MFC-MDR-PRE-F
- 1. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Mars Flyby CubeSat (temporary name) 22 October 2013 Mission Definition Review
- 2. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK CubeSat on an Earth-Mars Free-Return Trajectory to study radiation hazards in the future manned mission 22 October 2013 Mission Definition Review
- 3. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK • CubeSat Concept • Primary Mission Objective • High-level specifications & secondary objectives • MFC Payloads • MFC Main Challenges • MFC Preliminary Design • Conclusion Table of Contents 22 October 2013 Mission Definition Review
- 4. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK CubeSat Standard• CubeSat concept 1999 => Deployment standard Bob Twiggs Stanford University Jordi Puig-Suari California Polytechnic State Univ. • Many educational missions already launched! • Only a few interplanetary cubesat projects => Interplanetary & Education & Science Data 2U: 10cmx10cmx20cm 2Kg (2.6Kg) 1U: 10cmx10cmx10cm 1Kg (1.3Kg) 3U: 10cmx10cmx30cm 3Kg (4Kg) PACE Nanosatellite © NCKU Robusta, MaSat-1 and PW-Sat © ESA CSSWE CubeSat © University of Colorado Boulder 22 October 2013 Mission Definition Review
- 5. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK • CubeSat Concept • Primary Mission Objective • High-level specifications & secondary objectives • MFC Payloads • MFC Main Challenges • MFC Preliminary Design • Conclusion Table of Contents 22 October 2013 Mission Definition Review
- 6. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Primary Mission Objective - Radiation Measurements - • Lack of measurements between Earth and Mars. – only RAD on CURIOSITY was successful, – only on the way to go, – optimized to study on Mars, not during the cruise. • Lessons from RAD : – « simultaneous multisite measurements are key- data for Space Weather understanding » – « Solar min.activity is a key-period to study GCR » • Mission Focus : Scout the Manned Mars Missions. – Future crews will be exposed to hazardous radiations : which ones are dangerous? – Catch observational data of radiation hazards during the Earth-Mars-Earth journey. Picture of RAD Radiations Assessment Detector © NASA NASA Goddard Space Weather Research Center 22 October 2013 Mission Definition Review
- 7. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Primary Mission Objective - Focus on Mars Science Laboratory/RAD - RAD made for studying radiations on Mars! MSL and RAD © NASA 22 October 2013 Mission Definition Review
- 8. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK • CubeSat Concept • Primary Mission Objective • High-level specifications & secondary objectives • MFC Payloads • MFC Main Challenges • MFC Preliminary Design • Conclusion Table of Contents 22 October 2013 Mission Definition Review
- 9. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK High-level specifications • Volume: • 3U Cubesat. • 1,5U for radiations payload. • Trajectory: • Should be able to autonomously catch a Free-Return Earth-Mars trajectory after being jettisoned. • Tool to be developed to early assess the feasibility of trajectory corrections and flyby computation. • Autonomous regarding navigation because no communications. • Use of AOCS electrical propulsion and optical subsystems for navigation. • Onboard image processing for navigation. • Communications: • Only opportunity soon after being jettisoned, in Mars’s vicinity using another Martian orbiter and when back nearby the Earth. • Sience data: • Because of lack of communications long data storage and prepocessing. 22 October 2013 Mission Definition Review
- 10. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Mission Objectives - Secondary Mission Objectives - Earth Mars Free-Return => Small corrections of trajectory mandatory CubeSat to contribute to the global hunt for asteroids and other hazardous natural objects that may strike Earth. Very accurate optical AOCS with propulsion system needed Asteroid 2012DA14 (~50 meters wide) captured from Earth by the La Sagra Sky Survey in 2012 ~4millions kms away from Earth © LSS Near Earth Asteroids observed by WISE (NASA mission) © PERC/Chitec 22 October 2013 Mission Definition Review
- 11. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Mission Objectives - Secondary Mission Objectives - CubeSat jettisoned from a “host” mission going to Mars if requested by “host”, CubeSat to take pictures of the Host Selected pictures of the “host”, or Alert/Science data to be sent to the “host” and transferred back to the Earth CubeSat is a travel companion of Host mission, separated by few kilometers (host's safety) CubeSat to improve the situational awareness of the “Host” mission Artist view of the Martian CubeSat taking pictures of its “host” © NCKU 22 October 2013 Mission Definition Review
- 12. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Mission Objectives - Summary - To scout the manned mission by catching observational data of radiation hazards during the Earth-Mars-Earth journey. To improve the situational awareness of the “host” mission. To contribute to the global hunt for asteroids and other hazardous natural objects that may strike Earth. PRIMARY MISSION OBJECTIVE SECONDARY MISSION OBJECTIVE (AS A CONSEQUENCE OF THE PRIMARY MISSION OBJECTIVE) OPTIONAL MISSION OBJECTIVE 22 October 2013 Mission Definition Review
- 13. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK • CubeSat Concept • Primary Mission Objective • High-level specifications & secondary objectives • MFC Payloads • MFC Main Challenges • MFC Preliminary Design • Conclusion Table of Contents 22 October 2013 Mission Definition Review
- 14. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK MFC Payloads - Radiations Instrument - Particle species Quality factor Relevance Protons 1-7 Largest flux, large contributor to total dose. He (α particles) 2-30 Large flux, high Q at low energies thus large contributor to equivalent dose. HZE (C, O, Mg, Si) 5-30 High Q with large probability of reaction in body tissue. HZE (Fe) 6-30 High Q with largest probability of reaction in body tissue, large contributor to equivalent and effective dose (primary astronaut safety concern). Electrons 1 SEP precursor, highly penetrating, large fluence during SEP events (even with Q=1, large fluence contributes to large equivalent dose). Primary and secondary particles through spacecraft © E. R. Benton, E.V. Benton, March 2001 Particles to be studied by Martian CubeSat Quality factor (also weighting factor) = Quantity expressing the biological damage Identification of ions by species (or at least by group, e.g., C–N–O) is required to use the new risk assessment tools developed by NASA. Study primary particles causing direct damage or undirectly via secondary particles production. Goal is not to directly study the secondary particles. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK 22 October 2013 Mission Definition Review
- 15. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK MFC Payloads - Asteroids/NEO Optical Instrument - F°(solar flux & wavelengths ) Integration time Distance ast-CubeSat Pupil radius 704 Interamnia from Earth © Cerulli/Teramo Observatory Projets Master OSAE / Observatoire de Paris 27/10/2013 e.g. an asteroid with a magnitude of 20 (260-500m diameter) can be seen at a distance of 10⁶km 22 October 2013 Mission Definition Review
- 16. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK • CubeSat Concept • Primary Mission Objective • High-level specifications & secondary objectives • MFC Payloads • MFC Main Challenges • MFC Preliminary Design • Conclusion Table of Contents 22 October 2013 Mission Definition Review
- 17. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Main Challenges - Trajectory corrections - • Earth-Mars free-return trajectory that leaves Earth, fly by Mars and return to Earth without any deterministic maneuver after Trans-Mars injection. Trajectory corrections © Inspiration Mars Foundation After separation from launcher Before Mars Flyby After Mars Flyby 22 October 2013 Mission Definition Review STK trajectory of MFC
- 18. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Main Challenges - Trajectory corrections - • After Trans-Mars injection, only small corrections of trajectory are needed. • Use of an electrical propulsion onboard the CubeSat for trajectory corrections and attitude control. • Typically TRL 5 for CubeSat electrical propulsion systems. e.g. Key Performance Characteristics, Busek Micro-Pulsed Plasma Thruster © BUSEK departing Earth at 8-9 km/s 1H thrust => +0.45 m/s is this enough ? 22 October 2013 Mission Definition Review
- 19. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Main Challenges - Trajectory corrections : a few m/s for ΔV budget - YES ! Based on a Hohmann transfer from Earth's orbit to Mars's orbit Small corrections are sufficient • to cancel the jettisoning shock (1-2m/s) • to select the right approach path into Mars vicinity. Prograde ΔV = +/-0.45m/s +/-40'000km on encounter +/-3H on Mars' path • to select the correct flyby, i.e. – Mars-focused hyperbolic trajectory – Twist the orbital plane for the return (initial results, checks still in process) departing Earth at 8-9 km/s 1H burst => +0.45 m/s is this enough ? 22 October 2013 Mission Definition Review
- 20. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Main Challenges - Trajectory corrections : (θ, ΔV) trade-off ΔV θ 22 October 2013 Mission Definition Review
- 21. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK ΔV θ Main Challenges -Trajectory corrections : (θ, ΔV) trade-off (e.g.) a prograde ΔV=2m/s at θ=100° moves the apocenter by ~175'000km « left » (-x) and ~30'000km opposite to the Sun (+y) Sun ↓ 22 October 2013 Mission Definition Review 22 October 2013 Mission Definition Review
- 22. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Main Challenges - Communications - • The CubeSat would acquire data during its way to Mars and transmit them to a Martian orbiter while approaching Mars. • It would also acquire data on its way back to Earth and transmit them to the Ground Stations when back nearby the Earth. After separation from launcher Nearby Mars Return nearby Earth Communication opportunities 22 October 2013 Mission Definition Review
- 23. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Main Challenges - Onboard Storage and Data Processing - • CubeSat needs to be very autonomous due to the lack of communication opportunities. • Data from optical navigation, storage of pre-processed data needed. • Probably use of FPGA. Researches on FPGA for CubeSats. • Strong efforts must be done regarding the onboard data processing. 22 October 2013 Mission Definition Review
- 24. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK • CubeSat Concept • Primary Mission Objective • High-level specifications & secondary objectives • MFC Payloads • MFC Main Challenges • MFC Preliminary Design • Conclusion Table of Contents 22 October 2013 Mission Definition Review
- 25. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK MFC Preliminary Design Radiations Payload Asteroids/NEO Payload Electrical Propulsion 3 axis thrusters 22 October 2013 Mission Definition Review
- 26. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK • CubeSat Concept • Primary Mission Objective • High-level specifications & secondary objectives • MFC Payloads • MFC Main Challenges • MFC Preliminary Design • Conclusion Table of Contents 22 October 2013 Mission Definition Review
- 27. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Conclusion • This Educational Martian CubeSat would scout the manned mission to Mars by measuring radiations in situ over the full Earth-Mars-Earth journey. • Improve the Space Situational Awareness for the Earth by notifying unknown asteroids and other hazardous natural objects that may strike Earth. • And in the case of a launch as a piggyback of another Martian mission, it could improve the Situational Awareness of the “host” mission. • Phase 0 : Mission Design Review 22 October 2013. • Phase A : 06/2013-... • Phase B : from 10/2013, new students involved. • Precursor flight will be needed for testing some functions of the MFC. • Free-return trajectory opportunity in 2018. Dust devil hunters © 2005 - Association Planète Mars / Manchu ALL MARS MISSIONS COMPATIBLE! 22 October 2013 Mission Definition Review
- 28. 22 October 2013 Mission Definition Review REVIEWERS
- 29. European Planetary Science Congress 2013 8 – 13 September 2013, London, UK Thank You! Contact points: Project Mgr: boris.segret@obspm.fr System Mgr: jordan.vannitsen@gmail.com Mentors & Supporters: CNRS-LATMOS : Pr. M.Cabane, D.Coscia Mars Society Switzerland : P.Brisson Association Planète Mars : B.Segret NCKU : Pr. J.J.Miau, Pr. J.C.Juang Students: NCKU : J.Vannitsen, A. Heimann ELISA : A.Ansart, Q.Tahan … and many others to join in the coming years! 22 October 2013 Mission Definition Review