Sustainable Satellite Design Activities in the ESTEC CDF - Congrex

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ECOSAT de-orbiting system trade-off – Bad LCA indices were obtained for inflatable & cold-gas propulsion systems (due to high mass → large amount of aluminium) and Xenon-based electrical propulsion (due to difficult process to obtain Xenon) – With the exception of Xenon, any normal CDF system trade-off (minimizing mass, typically) would lead to the same result! – Level 1 design was done for de-orbiting using mono-propellant (slow re-entry) & solid propulsion ESA CDF sustainable activities | Robin Biesbroek | SECESA2010 | 13/10/2010 | D/TEC | Slide 14 ESA UNCLASSIFIED – For Official Use
ECOSAT sub-system trade-offs – Material selection for the satellite structure – Solar panel material trade-off (GaAs versus Si cells) – Reduction of the amount of used ground-stations by using a relay satellite – Launcher propellants and green propellants have a high impact on the eco-footprint – Improvement of clean-room air-conditioning by better ceilings, new doors – Reduction of paper work during Research and Development processes – Reduction of amount of travel during projects – Office conditions for project team members (air-conditioning) – Tele-testing and increased use of virtual models and simulation for spacecraft testing – Increasing the amount of satellite autonomy. – Again it was concluded that most trade-offs were performed in any satellite design (not taking into account environmental issues): – satellite structures are often based on CFRP due to its good structure qualities (high stiffness at low mass) – While a Si cell would receive a better LCA index than a GaAs cell, the LCA trade- off would still favour GaAs cells due to their lower mass (the LCA index of the entire solar panels system is lower than a Si system) ESA CDF sustainable activities | Robin Biesbroek | SECESA2010 | 13/10/2010 | D/TEC | Slide 15 ESA UNCLASSIFIED – For Official Use
Page 1 and 2: Sustainable Satellite Design Activi
Page 3 and 4: Introduction - Several activities w
Page 5 and 6: Introduction to C2C and LCA - Cradl
Page 7 and 8: ECOSAT C2C aspects - After the work
Page 9 and 10: 2a. Design for disassembly - Disass
Page 11 and 12: 2c. Design for recycle - On-orbit s
Page 13: ECOSAT C2C aspects: conclusions - U
Page 17 and 18: De-orbiting aspects using solids -
Page 19 and 20: Team behaviour - The subject of sus
Page 21: Conclusions and recommendations - T

Sustainable Satellite Design Activities in the ESTEC CDF - Congrex

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