Design of a Low-Cost Microsatellite Test-Bed for State-of-the-Art Planetary Observation Payloads
- Paper number
IAC-07-E2.3.06
- Author
Mr. Sybren De Jong, Delft University of Technology (TU Delft), The Netherlands
- Coauthor
Mr. Stefan Brak, Delft University of Technology (TU Delft), The Netherlands
- Coauthor
Mr. Rob Hamann, Technical University of Delft (TUDelft), The Netherlands
- Coauthor
Mr. M.C. Naeije, Delft University of Technology (TU Delft), The Netherlands
- Coauthor
Dr. S. Kraft, The Netherlands
- Year
2007
- Abstract
Space-qualification of state-of-the-art planetary observation payloads is preferably executed before these payloads are sent on expensive large-scale missions. This study presents a possibility for companies to qualify their advanced payloads by testing them in a microsatellite of low-cost. The Stereo Imaging and Laser Altimeter (SILAT) [1] payload was originally developed for the BepiColombo mission to Mercury, but was not selected by ESA because it contained non-proven technologies. The SILAT is a highly integrated payload that combines a high-resolution camera, a stereo camera and a laser altimeter in one single instrument. To qualify the SILAT this study presents a microsatellite design using existing technologies. This microsatellite has a mass of only 25~kg, a time-to-launch of just three years and costing less than 4 million euro. The microsatellite is designed for a low Earth orbit and it consists of five subsystems. The first subsystem is the attitude determination and control subsystem (AD\&C). Since SILAT requires accurate pointing, the AD\&C subsystem is an advanced three-axis control system. Attitude determination is based on a system of gyroscopes, magnetometers and star trackers. Reaction wheels and magnetic torquers are implemented as actuators. The telemetry, tracking and command subsystem (TT\&C) is also driven by demanding requirements from SILAT since a high data volume will be produced. For the TT\&C subsystem a space-proven computer and transceiver, a helix antenna and GPS receivers for tracking have been selected. The electrical power system (EPS) is designed as a direct energy transfer configuration. The EPS consists of three body-mounted GaAs solar arrays, lithium-ion batteries and a simple power regulator. The structure of the microsatellite has been designed as a 40~cm cube. This cube is made out of aluminium honeycomb panels with one extra panel inside to redirect launch forces and to allow mounting of devices. The thermal subsystem is a fully passive system. It provides an appropriate temperature envelope for all subsystems and facilitates a coldfinger for SILAT to unload heat. Apart from the SILAT, also other planetary observation payloads can be tested by the microsatellite. An accommodation feasibility for a spectrometer has been analyzed and proven, thereby demonstrating the adaptability of the design. In conclusion, the microsatellite presented allows for an efficient solution for space-qualification of state-of-the-art planetary observation payloads costing less than 4 million euro. \vskip 2mm \noindent References: \noindent [1] S.~Kraft, J.~Moorhouse, M.~Collon, A.~Palacios, J.~Montella, K.~Wielinga, E.~Kroesbergen, J.~Harris, C.~Erd, P.~Falkner, and A.~Peacock. \newblock Demonstration of highly integrated payload architectures and instrumentation for future planetary missions. \newblock 2005.
- Abstract document
- Manuscript document
IAC-07-E2.3.06.pdf (🔒 authorized access only).
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