handheld or mobile radios with Omni-directional whip antennas. Distant travelers, boats at sea, and stations in many parts of the world are presently unable to use the APRS system when on distant trips. |  |
| Flock-1c Dove-1 | Planet Labs | Company | US | 3U | 2014-06-19 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1c Dove-2 | Planet Labs | Company | US | 3U | 2014-06-19 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1c Dove-3 | Planet Labs | Company | US | 3U | 2014-06-19 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1c Dove-4 | Planet Labs | Company | US | 3U | 2014-06-19 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1c Dove-5 | Planet Labs | Company | US | 3U | 2014-06-19 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1c Dove-6 | Planet Labs | Company | US | 3U | 2014-06-19 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1c Dove-7 | Planet Labs | Company | US | 3U | 2014-06-19 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1c Dove-8 | Planet Labs | Company | US | 3U | 2014-06-19 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1c Dove-9 | Planet Labs | Company | US | 3U | 2014-06-19 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1c Dove-10 | Planet Labs | Company | US | 3U | 2014-06-19 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1c Dove-11 | Planet Labs | Company | US | 3U | 2014-06-19 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Lemur-1 | Spire (Nanosatisfi) | Company | US | 3U | 2014-06-19 | Operational | Technology demonstration of several science payloads hosted by a 3U CubeSat. In addition to technology demonstration, LEMUR-1 carries two Earth-observation payloads. Its primary Earth-observation payload is an electro-optical imaging system, operating in the visible band with a ground resolution of approximately 5m. Its secondary payload is a low-resolution IR imaging system, with an approximate ground resolution of 1km. |  |
| NANOSATC-BR1 (NCBR-1) | National Institute of Space Research | Institute | Brazil | 1U | 2014-06-19 | Was operational until 2017-12-XX? (Last SatNOGS report 2017-12-21) | Monitor real time the space weather and atmosphere anomalies over the Brazilian territory, such as the Geomagnetic field disturbs and its effects on the region knows as the South Atlantic Magnetic Anomaly (SAMA) |  |
| PACE (Platform for Attitude Control Experiments) | National Cheng Kung University | University | Taiwan | 2U | 2014-06-19 | No signal | Conduct attitude control experiments. Several types of attitude sensors and actuators are integrated in the satellite in order to allow the in-orbit evaluation of different attitude determination and control strategies. |  |
| Perseus-M 1 | Dauria / Canopus / Aquila Space | Company | Russia | 6U | 2014-06-19 | Operational? (No recent public news found) | - Automatic Identification System (AIS) receiver |  |
| Perseus-M 2 | Dauria / Canopus / Aquila Space | Company | Russia | 6U | 2014-06-19 | Operational? (No recent public news found) | - Automatic Identification System (AIS) receiver | |
| PolyITAN-1 | National Technical University of Ukraine | University | Ukraine | 1U | 2014-06-19 | Operational (Last DK3WN report 2018-05-01) | Training of specialists for space engineering, Development of a small-size platform for space exploration. Refining new design and technology solutions. Establishment of a training laboratory at the university for the control and data acquisition and processing system of small satellites. Establishment of the facilities on ground for the environmental testing of satellites, including thermal vacuum tests. Frame is made of CFRP (Carbon Fiber Reinforced Plastic) honeycomb panels with very low specific weight. |  |
| POPSAT-HIP 1 | Microspace Rapid Pte Ltd. | Company | Singapore | 3U | 2014-06-19 | Was operational for 1 year? | Demonstrate the functionality of a high resolution optical payload and attitude control propulsion system on a Cubesat Class Nano-satellite. GSD 5 m from LEO and 5 km swath. |  |
| QB50P1 | Von Karman Institute | Institute | Belgium | 2U | 2014-06-19 | Was operational until 2016-12-XX? | Test key subsystems of QB50. INMS Payload from MSSL, UK. QB50 ADCS system from SSC, UK. Thermocouple experiment from VKI, Belgium. AMSAT-NL 435/145 MHz linear transponder (FUNcube-3) from AMSAT-NL, The Netherlands. |  |
| QB50P2 | Von Karman Institute | Institute | Belgium | 2U | 2014-06-19 | Was operational until 2016-01-XX? | Test key subsystems of QB50. FIPEX (Flux-(Phi)-Probe-Experiment) Payload, University of Dresden, Germany. QB50 ADCS system from SSC, UK. Thermocouple experiment from VKI, Belgium. AMSAT-Fr 435/145 MHz FM voice transponder from AMSAT Francophone, France. | |
| Tigrisat | School of Aerospace Engineering of Rome | University | Italy | 3U | 2014-06-19 | Operational (Last DK3WN report 2018-06-09) | Detect dust storms over Iraq. The 3U cubesat features a RGB camera with a new scripted algorithm for dust detection. It has a deployable VHF/UHF antenna for telemetry telecommand and beacon and a S-Band antenna. Embedded magnetic coils inside solar panels provide attitude control to enable nadir pointing. Tigrisat transmits images to two ground stations, one located in Rome and another in Baghdad. |  |
| CanX-4 | Space Flight Laboratory (SFL) | Institute | Canada | 7 kg | 2014-06-30 | Operational (eoPortal status from 2018-05-22) | Primary mission is the demonstration of on-orbit formation flying. In this context, formation flying is defined as two or more satellites controlling their position and orientation with respect to one another to achieve a predefined configuration necessary for coordinated operations. |  |
| CanX-5 | Space Flight Laboratory (SFL) | Institute | Canada | 7 kg | 2014-06-30 | Operational (eoPortal status from 2018-05-22) | Primary mission is the demonstration of on-orbit formation flying. In this context, formation flying is defined as two or more satellites controlling their position and orientation with respect to one another to achieve a predefined configuration necessary for coordinated operations. |  |
| VELOX 1 (VELOX PIII, N-Sat) | Nanyang Technological University | University | Singapore | 0.193 kg | 2014-06-30 | Was operational until? | Picosatellite for intersatellite communication experiment. |  |
| VELOX-I N-Sat (VELOX 1) | Nanyang Technological University | University | Singapore | 3U | 2014-06-30 | Operational? (No recent public news found) | To launch the first Singapore’s nanosatellite VELOX-I, which is designed, built, and operated by students from different schools in the College of Engineering, NTU. To acquire images of Earth and transmit them back to ground station. A narrow angle camera with tele-optics is used to provide high-resolution images of Earth from LEO. To carry out experiments relevant to technology demonstration.Payloads include: a vision system, a dual-FOV sun sensor. To piggyback launch a picosatellite (VELOX-PIII) for intersatellite communication experiment. Optics extension system all use spring-loaded mechanisms for deployment after launch. Imaging system with extended optics for 20 m ground resolution, a quantum physics payload and an intersatellite communications payload. |  |
| AISSat-2 | Norwegian Space Centre | Agency | Norway | 6 kg | 2014-07-08 | Operational (Mentioned in public news) | Identical to AISSat-1 and incorporates all the improvements made to AISSat-1 following its launch. Given the great success of AISSat-1, the development of AISSat-2 implies that SFL’s nanosatellite solution has become ideal for operational monitoring and tracking of ships in Norwegian territorial waters. |  |
| UKube-1 (United Kingdom Universal Bus Experiment 1) | UK Space Agency | Agency | UK | 3U | 2014-07-08 | Semi-operational. Official mission ended on 2015-09-08, but FunCube is active. (Last DK3WN report 2018-07-27) | Demonstrate new UK space technology. Demonstrate the capability of useful science to be performed within a CubeSat sized spacecraft. Demonstrate industry and university based training in spacecraft development. Demonstrate education and outreach in STEM subjects. Demonstrate Payload Kick-Off to flight qualified spacecraft in less than 12 months. TOPCAT, from the University of Bath, is the first GPS device aimed at measuring plasmaspheric space weather. The CMOS Image Demonstrator by the Open University is a camera that will take images of the earth and test the effect of radiation on space hardware using a new generation of image sensor. Astrium’s “Janus” Experiment to demonstrate the feasibility of using cosmic radiation to improve the security of communications satellites and to flight test lower cost electronic systems. AMSAT’s FUNcube-2, an outreach payload allowing school children of primary and secondary age to interact with the spacecraft. |  |
| Flock-1b Dove-1 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-01-01. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-2 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-03-14. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-3 | Planet Labs | Company | US | 3U | 2014-07-13 | Returned to Earth. Aboard Dragon SpX-5 | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-4 | Planet Labs | Company | US | 3U | 2014-07-13 | Returned to Earth. Aboard Dragon SpX-5 | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-5 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2014-08-17. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-6 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-10-16. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-7 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-01-20. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-8 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-03-05. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-9 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-06-28. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-10 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-08-23. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-11 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-09-07. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-12 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-09-29. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-13 | Planet Labs | Company | US | 3U | 2014-07-13 | Returned to Earth. Aboard Dragon SpX-5 | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-14 | Planet Labs | Company | US | 3U | 2014-07-13 | Returned to Earth. Aboard Dragon SpX-5 | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-15 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-01-07. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-16 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2014-12-13. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-17 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-03-04. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-18 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-01-16. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-19 | Planet Labs | Company | US | 3U | 2014-07-13 | Returned to Earth. Aboard Dragon SpX-5 | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-20 | Planet Labs | Company | US | 3U | 2014-07-13 | Returned to Earth. Aboard Dragon SpX-5 | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-21 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-10-12. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-22 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-10-03. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-23 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-03-03. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-24 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-03-15. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-25 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-02-01. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-26 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2014-12-14. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-27 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-10-14. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1b Dove-28 | Planet Labs | Company | US | 3U | 2014-07-13 | Reentry 2015-08-07. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| GEARRS-1 (GEARRSAT, Globalstar Experiment And Risk Reduction Satellite) | Near Space Launch | Company | US | 3U | 2014-07-13 | Reentry 2015-11-07. Was operational. | Show that the Globalstar satellite network is a feasible option for the command and control of a small satellite system. |  |
| Lambdasat | San Jose State University | University | US | 3U | 2014-07-13 | Reentry 2015-05-16. Was operational. | Technology for two-way communication with the ground systems for operations. It carries a new science experiment which measures the radiation effects on the graphene material in real environment in Low Earth Orbit (LEO). Another technology that carries is an AIS receiver for tracking all the vessels inside its footprint around the globe. The communication consist of an Iridium Short Burst Data (SBD) modem and makes use of the Iridium constellation. |  |
| MicroMAS-1 | Massachusetts Institute of Technology | University | US | 3U | 2014-07-13 | Reentry 2015-08-01. Was operational until 2015-03-18, few days? Transmitter failed. | Passive microwave spectrometer operating near the 118.75-GHz oxygen absorption line to observe convective thunderstorms,tropical cyclones, and hurricanes from a near-equatorial orbit at approximately 500-km altitude. |  |
| TechEdSat-4 | NASA Ames Research Center | Agency | US | 3U | 2014-07-13 | Reentry 2015-04-03. Was operational. | Investigate technology to return small samples to Earth from the space station. TechEdSat-4 will deploy using the NanoRacks services. Its primary objectives are to further develop a tension-based drag device, called exo-brake, and demonstrate frequent uplink/downlink control capabilities. |  |
| BRITE-PL-2 Heweliusz (CanX 3D) | The Space Research Centre of the Polish Academy of Sciences | Institute | Poland | 6 kg | 2014-08-19 | Operational (http://www.tugsat.tugraz.at/) | Investigation of the brightness oscillations of massive luminous stars by differential photometry. The scientific instrument is an optical camera with a high-resolution CCD to take images from distant stars with magnitude of 3.5. | |
| Arkyd 3 | Planetary Resources | Company | US | 3U | 2014-10-28 | Launch failure | Technology demonstration nanosatellite based on the triple CubeSat form factor for the planned Arkyd-100 astronomy satellites but no optical payload. |  |
| Flock-1d Dove-1 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-2 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-3 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-4 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-5 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-6 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-7 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-8 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-9 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-10 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-11 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-12 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-13 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-14 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-15 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-16 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-17 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-18 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-19 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-20 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-21 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-22 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-23 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-24 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-25 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d Dove-26 | Planet Labs | Company | US | 3U | 2014-10-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| GOMX-2 | GomSpace | Company | Denmark | 2U | 2014-10-28 | Launch failure | A 2U CubeSat intended to test a de-orbit system designed by Aalborg University. Also flying a optical communications experiment from the National University of Singapore. The mission will also flight qualify a new highspeed UHF transceiver and SDR receiver from a new generation Aalborg University team. |  |
| RACE (CHARM, Radiometer Atmospheric CubeSat Experiment, CubeSat Hydrometric Atmospheric Radiometer Mission) | The University of Texas at Austin | University | US | 3U | 2014-10-28 | Launch failure | Spaceborne validation of a 183 GHz radiometer, utilizing an indium phosphide low noise amplifier front-end, to measure water vapor emission from the Earth’s atmosphere. To advance the technology of the 35 nm indium phosphide (InP) receiver subsystem of the radiometer instrument. To advance the technology of a 183 GHz water vapor radiometer CubeSat system. To reduce the risk for future users of the technology. To enhance the hands-on training for the RACE project team members within the Phaeton Program platform. To explore possibilities for smaller missions with distributed risks. |  |
| AESP-14 | Technological Institute of Aeronautics | University | Brazil | 1U | 2015-01-10 | Reentry 2015-05-11. No signal. | Main task is to develop a CubeSat that meets a specific scientific mission to be defined based on INPE’s research scientists’ needs. The technological mission consists on the multi-mission national CubeSat platform validation. The scientific mission is to obtain scientific parameters from the ionized atmosphere in a low orbit, with emphasis on the plasma bubbles study. A Langmuir Probe (LP) for measurement of electron density and temperature of the plasma ionospheric |  |
| Flock-1d' 1 | Planet Labs | Company | US | 3U | 2015-01-10 | Reentry 2015-10-13. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1d' 2 | Planet Labs | Company | US | 3U | 2015-01-10 | Reentry 2015-12-27. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| CP10 (ExoCube) | California Polytechnic State University | University | US | 3U | 2015-01-31 | Was semi-operational until 2016-07-30. | Measuring the Elemental Composition of the Exosphere Technology demonstration mission of a mass spectrometer sensor suite, EXOS, into low-Earth orbit to measure neutral and ionized species in the exosphere and thermosphere. Mass Spectrometer Incoherent Scatter models are essential in Earth system science and upper atmosphere composition. |  |
| FIREBIRD-2 C (FU3, FIREBIRD-3, Focused Investigations of Relativistic Electron Burst, Intensity, Range, and Dynamics) | Montana State University/ University of New Hampshire | University | US | 1.5U | 2015-01-31 | Operational (Last DK3WN 2018-05-13) | Space weather Cubesat mission to resolve the spatial scale size and energy dependence of electron microbursts in the Van Allen radiation belts. |  |
| FIREBIRD-2 D (FU4, FIREBIRD-4, Focused Investigations of Relativistic Electron Burst, Intensity, Range, and Dynamics) | Montana State University/ University of New Hampshire | University | US | 1.5U | 2015-01-31 | Operational (Last DK3WN report 2018-05-28) | Space weather Cubesat mission to resolve the spatial scale size and energy dependence of electron microbursts in the Van Allen radiation belts. |  |
| GRIFEX (GEO-CAPE ROIC In-Flight Performance Experiment) | University of Michigan | University | US | 3U | 2015-01-31 | Operational (Last DK3WN report 2018-07-23) | Validate detector technology for the Panchromatic Fourier Transform Spectrometer (PanFTS) which is an imaging FTS designed to operate in Geostationary orbit. GRIFEX will provide an on-orbit verification of a high performance focal plane array (FPA) consisting of an innovative in-pixel analog-to-digital (ADC) readout integrated circuit (ROIC) hybridized to a silicon detector array. The PanFTS engineering model instrument is currently being developed which will incorporate the focal plane assembly (FPA) and signal chain technology validated by the GRIFEX CubeSat flight experiment. GRIFEX will validate the JPL developed digital FPA and signal chain for the same signal levels expected for PanFTS in geostationary orbit. |  |
| Arkyd 3 reflight | Planetary Resources | Company | US | 3U | 2015-04-14 | Reentry 2015-12-23. Was operational. | Technology demonstration nanosatellite based on the triple CubeSat form factor for the planned Arkyd-100 astronomy satellites but no optical payload. |  |
| Centennial-1 | Booz Allen Hamilton | Company | US | 1U | 2015-04-14 | Reentry 2016-01-06. Was operational? | Developed during Booz Allen’s one hundredth year as a corporation, the “Centennial-1” cubesat is an internal company technology demonstration experiment to test a small optical sensor package including small photodetectors and a small camera as payload on a 1U cubesat. Staff engineers and college interns are designing and building Centennial-1 |  |
| Flock-1e 1 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-05-18. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 2 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-03-05. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 3 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-05-29. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 4 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-06-24. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 5 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-06-20. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 6 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-07-21. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 7 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-07-17. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 8 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-06-22. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 9 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-02-08. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 10 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-08-09. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 11 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-08-09. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 12 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-08-09. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 13 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-08-24. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1e 14 | Planet Labs | Company | US | 3U | 2015-04-14 | Reentry 2016-07-31. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| AeroCube-8A (IMPACT) | The Aerospace Corporation | Non-profit | US | 1.5U | 2015-05-20 | Operational? (No recent public news found) | Demonstrate Scalable ion-Electrospray Propulsion system (SiEPro). Measure IV curves for 4-junction IMM solar cells and 5-junction SBT cell. Demonstrate CNT harness and use of CNT/PEEK material. Evaluate CNT radiation-shielding material. | .png){kind=small} |
| AeroCube-8B (IMPACT) | The Aerospace Corporation | Non-profit | US | 1.5U | 2015-05-20 | Operational? (No recent public news found) | Demonstrate Scalable ion-Electrospray Propulsion system (SiEPro). Measure IV curves for 4-junction IMM solar cells and 5-junction SBT cell. Demonstrate CNT harness and use of CNT/PEEK material. Evaluate CNT radiation-shielding material. | .png){kind=small} |
| BRICSat-P (Ballistic Reinforced Communication Satellite, previously PSat B, ParkinsonSat B) | US Naval Academy | University | US | 1.5U | 2015-05-20 | Was operational until 2015-07-XX. Power problems and weak signals. | Primary objectives are to integrate a miniature size propulsion system into a 1.5U CubeSat and perform three maneuvers in space: de-tumbling, pointing control, and delta-V. Secondary objective is to expand APRS network. APRS constellation transponder with downlink on 437.975MHz and with uplink on 145.825MHz 1k2 and 9k6 AX25 - PSK31 Xponder with 28.120 MHz uplink and UHF FM downlink on 435.350 MHz |  |
| GEARRS 2 (GEARRSAT 2, Globalstar Experiment And Risk Reduction Satellite) | Near Space Launch | Company | US | 3U | 2015-05-20 | Was operational until 2016-02-XX? | Show that the Globalstar satellite network is a feasible option for the command and control of a small satellite system. |  |
| LightSail-A | The Planetary Society | Non-profit | US | 3U | 2015-05-20 | Reentry 2015-06-15. Was operational until 2015-06-11. Various problems, but deployed solar sail. | Demonstrate the deployment of a 32 m2 solar sail from a 3-unit CubeSat platform. Following deployment from the launch vehicle, LightSail-A will power on engineering subsystems, and a system checkout will be performed. It is anticipated that solar sail deployment will occur approximately two weeks after launch. Following sail deployment, engineering telemetry and imaging of the sail deployment event will be downlinked. |  |
| OptiCube 1 (O/C, Optical CubeSat) | California Polytechnic State University | University | US | 3U | 2015-05-20 | Passive, mass dummy basically. No signal. | Provide on-orbit targets for ground assets to calibrate sensors for orbital debris studies and small-object tracking improvements These satellites were produced as a back-up on short notice on request of the NASA Orbital Debris Program Office and the Air Force's Starfire Optical Range, when it became clear, that not enough CubeSats would be ready to fill all the launch slots on the ULTRASAT mission. |  |
| OptiCube 2 (O/C, Optical CubeSat) | California Polytechnic State University | University | US | 3U | 2015-05-20 | Passive, mass dummy basically. No signal. | Provide on-orbit targets for ground assets to calibrate sensors for orbital debris studies and small-object tracking improvements These satellites were produced as a back-up on short notice on request of the NASA Orbital Debris Program Office and the Air Force's Starfire Optical Range, when it became clear, that not enough CubeSats would be ready to fill all the launch slots on the ULTRASAT mission. | |
| OptiCube 3 (O/C, Optical CubeSat) | California Polytechnic State University | University | US | 3U | 2015-05-20 | Passive, mass dummy basically. No signal. | Provide on-orbit targets for ground assets to calibrate sensors for orbital debris studies and small-object tracking improvements These satellites were produced as a back-up on short notice on request of the NASA Orbital Debris Program Office and the Air Force's Starfire Optical Range, when it became clear, that not enough CubeSats would be ready to fill all the launch slots on the ULTRASAT mission. | |
| PSat A (PSat, ParkinsonSat A, UltraSat1?, NO-84) | US Naval Academy Satellite Lab | University | US | 1.5U | 2015-05-20 | Operational (Last DK3WN report 2018-06-04) | Two way communications transponder for relaying remote telemetry, sensor and user data from remote environmental experiments or other data sources back to experimenters via a global network of internet linked volunteer ground stations. The data transponder also includes all telemetry, command and control for a complete CubeSat. |  |
| USS Langley (Unix Space Server) | US Naval Academy | University | US | 3U | 2015-05-20 | No signal | Fly the Unix-Space-Server (USS) to experiment with using a server in space of Amateur Experimentation and the second mission is to continue the PSK-31 multi-user transponder experiments. |  |
| Flock-1f 1 | Planet Labs | Company | US | 3U | 2015-06-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1f 2 | Planet Labs | Company | US | 3U | 2015-06-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1f 3 | Planet Labs | Company | US | 3U | 2015-06-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1f 4 | Planet Labs | Company | US | 3U | 2015-06-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1f 5 | Planet Labs | Company | US | 3U | 2015-06-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1f 6 | Planet Labs | Company | US | 3U | 2015-06-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1f 7 | Planet Labs | Company | US | 3U | 2015-06-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-1f 8 | Planet Labs | Company | US | 3U | 2015-06-28 | Launch failure | Constellation for optical Earth observation with 3-5m resolution | |
| Deorbitsail | EU FP7 consortium | Agency | UK | 3U | 2015-07-10 | Was semi-operational until 2016-10-30, high spin rates. (Last SatNOGS report 2018-10-30) | Launch and deploy a 5-by-5-metre, four-quadrant sail to demonstrate deorbiting. |  |
| AAUSAT5 | Aalborg University | University | Denmark | 1U | 2015-08-19 | Reentry 2016-03-15. Was operational. | Monitor ship traffic, especially around Greenland, using a new and improved AIS receiver. |  |
| Flock-2b 1 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-09-22. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 2 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-10-02. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 3 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-10-14. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 4 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-10-17. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 5 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-09-25. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 6 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-08-22. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 7 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-09-21. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 8 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-05-22. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 9 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-10-16. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 10 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-10-12. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 11 | Planet Labs | Company | US | 3U | 2015-08-19 | Returned to Earth. Aboard Dragon SpX-8? | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 12 | Planet Labs | Company | US | 3U | 2015-08-19 | Returned to Earth. Aboard Dragon SpX-8? | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 13 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-10-11. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2b 14 | Planet Labs | Company | US | 3U | 2015-08-19 | Reentry 2016-09-12. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| GOMX-3 | GomSpace | Company | Denmark | 3U | 2015-08-19 | Reentry 2016-10-18. Was operational. | Part of the outreach programme for the visit of the Danish astronaut Andreas Mogensen, to the ISS A number of outreach activities are being planned that will involve schools, radio amateur societies and social media both during the astronaut mission and continuing with the CubeSat mission. |  |
| S-CUBE (S3, Shootingstar Sensing Satellite) | Chiba Institute of Technology | University | Japan | 3U | 2015-08-19 | Reentry 2016-11-23. Was operational? | Detect UV emission from a meteor by PMT, which is used as a trigger of a camera (minimum success). Take an image of meteor by a camera to estimate the meteoroid size from brightness (minimum success). Obtain the flux (i. e., size distribution) of meteors (full success). Estimate the compositions of meteors quantitatively from emission from species, such as sulfur (optional). The scientific instruments consist of a CCD camera inherited from SpriteSat and a Photomultiplier tube (PMT) for detection at ultraviolet wavelengths. |  |
| SERPENS | SERPENS (Sistema Espacial para Realização de Pesquisa e Experimentos com Nanossatélites) programme university consortium | University | Brazil | 3U | 2015-08-19 | Reentry 2016-03-27. Was operational. | Transponder to test VHF and S-band communications for store and forward messaging,a UHF transponder fully compatible with the HUMSAT store and forward messaging system and pulsed plasma thruster (PPT) built by Mars Space Ltd. and Clyde Space. |  |
| DCBB (CAS 3G, Chinese Amateur Radio Satellite) | Shenzhen Aerospace Dongfanghong HIT Satellite Ltd | Company | China | 2U | 2015-09-19 | Operational? (No public news found) | Amateur radio missions. The amateur communications payload consists of U/V 20 kHz wide transponders with 145 MHz CW beacon and 19k2 GMSK AX25 telemetry downlinks. | |
| KJSY 1 (Kongjian Shiyan 1) | Tsinghua University | University | China | 0.173 kg | 2015-09-19 | Operational? (No public news found) | Test formation flying on tethers with ZJ-1 ans inter-satellite communications and GaN electronic boards in space. | |
| LilacSat-2 (Zidingxiang-2, CAS 3H) | Harbin Institute of Technology | University | China | 10 kg | 2015-09-19 | Operational (Last DK3WN report 2018-06-12) | Education, amateur radio communication and technology demonstration. Provides hands-on experience for students who would not otherwise have the opportunity to build flight hardware for a space mission. 4 mission payloads: 1. A V/U amateur radio SDR platform. It can be configured as an FM repeater or an APRS digipeater.It will also provide a VHF CW beacon and UHF 9k6 BPSK telemetry downlink 2. An SDR based multi-band receiver, for reception and decoding of signals from AIS, ADS-B, etc. 3. An FPGA software testing platform. 4. A thermal infrared camera. |  |
| NUDT-PhoneSat (CAS 3I, Kaituo 1B) | National University of Defense Technology | University | China | 1U | 2015-09-19 | Operational? (No public news found) | - |  |
| XC 1 (Xingchen 1) | National University of Defense Technology (NUDT) | University | China | 100 g | 2015-09-19 | Operational? (No public news found) | Test out inter-satellite communication techniques. |  |
| XC 2 (Xingchen 2) | National University of Defense Technology (NUDT) | University | China | 100 g | 2015-09-19 | Operational? (No public news found) | Test out inter-satellite communication techniques. |  |
| XC 3 (Xingchen 3) | National University of Defense Technology (NUDT) | University | China | 100 g | 2015-09-19 | Operational? (No public news found) | Test out inter-satellite communication techniques. |  |
| XC 4 (Xingchen 4) | National University of Defense Technology (NUDT) | University | China | 100 g | 2015-09-19 | Operational? (No public news found) | Test out inter-satellite communication techniques. |  |
| XW-2B (CAS 3B, Chinese Amateur Radio Satellite) | CAMSAT (AMSAT China) | Non-profit | China | 10 kg | 2015-09-19 | Operational (Last DK3WN report 2018-06-20) | Atmospheric physics experiments and amateur radio missions. The amateur communications payload consists of U/V 20 kHz wide transponders with 145 MHz CW beacon and 19k2 GMSK AX25 telemetry downlinks. |  |
| XW-2C (CAS 3C, Chinese Amateur Radio Satellite) | CAMSAT (AMSAT China) | Non-profit | China | 10 kg | 2015-09-19 | Operational (Last DK3WN report 2018-05-25) | Atmospheric physics experiments and amateur radio missions. The amateur communications payload consists of U/V 20 kHz wide transponders with 145 MHz CW beacon and 19k2 GMSK AX25 telemetry downlinks. |  |
| XW-2D (CAS 3D, Chinese Amateur Radio Satellite) | CAMSAT (AMSAT China) | Non-profit | China | 10 kg | 2015-09-19 | Operational (Last SatNOGS report 2018-07-22) | Atmospheric physics experiments and amateur radio missions. The amateur communications payload consists of U/V 20 kHz wide transponders with 145 MHz CW beacon and 19k2 GMSK AX25 telemetry downlinks. |  |
| XW-2E (CAS 3E, Chinese Amateur Radio Satellite) | CAMSAT (AMSAT China) | Non-profit | China | 1.5 kg | 2015-09-19 | Operational (Last DK3WN report 2018-07-12) | Amateur radio missions. The amateur communications payload consists of U/V 20 kHz wide transponders with 145 MHz CW beacon and 19k2 GMSK AX25 telemetry downlinks. |  |
| XW-2F (CAS 3F, Chinese Amateur Radio Satellite) | CAMSAT (AMSAT China) | Non-profit | China | 1.5 kg | 2015-09-19 | Operational (Last DK3WN report 2018-06-20) | Amateur radio missions. The amateur communications payload consists of U/V 20 kHz wide transponders with 145 MHz CW beacon and 19k2 GMSK AX25 telemetry downlinks. | |
| ZJ 1 (Zijing 1) | Tsinghua University | University | China | 0.234 kg | 2015-09-19 | Operational? (No public news found) | Evaluate micro CMOS cameras and MEMS magnetometers, as well as formation flying on tethers with KJSY 1 and inter-satellite communications. | |
| TW-1A (STU-2, Shankeda 2, Tianwang-1A, Sat-A, SECM-1) | Shanghai Engineering Centre for Microsatellites (SECM) | Institute | China | 3U | 2015-09-25 | Operational (Last DK3WN report 2018-05-08) | GAMALINK, which is an S-band inter-satellite communication module, a novel dual band GPS/BD receiver, an AIS receiver, and an ADS-B receiver, all being designed based on SDR technologies. Also a novel cold-gas micro propulsion module based on MEMS technology will be used for orbit and constellation control. TW-1 project consists of three CubeSats carrying different payloads and instruments with one 3U CubeSat and two 2U CubeSats, forming an along-trace satellite network and/or constellation. CubeSats networking based on Gamalink. Monitoring sea ice and gaining the maritime traffic information in polar region based on AIS receiver and camera. Demonstration of autonomous formation flying including the along-track orbital (ATO) formation and the projected circular orbital (PCO) formation. In-orbit demonstration and validation of ADS-B receiver/ Gamalink / Micro-propulsion. Imaging the satellite separating process. |  |
| TW-1B (STU-2, NJUST 2, Tianwang-1B, Sat-B, SECM-1) | Shanghai Engineering Centre for Microsatellites | Institute | China | 2U | 2015-09-25 | Was operational until 2015-11-XX? (Last DK3WN report 2015-10-30) | GAMALINK, which is an S-band inter-satellite communication module, a novel dual band GPS/BD receiver, an AIS receiver, and an ADS-B receiver, all being designed based on SDR technologies. Also a novel cold-gas micro propulsion module based on MEMS technology will be used for orbit and constellation control. TW-1 project consists of three CubeSats carrying different payloads and instruments with one 3U CubeSat and two 2U CubeSats, forming an along-trace satellite network and/or constellation. CubeSats networking based on Gamalink. Monitoring sea ice and gaining the maritime traffic information in polar region based on AIS receiver and camera. Demonstration of autonomous formation flying including the along-track orbital (ATO) formation and the projected circular orbital (PCO) formation. In-orbit demonstration and validation of ADS-B receiver/ Gamalink / Micro-propulsion. Imaging the satellite separating process. |  |
| TW-1C (STU-2, NJFA , Tianwang-1C, Sat-C, SECM-1) | Shanghai Engineering Centre for Microsatellites | Institute | China | 2U | 2015-09-25 | Operational (Last SatNOGS report 2018-08-01) | GAMALINK, which is an S-band inter-satellite communication module, a novel dual band GPS/BD receiver, an AIS receiver, and an ADS-B receiver, all being designed based on SDR technologies. Also a novel cold-gas micro propulsion module based on MEMS technology will be used for orbit and constellation control. TW-1 project consists of three CubeSats carrying different payloads and instruments with one 3U CubeSat and two 2U CubeSats, forming an along-trace satellite network and/or constellation. CubeSats networking based on Gamalink. Monitoring sea ice and gaining the maritime traffic information in polar region based on AIS receiver and camera. Demonstration of autonomous formation flying including the along-track orbital (ATO) formation and the projected circular orbital (PCO) formation. In-orbit demonstration and validation of ADS-B receiver/ Gamalink / Micro-propulsion. Imaging the satellite separating process. |  |
| exactView-9 (EV-9, EV9) | exactEarth Inc | Company | Canada | 5.5 kg | 2015-09-28 | Operational? | Next generation Automatic Identification System (AIS) receiver for high ship-detection rates, and a high speed downlink transmitter for high data volume transfers. The satellite is designed to operate in a low inclination orbit to service some of the more remote and not-as-well covered areas of Earth. |  |
| Lemur-2 1 Joel | Spire | Company | US | 3U | 2015-09-28 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. |  |
| Lemur-2 2 Peter | Spire | Company | US | 3U | 2015-09-28 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 3 Jeroen | Spire | Company | US | 3U | 2015-09-28 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 4 Chris | Spire | Company | US | 3U | 2015-09-28 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| AeroCube-5C | The Aerospace Corporation | Non-profit | US | 1.5U | 2015-10-08 | Operational? (No recent public news found) | Demonstrate new technologies for pointing and tracking between two identical CubeSats and to demonstrate a deorbit device. |  |
| Aerocube-7A (OCSD, Optical Communications and Sensor Demonstration, IOCPS-A, Integrated Optical Communications and Proximity Sensors) | The Aerospace Corporation | Non-profit | US | 1.5U | 2015-10-08 | Semi-operational. A software update anomaly disabled the attitude control main processor. Booted into partially updated program. | Demonstrate optical communications from a CubeSat to a 30 cm diameter ground station from LEO at a rate of at least 5 Mbps. Demonstrate tracking of a nearby spacecraft using a commercial COTS automotive anti-collision radar sensor and an inexpensive optical mouse sensor. |  |
| ARC-1 (Alaska Research CubeSat) | University of Alaska | University | US | 1U | 2015-10-08 | No signal | Provide authentic, interdisciplinary, hands-on student experiences in science and engineering through the design, development, and operation of a student small satellite mission. Characterize the thermal and vibration environment inside the launch vehicle from ignition to orbit insertion. Validate a novel low power Attitude Control and Determination System (ACDS). Validate a high bandwidth communication system by obtaining images of changing snow/ice coverage in arctic regions. |  |
| BisonSat (Nwist Q̓ʷiq̓ʷáy, SKC) | Salish Kootenai College | University | US | 1U | 2015-10-08 | Semi-operational, no commanding possible. (Last DK3WN report 2018-05-28). | The primary purpose of the SKC CubeSat mission is educational, but also has a science objective of using broad-band visible light orbital imagery to study atmospheric aerosols, cloud formation, and various hydrologic processes. |  |
| Fox-1A | The Radio Amateur Satellite Corporation (AMSAT) | Non-profit | US | 1U | 2015-10-08 | Operational (Last DK3WN report 2018-05-12) | Fox-1 will be an easy-to-operate, FM transponder satellite, one with very similar operating characteristics to those of AMSAT OSCAR-51. The project will introduce the concept of designed-in, partial-failure operation. The satellite will be specifically designed so that when the battery fails, the transponder can continue to operate when the satellite is in sunlight. |  |
| LMRSTSat (LMRSat , LMRST-Sat, Low Mass Radio Science Transponder - Satellite) | Stanford University | University | US | 2U | 2015-10-08 | No signal | The objective of the LMRST payload is to provide a far-field source for calibration of the DSN (Deep Space Network) X-band |  |
| PropCube 1 (Flora, Propagation CubeSat) | Naval Postgraduate School (NPS) | University | US | 1U | 2015-10-08 | Operational (Tyvak, CubeSat Developers Workshop 2018) | The CubeSats are performing dual frequency ionospheric calibration measurements of ionospheric electron density and irregularities. They performing measurements of total electron content by differential group delay, of plasma irregularities by amplitude and phase scintillations and detection of artificial ionization and irregularities generated by the HAARP, Arecibo and Sura high frequency facilities. |  |
| PropCube 3 (Merryweather. Propagation CubeSat) | Naval Postgraduate School (NPS) | University | US | 1U | 2015-10-08 | Operational (Tyvak, CubeSat Developers Workshop 2018) | The CubeSats are performing dual frequency ionospheric calibration measurements of ionospheric electron density and irregularities. They performing measurements of total electron content by differential group delay, of plasma irregularities by amplitude and phase scintillations and detection of artificial ionization and irregularities generated by the HAARP, Arecibo and Sura high frequency facilities. |  |
| SINOD-D 1 (SRI International NanoSat Orbital Demonstration) | SRI International | Company | US | 2U | 2015-10-08 | Operational? (No recent public news found) | High-speed data downlink for wide-bandwidth CubeSat payloads via software defined radio communications. | |
| SINOD-D 3 (SRI International NanoSat Orbital Demonstration) | SRI International | Company | US | 2U | 2015-10-08 | Operational? (No recent public news found) | High-speed data downlink for wide-bandwidth CubeSat payloads via software defined radio communications. | |
| SNaP-3 A ALICE ((Space and Missile Defense Command Nano-Satellite-3) | US Army Space and Missile Defense Command | Military | US | 3U | 2015-10-08 | Operational? (No recent public news found) | Related to the SMDC NAnosatellite Program (SNaP) - Joint Capabilities Technology Demonstrations. | |
| SNaP-3 B EDDIE ((Space and Missile Defense Command Nano-Satellite-3) | US Army Space and Missile Defense Command | Military | US | 3U | 2015-10-08 | Operational? (No recent public news found) | Related to the SMDC NAnosatellite Program (SNaP) - Joint Capabilities Technology Demonstrations. | |
| SNAP-3 C JIMI (Space and Missile Defense Command Nano-Satellite-3) | US Army Space and Missile Defense Command | Military | US | 3U | 2015-10-08 | Operational? (No recent public news found) | Related to the SMDC NAnosatellite Program (SNaP) - Joint Capabilities Technology Demonstrations. | |
| Argus (SLU-02) | Saint Louis University | University | US | 2U | 2015-11-04 | Launch failure | Mission is to improve the ability to model the effects of space radiation on modern electronics. We will do this by comparing the rates of on-orbit radiation events against the predictive models developed by Institute for Defense and Space Electronics (ISDE) at Vanderbilt University. |  |
| EDSN 1 (Edison Demonstration of Smallsat Networks) | NASA/ Ames Research Center | Agency | US | 1.5U | 2015-11-04 | Launch failure | Develop technology to send multiple, advanced, yet affordable nanosatellites into space with cross-link communications. Other goals of the mission include lowering the cost and shortening the development time for future small spacecraft. This technology has the potential to provide extremely flexible data correlation and distribution, simplify spacecraft operations, and accelerate data downlinks so that a satellite network could be rapidly reconfigured. |  |
| EDSN 2 (Edison Demonstration of Smallsat Networks) | NASA/ Ames Research Center | Agency | US | 1.5U | 2015-11-04 | Launch failure | Develop technology to send multiple, advanced, yet affordable nanosatellites into space with cross-link communications. Other goals of the mission include lowering the cost and shortening the development time for future small spacecraft. This technology has the potential to provide extremely flexible data correlation and distribution, simplify spacecraft operations, and accelerate data downlinks so that a satellite network could be rapidly reconfigured. | |
| EDSN 3 (Edison Demonstration of Smallsat Networks) | NASA/ Ames Research Center | Agency | US | 1.5U | 2015-11-04 | Launch failure | Develop technology to send multiple, advanced, yet affordable nanosatellites into space with cross-link communications. Other goals of the mission include lowering the cost and shortening the development time for future small spacecraft. This technology has the potential to provide extremely flexible data correlation and distribution, simplify spacecraft operations, and accelerate data downlinks so that a satellite network could be rapidly reconfigured. | |
| EDSN 4 (Edison Demonstration of Smallsat Networks) | NASA/ Ames Research Center | Agency | US | 1.5U | 2015-11-04 | Launch failure | Develop technology to send multiple, advanced, yet affordable nanosatellites into space with cross-link communications. Other goals of the mission include lowering the cost and shortening the development time for future small spacecraft. This technology has the potential to provide extremely flexible data correlation and distribution, simplify spacecraft operations, and accelerate data downlinks so that a satellite network could be rapidly reconfigured. | |
| EDSN 5 (Edison Demonstration of Smallsat Networks) | NASA/ Ames Research Center | Agency | US | 1.5U | 2015-11-04 | Launch failure | Develop technology to send multiple, advanced, yet affordable nanosatellites into space with cross-link communications. Other goals of the mission include lowering the cost and shortening the development time for future small spacecraft. This technology has the potential to provide extremely flexible data correlation and distribution, simplify spacecraft operations, and accelerate data downlinks so that a satellite network could be rapidly reconfigured. | |
| EDSN 6 (Edison Demonstration of Smallsat Networks) | NASA/ Ames Research Center | Agency | US | 1.5U | 2015-11-04 | Launch failure | Develop technology to send multiple, advanced, yet affordable nanosatellites into space with cross-link communications. Other goals of the mission include lowering the cost and shortening the development time for future small spacecraft. This technology has the potential to provide extremely flexible data correlation and distribution, simplify spacecraft operations, and accelerate data downlinks so that a satellite network could be rapidly reconfigured. | |
| EDSN 7 (Edison Demonstration of Smallsat Networks) | NASA/ Ames Research Center | Agency | US | 1.5U | 2015-11-04 | Launch failure | Develop technology to send multiple, advanced, yet affordable nanosatellites into space with cross-link communications. Other goals of the mission include lowering the cost and shortening the development time for future small spacecraft. This technology has the potential to provide extremely flexible data correlation and distribution, simplify spacecraft operations, and accelerate data downlinks so that a satellite network could be rapidly reconfigured. | |
| EDSN 8 (Edison Demonstration of Smallsat Networks) | NASA/ Ames Research Center | Agency | US | 1.5U | 2015-11-04 | Launch failure | Develop technology to send multiple, advanced, yet affordable nanosatellites into space with cross-link communications. Other goals of the mission include lowering the cost and shortening the development time for future small spacecraft. This technology has the potential to provide extremely flexible data correlation and distribution, simplify spacecraft operations, and accelerate data downlinks so that a satellite network could be rapidly reconfigured. | |
| PrintSat | Montana State University | University | US | 1U | 2015-11-04 | Launch failure | Measure and report on the characteristics of the Windform XT2.0 printed material and plating during its mission life in order to verify the utility of additive manufacturing for spacecraft structures and mechanisms. The entire structure of the small satellite will be printed with nano-carbon-impregnated plastic using a 3D printer. |  |
| STACEM | Utah State University Research Foundation Space Dynamics Laboratory | Institute | US | 3U | 2015-11-04 | Launch failure | The mission is to conduct a spaceborne optical experiment to collect imagery, both visible/near infrared and hyperspectral, of earth scenes for environmental analysis and monitoring. | |
| SUPERNOVA-BETA (TechSat I) | Pumpkin | Company | US | 6U | 2015-11-04 | Launch failure | Test flight of multiple subsystems on the SUPERNOVA 6U bus developed by Pumpkin, Inc, including structure, EPS, GPS, ADACS, CDH, and imagers. 1) Real-time image processing experiments. Use of embedded CPU/GPU on orbit. Improvements to imaging via coupled processing control pipeline, only feasible on-board. 2) Reflight of improved hardware developed for crowdFunded SkyCube in 2012-2014 Intended to provide consumer-grade Earth imagery, “tweets from space”, inflatable deorbit device. |  |
| BEVO 2 (Bevo-2, LONESTAR) | University of Texas at Austin | University | US | 3U | 2015-12-06 | Reentry 2017-06-13. Was semi-operational. | Demonstrating Autonomous Rendezvous and Docking (ARD) technology for use on cost effective, low power microsatellite infrastructures. demonstrate a state-of-the-art CubeSat attitude determination and control (ADC) suite that will be necessary to conduct ARD. The ADC suite includes a GPS receiver, MEMS gyroscopes, an accelerometer, sun sensors, star tracker, magnetometer, reaction wheels, torque rods, and a cold-gas propulsion unit. Additionally, the LONESTAR (AggieSat-4) spacecraft will photograph its partner satellite and conduct crosslink communications to calculate relative navigation solutions. |  |
| CADRE (CubeSat investigating Atmospheric Density Response to Extreme driving) | University of Michigan | University | US | 3U | 2015-12-06 | Reentry 2017-01-03. No signal | Wind Ion Neutral Composition Suite (WINCS). Flight-test low-cost dual-frequency GPS to measure atmospheric and ionospheric total electron content. Advance CubeSat capabilities to enable Armada and other NanoSat missions. Reduce the costs to perform in-situ measurements of the upper thermosphere. ADCS system pointing/knowledge accurate to 1.0°/0.1° for CubeSats. Flight testing of deployable solar panels. |  |
| Flock-2e 1 | Planet Labs | Company | US | 3U | 2015-12-06 | Reentry 2018-06-16. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e 2 | Planet Labs | Company | US | 3U | 2015-12-06 | Reentry 2018-01-23. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e 3 | Planet Labs | Company | US | 3U | 2015-12-06 | Reentry 2018-04-05. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e 4 | Planet Labs | Company | US | 3U | 2015-12-06 | Reentry 2018-03-11. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e 5 | Planet Labs | Company | US | 3U | 2015-12-06 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e 6 | Planet Labs | Company | US | 3U | 2015-12-06 | Reentry 2018-02-12. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e 7 | Planet Labs | Company | US | 3U | 2015-12-06 | Reentry 2018-04-07. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e 8 | Planet Labs | Company | US | 3U | 2015-12-06 | Reentry 2017-07-25. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e 9 | Planet Labs | Company | US | 3U | 2015-12-06 | Reentry 2017-12-25. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e 10 | Planet Labs | Company | US | 3U | 2015-12-06 | Reentry 2018-02-28. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e 11 | Planet Labs | Company | US | 3U | 2015-12-06 | Reentry 2018-03-04. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e 12 | Planet Labs | Company | US | 3U | 2015-12-06 | Reentry 2018-03-04. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| MinXSS (Miniature X-ray Solar Spectrometer CubeSat) | University of Colorado at Boulder | University | US | 3U | 2015-12-06 | Reentry 2017-05-05. Was operational. | The importance of the MinXSS mission is providing new spectral obser-vations of the solar SXR near the maximum of solar cycle 24, improving the understanding of how highly variable solar X-rays affect the ITM, and advancing the knowledge of flare energetics in the SXR. Measure the intensity of the soft x-ray spectrum from 0.6 keV (20Å) to 25 keV (0.5Å). |  |
| Nodes J (Nodes B, Nodes 2) | NASA Ames Research Center | Agency | US | 1.5U | 2015-12-06 | Reentry 2017-09-23. Was operational until 2017-04-XX? | Nodes is a technology demonstration of a pair of lowcost 1.5U CubeSats in Low Earth Orbit (LEO) with advanced cross-link and downlink communications capability, suitable as a platform for Space Weather or other science applications requiring geographically distributed, synchronized data acquisition. Companion mission to EDSN, using the same satellite design with additional new software capabilities. |  |
| Nodes K (NODes 1, Nodes 1, Nodes A) | NASA Ames Research Center | Agency | US | 1.5U | 2015-12-06 | Reentry 2017-09-19. Was operational until 2017-04-XX? | Nodes is a technology demonstration of a pair of lowcost 1.5U CubeSats in Low Earth Orbit (LEO) with advanced cross-link and downlink communications capability, suitable as a platform for Space Weather or other science applications requiring geographically distributed, synchronized data acquisition. Companion mission to EDSN, using the same satellite design with additional new software capabilities. | |
| SNAPS (Stanford Nano Picture Satellite) | Stanford University | University | US | 0.25U | 2015-12-06 | Operational? Was it even launched or deployed? (No public news found) | Image other CubeSats autonomously using H264 compression. Xreate a reference design for an inspector satellite that others can build off of and a reference process where university students can launch productive CubeSats with the highest chance of success. 1080p camera, 32-bit ARM microcontroller with SRAM and FRAM, UHF radio and non-deploying antenna, nondeploying solar array, and ~20Wh of lithium-ion battery capacity. |  |
| STMSat-1 (STM CubeSat, St. Thomas More Cathedral School) | St. Thomas More Cathedral School | School | US | 1U | 2015-12-06 | Reentry 2017-04-21. No signal. | Perform Earth Observation and engage grade school students around the World as remote mission operation centers. |  |
| Athenoxat-1 | Microspace Rapid Pte Ltd. | Company | Italy | 3U | 2015-12-16 | Operational (http://www.micro-space.org/ham.html) | Demonstrate the functionality of night vision optical payload on a Cubesat Class Nanosatellite. |  |
| Galassia | National University of Singapore | University | Singapore | 2U | 2015-12-16 | Operational (Smallsat 2018) | Main objective is for students to understand space technologies and to gain practical experiences while building, integrating and testing 2U CubeSat bus and payloads. First payload aims to measure the Total Electron Count (TEC) in the ionosphere above Singapore. The second primary payload is the Small Photon-Entangling Quantum System (SPEQS) payload, which is developed by the Center for Quantum Technologies (CQT) in NUS. A compact and efficient system for generating and detecting photon pairs is conducted. The SPEQS experiment utilizes a process called Spontaneous Parametric Down Conversion (SPDC) to generate entangled photon pairs. The generation and detection of photon pairs are performed within the package to check the quality of the entanglement. |  |
| VELOX-II | Nanyang Technological University | University | Singapore | 6U | 2015-12-16 | Operational? (Last eoPortal report 2017-05) | Experimental satellite-based communication hardware developed by Addvalue Innovation Pte Ltd, a subsidiary of Singapore Exchange mainboard listed Addvalue Technologies Ltd. This unique payload transmits data it collects to a Inmarsat geostationary communications satellite. If proven successful in space, the payload will allow the VELOX-II to send data back to the NTU ground station from anywhere even if the satellite is not flying above Singapore, as is presently the case. |  |
| HORYU-4 (AEGIS) | Kyushu Institute of Technology | University | Japan | 10 kg | 2016-02-17 | Operational? (Last DK3WN report 2017-07-13) | Horyu-4 is testing an experimental high-voltage solar array system and observing corresponding spacecraft charging effects on the satellite caused by the high voltage. The mission of Horyu-4 is to: Acquire current waveform of arcing phenomena on high voltage solar array. Acquire image of arcing phenomena on high voltage solar array. Advance our knowledge on spacecraft charging Contribute to reliability improvement of present space systems and realization of future high power space system. |  |
| Flock-2e' 1 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-04-15. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 2 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2017-12-01. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 3 | Planet Labs | Company | US | 3U | 2016-03-23 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 4 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2017-11-08. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 5 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-06-27. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 6 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-04-05. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 7 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2017-10-03. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 8 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-04-05. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 9 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-03-12. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 10 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-02-17. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 11 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-03-11. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 12 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-02-28. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 13 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-06-03. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 14 | Planet Labs | Company | US | 3U | 2016-03-23 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 15 | Planet Labs | Company | US | 3U | 2016-03-23 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 16 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-06-01. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 17 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-06-26. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 18 | Planet Labs | Company | US | 3U | 2016-03-23 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 19 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-05-12. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2e' 20 | Planet Labs | Company | US | 3U | 2016-03-23 | Reentry 2018-04-18. Was operational. | Constellation for optical Earth observation with 3-5m resolution | |
| Lemur-2 5 Theresacondor | Spire | Company | US | 3U | 2016-03-23 | Reentry 2017-03-30. Was operational. | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 6 Kane | Spire | Company | US | 3U | 2016-03-23 | Reentry 2017-04-07. Was operational. | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 7 Nick-Allain | Spire | Company | US | 3U | 2016-03-23 | Reentry 2017-04-05. Was operational. | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 8 Jeff | Spire | Company | US | 3U | 2016-03-23 | Reentry 2017-03-24. Was operational. | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 9 Cubecheese | Spire | Company | US | 3U | 2016-03-23 | Reentry 2017-03-06. Was operational. | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 10 Drmuzz | Spire | Company | US | 3U | 2016-03-23 | Reentry 2017-06-25. Was operational. | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 11 Bridgeman | Spire | Company | US | 3U | 2016-03-23 | Reentry 2017-03-08. Was operational. | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 12 Nate | Spire | Company | US | 3U | 2016-03-23 | Reentry 2017-03-23. Was operational. | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 13 Beccadewey | Spire | Company | US | 3U | 2016-03-23 | Deployment failure. Failed to deploy from Cygnus OA-6 on 2016-06-22. | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Tomsk-TPU 120 (Tomsk-TPU-120) | Tomsk Polytechnic University | University | Russia | 3U | 2016-03-31 | Operational? (No recent public news) | Test new space materials technology and will be the world’s first space vehicle with a 3D-printed structure.Tomsk Polytechnic University celebrates its 120th anniversary. As part of the celebrations on May 10-11 the Tomsk-TPU-120 will be activated in the ISS and will transmit a greeting to Earth inhabitants, recorded by students of the university in 10 languages: Russian, English, German, French, Chinese, Arabic, Tatar, Indian, Kazakh and Portuguese. |  |
| AAUSAT4 (AAUSAT-4) | Aalborg University | University | Denmark | 1U | 2016-04-25 | Operational (Last DK3WN report 2018-05-31) | Test an improved version of the AIS receiver developed by the student team, which can be used for automatic tracking and identification of vessels. As a secondary payload AAUSAT4 will also test on-orbit a 3-axis attitude control system designed by means of active magnetic actuators. |  |
| e-st@r-II | Polytechnic University of Turin | University | Italy | 1U | 2016-04-25 | Was operational until 2016-09-XX? (Last DK3WN report 2016-09-04) | Demonstrate the capability of autonomous determination, control and manoeuver, through the development and test in orbit of an A-ADCS entirely designed and manufactured by students. Test in orbit COTS technology and self-made hardware. |  |
| OUFTI-1 | University of Liège | University | Belgium | 1U | 2016-04-25 | Was operational until 2016-05-07 | Test the use of the D-STAR communication protocol in space. |  |
| SamSat-218/D (Kontact-Nanosputnik) | Samara State Aerospace University | University | Russia | 3U | 2016-04-28 | Was semi-operational? Communication problems. | The main objective of this satellite is a demonstration of navigation and control technologies. Researches aimed at improving of performance reliability of equipment will make space experiments more efficient. |  |
| BEESAT-4 | Berlin Technical University | University | Germany | 1U | 2016-06-22 | Operational (Last DK3WN report 2018-06-05) | Technology demonstration and education/ training in the field of satellite technology. A GPS receiver will get GPS signals to determine the satellite’s position accurately. Therefore 3-axes stabilization will be realized with reaction wheels and magnetorquers. A camera will take pictures of the Earth to verify the attitude of the satellite. Target for BIROS microsatellite making use of only optical or vision-based navigation which approached to 50 meters. |  |
| Flock-2p 1 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2p 2 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2p 3 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2p 4 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2p 5 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2p 6 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2p 7 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2p 8 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2p 9 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2p 10 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2p 11 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-2p 12 | Planet Labs | Company | US | 3U | 2016-06-22 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Sathyabamasat (SNSAT) | Sathyabama University | University | India | 2U | 2016-06-22 | Was operational until 2016-11-XX? (Last DK3WN report 2016-11-13) | Measure the densities of the green house gases over the region in which it moves on using ARGUS 1000 IR Spectrometer. | |
| Swayam COEP | College of Engineering, Pune | University | India | 1U | 2016-06-22 | Was operational? (Latest report from COEP Facebook from 2016) | - Passive attitude stabilisation system, plus a store and forward message system and also an experiment with an analogue power subsystem. |  |
| Aoxiang Zhixing (Star of Aoxiang, SAOX, AX-1) | Northwestern Polytechnical University | University | China | 12U | 2016-06-25 | Reentry 2016-09-29. Was operational? (No public news found) | 1) To investigate the feasibility of using polarized sunlight for spacecraft attitude determination and navigation; 2) To perform microgravity research using a miniaturized gravimeter, and 3) To demonstrate hopefully the world first 12U CubeSat platform and relevant technologies. |  |
| 3CAT2 (3CAT-2) | Universitat Politècnica de Catalunya | University | Spain | 6U | 2016-08-15 | Was operational until 2018-03-XX? (Last SatNOGS report 2018-03-03) | Perform ocean altimetry by means of Global Navigation Satellite Systems Reflectometry (GNSS-R). The main payload is the novel dual-band altimeter P(Y) & C/A ReflectOmeter (PYCARO). Also star tracker Mirabilis and experimental magnetometer for eLISA. Uses FAPEC, a powerful data compressor. PYCARO reflectometer is designed to compare a direct signal from a global navigation satellite system (GNSS) such as GPS, GLONASS, Galileo and Beidou with the same signal reflected to Earth. PYCARO therefore operates as what is called a bistatic radar, i.e. it does not emit a signal but merely captures the signals emitted by other systems. This technique is known as GNSS-R, and can be used to obtain data on ocean altimetry, sea conditions and soil moisture, among other applications. |  |
| AISat Nano (AISat-1N) | UK Space Agency | Agency | UK | 3U | 2016-09-26 | Operational (Last DK3WN report 2018-05-04) | Teach Algerian students how to design, build and operate a 3U CubeSat. The programme involves a number of Algerian graduate students who will be hosted at the Surrey Space Centre (University of Surrey) and focuses on the development of the CubeSat as a hands-on learning exercise for the students, to demonstrate the practical implementation of this type of low cost space technology. As well as the practical element of the programme there will be a focus on research modules around the use of low cost nano-satellite technologies and applications in developing nations such as Algeria, which would help to create sustainable growth and have practical uses such as earthresource management (agriculture, water), atmospheric monitoring, and disaster management. SpaceMag-PV Boom - arms used to hold instrument sensors as far as possible from the spacecraft body to minimise interference. C3D2 is a highly customisable CubeSat camera offering three fields of view and innovative on-board software processing capabilities. The payload will also be a remote experiment of the Open Science Laboratory - suite of remote experiments that supports distance learning students studying science and engineering. The payload development is led by the Open University Centre for Electronic Imaging with sensor hardware provided by e2v Ltd and electronics from XCAM Ltd. Thin Film Solar Cell is a novel and potentially step-changing solar cell structure which is directly deposited on cover glass just 1/10th of a millimeter thick. |  |
| CanX-7 | Space Flight Laboratory (SFL) | Institute | Canada | 3U | 2016-09-26 | Operational (Personal contact 2018-08-10) | Incorporate a lightweight, compact, deployable drag sail. Demonstrate the drag sail’s customizability, modularity, stowability and effectiveness at achieving the deorbiting requirements of the IADC. The results will then be used to create a low cost, modular, and customizable deorbiting device for nanosatellites and microsatellites in low Earth orbit, thus alleviating the programmatic and technical risk to space missions when using satellites of this class. Test an ADS-B (Automatic Dependent Surveillance-Broadcast) receiver developed by Royal Military College (RMC) with support from COM DEV Ltd. ADS-B is a cooperative surveillance technology for tracking aircraft. Detecting ADS-B signals from space will enable enhanced global awareness of aircraft identities, locations, and headings. CanX-7 will be among the first satellites in the world to evaluate this technology from space. |  |
| PISat (PESIT Imaging Satellite) | PES Institute of Technology | University | India | 5.3 kg | 2016-09-26 | Was operational? (Last reports from 2016 http://pes.edu/pisat/health/#!) | Provide a hands-on environment for students in all aspects of satellite building and operations. The spacecraft is equipped with an imaging instrument to capture imagery of Earth's surface. |  |
| Pratham | Indian Institute of Technology Bombay | University | India | 10 kg | 2016-09-26 | Was operational? (No recent news found) | Enabling students and faculty to gain knowledge and experience in the field of Satellite and Space technology. Empowering the Satellite Team with the skills to develop the Satellite through various phases of Design, Analysis, Fabrication and Testing until the Flight Model is made. Launching the satellite into orbit and measuring Total Electron Count of the Ionosphere. Involving students from other universities in our Satellite mission by building ground stations in their universities. |  |
| Lemur-2 14 Sokolsky | Spire | Company | US | 3U | 2016-10-18 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 15 Xiaoqing | Spire | Company | US | 3U | 2016-10-18 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 16 Anubhavthakur | Spire | Company | US | 3U | 2016-10-18 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 17 Wingo | Spire | Company | US | 3U | 2016-10-18 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| CAS 2T (Chinese Amateur Radio Satellite 2T, Fengtai-1, CAS-2T) | CAMSAT | Non-profit | China | 2U | 2016-11-09 | Semi-operational. Attached to the upper stage on purpose. Lots of CW telemetry not correct. | FM transponder. |  |
| Lishui-1 (Lishui 1-01) | Zhejiang Lizhui Electronic Technology Co | Company | China | 3U | 2016-11-09 | Operational? (No public news found) | - | |
| Pina-2 01 | Aerospace DFH | Company | China | 3U | 2016-11-09 | Operational? Was it even launched? (No public news found) | - | |
| Pina-2 02 | Aerospace DFH | Company | China | 3U | 2016-11-09 | Operational? Was it even launched? (No public news found) | - | |
| XX-1 (Xiaoxiang 1, XX1) | Spacety | Company | China | 6U | 2016-11-09 | Operational? (No recent public news) | Stabilized camera system. |  |
| AeroCube-8C (IMPACT) | The Aerospace Corporation | Non-profit | US | 1.5U | 2016-11-11 | Operational? (No recent public news found) | Demonstrate Scalable ion-Electrospray Propulsion system (SiEPro). Measure IV curves for 4-junction IMM solar cells and 5-junction SBT cell. Demonstrate CNT harness and use of CNT/PEEK material. Evaluate CNT radiation-shielding material. | .png){kind=small} |
| AeroCube-8D (IMPACT) | The Aerospace Corporation | Non-profit | US | 1.5U | 2016-11-11 | Operational? (No recent public news found) | Demonstrate Scalable ion-Electrospray Propulsion system (SiEPro). Measure IV curves for 4-junction IMM solar cells and 5-junction SBT cell. Demonstrate CNT harness and use of CNT/PEEK material. Evaluate CNT radiation-shielding material. | .png){kind=small} |
| CELTEE 1 | Air Force Research Laboratory | Military | US | 1U | 2016-11-11 | Operational? (No public news found) | Evaluate the performance of M42 Techs Enhanced Location Transponder (ELT) small satellite tracking and orbit determination technology. |  |
| OptiCube 4 (O/C, Optical CubeSat) | California Polytechnic State University | University | US | 2U | 2016-11-11 | Passive, mass dummy basically. | Provide on-orbit targets for ground assets to calibrate sensors for orbital debris studies and small-object tracking improvements Was produced as a back-up on short notice on request of the NASA Orbital Debris Program Office and the Air Force's Starfire Optical Range |  |
| Prometheus 2.1 | Los Alamos National Laboratory | Military | US | 1.5U | 2016-11-11 | Operational? (No public news found) | Improving from lessons learned on Block 1. Replacing single coil with 3 torque rods, increasing momentum wheel storage, adding star field sensor, adding GPS receiver. Possibility to add 1.5U payload at the end of the satellite. |  |
| Prometheus 2.3 | Los Alamos National Laboratory | Military | US | 1.5U | 2016-11-11 | Operational? (No public news found) | Improving from lessons learned on Block 1. Replacing single coil with 3 torque rods, increasing momentum wheel storage, adding star field sensor, adding GPS receiver. Possibility to add 1.5U payload at the end of the satellite. | |
| RAVAN XB3 (Radiometer Assessment Using Vertical Aligned Nanotubes) | Johns Hopkins Applied Physics Laboratory | University | US | 3U | 2016-11-11 | Operational? (No recent public news) | Demonstrate technology needed to measure the absolute imbalance in the Earth's radiation budget for the first time, giving scientists valuable information to study our climate. Demonstrate a radiometer that is compact, low-cost, and low-uncertainty. The radiometer uses a gallium fixed-point black body as a built-in calibration source and a vertically aligned carbon nanotube (VACNT) absorber. VACNTs are the blackest known substance. Neither the VACNT nor gallium black body has ever been used in an orbiting scientific instrument. Successful demonstration will pave the way for a constellation Earth radiation budget mission that can provide valuable measurements needed to significantly advance our understanding of ongoing and future climate change. |  |
| Aoba-Velox-III (VELOX-III) | Kyushu Institute of Technology | University | Japan | 2U | 2016-12-09 | Operational (Last DK3WN report 2018-06-04) | Technology demonstration of PPT (Pulsed Plasma Thruster). In addition, one sub-mission consists in performing communication test using Bluetooth inside the satellite. The second sub-mission consists in testing microcomputer resistance to radiations. For the PPT mission, the solid fuel collected in the capacitor is ionized and thrust is generated from Lorentz force. By measuring satellite’s angular speed, thrust performance from PPT can be evaluated. This satellite therefore aims at demonstrating the possibility of using small thruster in space. Through the mission success, utilization of such device on-board future CubeSat could be considered to extend their orbital lifetime. Moreover, in addition to the CW and HK data, AOBA-VELOXIII will also send a special message and award will be sent to the amateur radio station that receives downlink report of AOBA-VELOXIII. From this, mapping of downlink reception of AOBA-VELOXIII data could be performed. |  |
| EGG (re-Entry satellite with Gossamer aeroshell and Gps/Iridium) | University of Tokyo | University | Japan | 3U | 2016-12-09 | Reentry 2017-05-15. Was operational? | Test a deployable gossamer aeroshell for reentry. Experimental, such as torus type expansion frame structure. The satellite will deploy a 60 cm gossamer aeroshell. Also on board will be a GPS receiver for position determination and an Iridium modem for communication via the Iridium constellation. |  |
| FREEDOM | Tohoku University | University | Japan | 1U | 2016-12-09 | Reentry 2017-02-05. Was operational? | Membrane deployment orbit experiments. The satellite will deploy the DOM1500 device, which will form a 1 m by 1.5 m membrane to increase the aerodynamic resistance to accelerate the decay from orbit. |  |
| ITF-2 (Imagine The Future 2) | University of Tsukuba | University | Japan | 1U | 2016-12-09 | Operational (Last SatNOGS report 2018-07-30) | Establish human network by amateur satellite. Prove the ability of the micro engineered 1/20 wavelength small antenna. |  |
| Lemur-2 18 Trutna | Spire | Company | US | 3U | 2016-12-09 | Reentry 2018-04-15. Was operational. | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 19 TrutnaHD | Spire | Company | US | 3U | 2016-12-09 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 20 Austintacious | Spire | Company | US | 3U | 2016-12-09 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 21 Redfern-Goes | Spire | Company | US | 3U | 2016-12-09 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| OSNSAT | Open Space Network | Company | US | TubeSat | 2016-12-09 | Reentry 2018-01-11. Was operational? | - |  |
| STARS-C Koki (STARS-III Daughter, Hagoromo) | Shizuoka University | University | Japan | 1U | 2016-12-09 | Reentry 2018-03-03. Was operational. | First step of the research and development of the universe an elevator (lift), and a tether extension experiments in orbit and mission. Primary purpose of STARS-C mission is focusing on basic tether extension technology. 1. Installation of tether to be used for Space Elevator on a pico-satellite. 2. Technology demonstration of the tether extension. 3. Dynamic motion analysis of two satellites connected by tether by telemetry data received through amateur radio communication. |  |
| STARS-C Oyaki (STARS-III Mother, Hagoromo) | Shizuoka University | University | Japan | 1U | 2016-12-09 | Reentry 2018-03-03. Was operational. | First step of the research and development of the universe an elevator (lift), and a tether extension experiments in orbit and mission. Primary purpose of STARS-C mission is focusing on basic tether extension technology. 1. Installation of tether to be used for Space Elevator on a pico-satellite. 2. Technology demonstration of the tether extension. 3. Dynamic motion analysis of two satellites connected by tether by telemetry data received through amateur radio communication. | |
| Tancredo 1 | Presidente Tancredo de Almeida Neves | School | Brazil | TubeSat | 2016-12-09 | Reentry 2017-10-18. Was operational until 2017-02-XX? | First satellite of the Ubatubasat Project, designed in elementary school. Our goal is to arouse the interest in Science and Technology in our students, aged between ten to fourteen ( the youngest team in the world to build a satellite). Our tasks range from integration, testing, assembly, coding, launching and operating the satellite, aiming students to pursue careers in the science and technology areas, especially in the Space Engineering fields. The project has received since its inception the technological support from INPE, AEB- Brazilian Space Agency and UNESCO. Additionally, it is getting a lot of repercussion in the Brazilian and World media as well as a great support from the scientific community. Tancredo 1 was developed from a commercial kit supplied by the company Interorbital Systems from CA-USA, the original project has been greatly modified and improved by the project team, especially by the engineer Auro Tikami from INPE, as part of his masters dissertation. Tancredo 1 has a on-board voice recorder IC as payload, that will transmit a message chosen by a contest among students from our schools in Ubatuba. |  |
| TechEdSat-5 (PhoneSat 5, TES-5) | NASA Ames Research Center | Agency | US | 3.5U | 2016-12-09 | Reentry 2017-07-29. Was operational? | First "Modulated" Exobrake to target re-entry point. Updated Avionics, Radio, Iridium & GPS hardware. Digi XBee RF modules, taking the place of wired connections in the satellite, operated as wireless "data-crossroads" between TechEdSat 5 key components. Establish improved uncertainty analysis for eventual controlled flight through the Thermosphere. Improve prediction of re-entry location. Provide the base technology for sample return technology from orbital platforms. Provide the eventual testing of independent TDRV-based planetary missions. Provide engineering data for an OnOrbit Tracking Device that could improve the prediction of jettisoned material from the ISS. |  |
| TuPOD | GAUSS Srl | Company | Italy | 3U | 2016-12-09 | Reentry 2017-09-08. Was operational until 2017-01-24 by design. | In orbit deployment of the first TubeSats: Tancredi I from Brazil and OSNSAT from US. After the TubeSat release, the TuPOD will perform its own mission transmitting a Morse code beacon for a few days and some weeks later it will re-enter the atmosphere, disintegrating. From a technical point of view the satellite represents an innovation since its structure has been completely 3D printed. |  |
| Waseda-SAT 3 | Waseda University | University | Japan | 1U | 2016-12-09 | No signal | The small satellite will deploy a ultra light drag chute for accelerated deorbiting. A camera will observe and verify the chute deployment. Also on board will be a LCD projector to project images on the drag chute, where the camera will take pictures of it. On-orbit experiment of active thermal control mechanism by the LCD. |  |
| BY70-1 (Bayi Kepu Weixing 1) | China Center for Aerospace Science and Technology | Institute | China | 2U | 2016-12-28 | Reentry 2017-02-18. Was operational. | For school education and amateur radio. The amateur radio station onboard will provide telecommand, telemetry and FM repeater functions. 3 axis stabilised and have deployable solar panels. |  |
| Kaidun 1 (Caton 1) | Beijing Kaidun Universal Technology | Company | China | 2U | 2017-01-09 | Operational (Last DK3WN report 2018-05-06) | Test a VHF Data Exchange System (VDES) for communications via the Inmarsat satellite system |  |
| XY S1 (Xingyun Shiyan 1, Dong Fang Hong 166) | Northwestern Polytechnical University | University | China | 2U | 2017-01-09 | Operational? (No public news found) | Test L-band narrow-band communications. |  |
| TRICOM 1 | University of Tokyo | University | Japan | 3U | 2017-01-14 | Launch failure | Two cameras, one on either side, to take pictures of the Earth. Expected to operate for about a month before re-entering the earth’s atmosphere and burning up. |  |
| Al–Farabi 1 | Al-Farabi Kazak National University | University | Kazakhstan | 2U | 2017-02-15 | No signal (No public news found) | Technology demonstration and Earth observation mission. 3MP camera, testing ADCS, communication experiments. |  |
| BGUSat (NEGEVSAT) | Ben Gurion University Satellite | University | Israel | 3U | 2017-02-15 | Operational? (No recent news found) | First educational satellite. VGA Camera, ADCS. |  |
| DIDO-2 (SpacePharma, Chen Jiayong 1) | SpacePharma | Company | Israel | 3U | 2017-02-15 | Operational (Last news from ISIS 2018-05-18) | Carry the first generation of their mGnify lab to conduct biochemical experiments in microgravity. |  |
| Flock-3p 1 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 2 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 3 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 4 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 5 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 6 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 7 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 8 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 9 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 10 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 11 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 12 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 13 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 14 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 15 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 16 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 17 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 18 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 19 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 20 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 21 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 22 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 23 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 24 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 25 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 26 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 27 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 28 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 29 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 30 | Planet Labs | Company | US | 3U | 2017-02-15 | No signal (2 are non-responsive) | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 31 | Planet Labs | Company | US | 3U | 2017-02-15 | No signal (2 are non-responsive) | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 32 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 33 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 34 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 35 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 36 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 37 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 38 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 39 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 40 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 41 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 42 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 43 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 44 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 45 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 46 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 47 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 48 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 49 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 50 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 51 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 52 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 53 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 54 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 55 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 56 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 57 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 58 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 59 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 60 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 61 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 62 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 63 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 64 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 65 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 66 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 67 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 68 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 69 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 70 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 71 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 72 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 73 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 74 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 75 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 76 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 77 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 78 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 79 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 80 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 81 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 82 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 83 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 84 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 85 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 86 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 87 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| Flock-3p 88 | Planet Labs | Company | US | 3U | 2017-02-15 | Operational | Constellation for optical Earth observation with 3-5m resolution | |
| INS 1A (ISRO Nanosatellite) | ISRO | Agency | India | 8.4 kg | 2017-02-15 | Operational? (No public news found) | Two science payloads. Surface BRDF Radiometer (SBR) payload that can be used measure the Bidirectional Reflectance Distribution Function (BRDF) of targets on the Earth's surface and will be able to take readings of the sunlight reflected off different surface features. Single Event Upset Monitor (SEUM), which can be used to track Single Event Upsets that happen due to high energy radiation in space environment in Commercial, Off-the-Shelf (COTS) electronic components. |  |
| INS 1B (ISRO Nanosatellite) | ISRO | Agency | India | 9.7 kg | 2017-02-15 | Operational? (No public news found) | Carries two science payloads. EELA keeps track of terrestrial exospheric line-of-sight neutral atomic hydrogen Lyman Alpha flux and can give an estimate for the interplanetary hydrogen Lyman Alpha background flux by means of deep space observations. The Origami Camera is a remote sensing colour camera that can take high-resolution pictures of the Earth with a small package. |  |
| Lemur-2 22 Jobanputra | Spire | Company | US | 3U | 2017-02-15 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 23 Spire-Minions | Spire | Company | US | 3U | 2017-02-15 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 24 Satchmo | Spire | Company | US | 3U | 2017-02-15 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 25 Rdeaton | Spire | Company | US | 3U | 2017-02-15 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 26 Smita-Sharad | Spire | Company | US | 3U | 2017-02-15 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 27 Mia-Grace | Spire | Company | US | 3U | 2017-02-15 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 28 Noguescorreig | Spire | Company | US | 3U | 2017-02-15 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Lemur-2 29 Tachikoma | Spire | Company | US | 3U | 2017-02-15 | Operational | Weather data for government and commercial customers. Measuring signals from GPS satellites as those signals pass through the atmosphere. STRATOS imaging payload and the SENSE AIS payload. The SENSE payload enables tracking shipos worldwide by receiving their AIS signals. GPS radio occultation, provides profiles of temperature, pressure, and humidity in the atmosphere that can be incorporated into weather forecasting models. | |
| Nayif-1 | Mohammed Bin Rashid Space Centre | Institute | United Arab Emirates | 1U | 2017-02-15 | Operational (Last DK3WN report 2018-05-29) | Goal of providing an actual space project for Emirati University students. Additionally it is intended to enthuse and educate young people about radio, space physics and electronics. Carries the FUNcube 5 amateur communications payload. |  |
| PEASSS (PiezoElectric Assisted Smart Satellite Structure) | ISIS (Innovative Solutions In Space) | Company | Netherlands | 3U | 2017-02-15 | Operational? (No recent public news found) | EU FP7 project to develop, manufacture, test and qualify “smart structures” which combine composite panels, piezoelectric materials, and next generation sensors, for autonomously improved pointing accuracy and power generation in space. Smart structures will enable fine angle control, thermal and vibration compensation, improving all types of future Earth observations, such as environmental and planetary mapping, border and regional imaging. Develop and test the following smart structures: piezo actuated “smart panels” for pointing of optical instruments/sensors; piezo actuated “smart panels” for power harvesting; fiber bragg gratings for composite structure strain and temperature measurement; next generation of power conditioners for future applications in space missions. |  |
| Aalto-2 | Aalto University | University | Finland | 2U | 2017-04-18 | Was operational until 2017-05-29, 4 days? | Scientific objective to study in-situ the temporal and spatial variations of a number of key constituents and parameters in the lower thermosphere (90-320 km) in a network of about 40 double CubeSats, separated by a few hundred kilometers and carrying identical sensors. It will also study the re-entry process by measuring a number of key parameters during re-entry and by comparing predicted and actual CubeSat trajectories and orbital lifetimes. QB50. |  |
| ALTAIR 1 (ALTAIR Pathfinder) | Millennium Space Systems | Company | US | 6U (1x6U) | 2017-04-18 | Operational | Test flight of ALTAIR bus. Technology demonstration / risk reduction mission for critical subsystems for the ALTAIR product line of spacecraft. |  |
