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JumpSat Thermal and Mechanical Analysis

Martin Lopez, Eduardo and Lizy-Destrez, Stéphanie JumpSat Thermal and Mechanical Analysis. ( In Press: 2015) In: Proceedings of 3rd IAA Conference on University Satellite Missions and Cube Sat Workshop Satellites, 30 November 2015 - 5 December 2015 (Rome, Italy).

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Abstract

In 2017, Swiss Space Systems (S3) is planned to operate unmanned suborbital space planes for launching small satellites. Within this scenario it was supposed to be launched JumpSat, a 3-Units CubeSat developed by ISAE-SUPAERO students, in collaboration with ONERA, CNES, and TELECOM Bretagne. JumpSat mission was proposed by ISAE in 2012. Their main objectives are both in-orbit technological demonstration and scientific research [1], through an elliptical Low Earth Orbit (LEO). The students are entirely involved in this mission, beyond both technological and scientific objectives, from the early stage to the disposal. ONERA, in Toulouse, is developing Dynagrad, a radiation sensor for trapped particles in the Earth’s magnetic belts, especially in the South Atlantic Anomaly (SAA), to improve the current models of radiation and their accuracy. Space qualification for a low-cost Star Tracker is under development at ISAE-SUPAERO. It will provide enough useful knowledge about system concept and software development for future small satellites missions. Another technological demonstration will accomplish a space qualification for the three-axis attitude control sub-system (AOCS) within the JumpSat mission. The acquired knowledge will help future CubeSatsAOCS sub-systems, while other components are COTS.Moreover, a consortium with Thales Alenia Space, LAAS and ISAE-SUPAERO designed NIPMH (Nanosatellite Investigate Microwave Photonic Hardware), an experimental payload based on opto-microwave technology. It would be embedded in a 3U CubeSat for testing different components sensitivity to radiations in space, especially the optical fiber doped with erbium. Furthermore,due to the similarities among both missions, it was analyzed the possibility of the combination of both projects: NIMPH as an additional payload to JumpSat mission. It increases the mission duration up to a minimum of two years, with respect to French law for Space Operations (maximal mission duration: 25 years). This paper will focus on mechanical and thermal aspects that were completely redesigned for JumpSat to comply with all requirements of both missions. From that point comes out the idea of building the first 6U CubeSat by ISAE-SUPAERO. As those studies are present in all design phases, they have important impact on the optimal architecture design within all the subsystems. Finally, temperatures gradients are such a great problem in space that it is even more important with strong radiation doses, like for this mission. Then, thermal analysis for worst cold and hot cases is critical for analyzing the impact of the new payload within the mission.

Item Type:Conference or Workshop Item (Paper)
Audience (conference):International conference proceedings
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Institution:Université de Toulouse > Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE)
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Deposited By: Lizy-Destrez Stéphanie
Deposited On:07 Dec 2015 14:46

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