Ten-koh 3 Spacecraft - Nanosats Database

Spacecraft name	Ten-koh 3
Form factor	CubeSat
Units or mass	3U
Status	not launched, expected in 2025
Launcher	not launched
Organisation	Nihon University
Institution	University
Entity	Academic / Education
Country	Japan
Partners	Japan Amateur satellite communications Association (JAMSAT), JARL
Oneliner	Amateur radio mission with a digipeater system using LoRa modulation and a camera.
Description	Amateur Mission. Operation of a digipeater system using LoRa modulation. Amateur radio operators uplink any message to Ten-koh 3 at 145 MHz (AFSK modulation). Ten-koh 3 downlink the received messages and HK data in the 430MHz LoRa modulation system. One month after launch, we plan to run this operation for two days continuously every week. Educational mission. Demonstration of the operation of the image compression algorithm “ICER” Data is generated using an image compression method and error-correcting code that can tolerate the data loss used in planetary exploration rovers. This reduces the effect of the error rate that increases when the communication data rate is increased. This mission is to capture images and process, store and transmit the captured data as packet data with error correcting codes. One month after launch, we plan to run this operation for once every five days. Observation of degradation of advanced materials This is a mission aimed at space demonstration of materials for space applications. Data from strain gauges, temperature sensors, UV sensors and cameras are used to observe and evaluate the degradation of PEEK/CFRTP and the base material PEEK. During sunlight, the strain gages, temperature sensors and UV sensors are activated for three minutes to acquire data. Also, photos are taken with the camera to observe the deterioration. During shade, the strain gages, temperature sensor and UV sensor are activated for three minutes to acquire data. The data obtained from the photography and measurements are downlinked. After launch, we plan to run this operation for once every five days in sun and shade. Attitude angle detection Earth images taken by the observation visible light camera are processed to derive the satellite attitude angle using on-board processing in the satellite. To evaluate the usefulness of the attitude angle derived from the image processing, an IMU six axis sensor with an accuracy that meets the mission requirements will be installed. Although the goal of this mission is to derive a two-axis attitude angle, three-axis attitude angle detection is also possible through sensor fusion with the IMU. The captured images of the Earth, numerical data of the satellite attitude angle derived through image processing, and numerical satellite attitude data obtained from the IMU six-axis sensor data are downlinked. After launch,the camera is tested during Early Orbit Phase. One month after launch, we plan to run this operation for once a week.
Sources	[1]

Last modified: 2024-12-26