E.T.PACK DMM & EEM Satellite

Spacecraft E.T.PACK DMM & EEM (Electrodynamic Tether technology for PAssive Consumable-less deorbit Kit, E.T.PACK-F)
Type CubeSat
Units or mass 12U
Status not launched, expected in 2025
Launcher not launched
Organisation Universidad Carlos III de Madrid
Institution University
Entity Academic / Education
Country Spain
Manufacturer AIVT by ?
Operator ?
Partners Universidad Carlos III de Madrid (UC3M), University of Padova, Technical University of Dresden (TU Dresden)
Costs €5.5M

Develop a deorbit device based on 500m electrodynamic tether.


The E.T.PACK deorbit device has been designed to fit into a standard 12U envelope, with a maximum mass of 24 kg. It is composed of two modules: the Deployment Mechanism Module (DMM), with an approximated dimension of 2U x 2U x 1.5U, and the Electron Emitter Module (EEM), with 2U x 2U x 2.5U of rough size. The DMM hosts 500 m of tape-tether (80% Aluminum and 20% PEEK) and it is responsible for deploying it.

The EEM main goals are (i) to emit the electrons captured by the tether back to the ambient plasma to maintain a steady electrical current in the tether, (ii) to activate the Hold Down and Release Mechanism (HDRM) before the tether deployment to break the mechanical connection between it and the DMM, and (iii) provide the necessary acceleration during the deployment phase. The avionics of both modules is similar, with some differences that correspond to the dedicated electronics of the deployment mechanism in the DMM and the electron emitter in the EEM.  

Universidad Carlos III de Madrid (UC3M, Coordinator), the University of Padova, the Technical University of Dresden (TU Dresden), the Spanish company SENER Aeroespacial and the German start-up Rocket Factory Augsburg (RFA). 

Sources [1] [2]
Photo sources [1]
Keywords Propulsion

Last modified: 2024-05-29

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