Sustainable Satellite Design Activities in the ESTEC CDF - Congrex

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De-orbiting study – Continuing in the field of de-orbiting – Kick-off on the 3rd June 2009 and finishing with an Internal Final Presentation on the 16th July 2009 – The objective was to create an ‘add-on’ package that can easily be attached to a spacecraft – in line with “design for reuse” – The CDF team assessed, more in detail, requirements stated in the Code of Conduct for Space Debris Mitigation – ESA satellites within certain regions (LEO/MEO/GEO) required to de- or re-orbit within 25 years – In case the total casualty risk is larger than 10 -4 , uncontrolled re- entry is not allowed – Solid rocket motors releasing burn products larger than 1mm into orbit shall not be used – Different options were assessed (same system trade-off, however without LCA index) – Two baselines were selected. The only baseline allowing for an immediate re- entry (i.e. controlled re-entry) was based on solid-propulsion – Same option as ECOSAT ESA CDF sustainable activities | Robin Biesbroek | SECESA2010 | 13/10/2010 | D/TEC | Slide 16 ESA UNCLASSIFIED – For Official Use
De-orbiting aspects using solids – High thrust level of solids – The thrust level should be low enough not to rip the satellite apart when ignited i.e. causing more space debris! – In this study, the acceleration caused by the thrust was limited to 0.04 g, similar to g-force limits on geostationary satellites – The amount of burn products released in space – The Code of Conduct for Space Debris Mitigation requires that solid rocket motors releasing burn products larger than 1mm into orbit shall not be used – This was solved by selecting aluminium-free propellants. – Autonomy – Typically satellite operators tend to operate spacecraft until a critical sub-system fails, or contact is lost. In this case, a de-orbit sequence won’t be possible unless the de-orbiting package can be managed autonomously – Even if there is no malfunction, and it’s required to de-orbit, operators try to get away with it (apply for ‘waivers’, or continue until propellant runs out) – Solid propulsion seems the best solution for implementing an autonomous system, as they require only little energy to be ignited (using a small primary battery to supply power) and have a short duration thrust – One problem remaining is how to achieve the correct attitude of the spacecraft; this was investigated at high level but requires further detail ESA CDF sustainable activities | Robin Biesbroek | SECESA2010 | 13/10/2010 | D/TEC | Slide 17 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 and 14: ECOSAT C2C aspects: conclusions - U
Page 15: ECOSAT sub-system trade-offs - Mate
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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