Phobos Sample Return Mission
- Paper number
IAC-07-A3.3.07
- Author
Dr. Georgy Polishchuk, Lavochkin Association, Russia
- Year
2007
- Abstract
Subjects of research:
- Laboratory examination of Fobos substance, delivered to Earth; - Research of Fobos and monitoring of Mars from landing module; -Research of Fobos and its surrounding space from orbital module.
MAIN FACTS:
Launch Vehicle (LV)...Soyuz-2/1b Launch site...Baikonur Cosmodrome Launch date...October, 2009 Interplanetary Earth – Mars cruise time...10 – 11.5 months Launch from Phobos…...July –August, 2011 Interplanetary Mars – Earth cruise time....10.5 – 11.5 months Return to Earth ...June – July, 2012 Mission total time... 33-34 months SC mass...8120 kg Scientific equipment mass...50 kg Phobos soil samples mass...0.2 kg
MISSION MAIN PHASES
1. SC launch and insertion by 3 steps “Soyuz” LV into 200 km circle earth orbit with inclination of 51.8 grad; 2. Injection PS first ignition to transfer into the parking orbit; 3. Injection PS 2nd ignition PS separation; 4. Cruise Module (CM) PS ignition to get into the hyperbolic Earth flying-off trajectory; 5. Earth – Mars cruise, TCMs; 6. Reacceleration by means of CM PS into 3-days Mars orbit; 7. Combining the SC orbit and the Mars orbit by means of CM PS and increase perigee altitude up to 9910 km; 8. SC transfer into observation orbit by means of CM PS, carrying out navigation observations of the Fobos, needed for further approaching of SC and Fobos orbits and landing; 9. By means of CM PS SC is transferred into quasisynchronical orbit, which has the same orbital period as Fobos, but differs from it by altitude on the one part of the circuit up to plus 50, and on the other up to minus 50 km; 10. Phobos landing; 11. Phobos soil sampling; 12. Cruise module and return vehicle separation; Return Vehicle (RV) PS ignition and boost up to 10 m/sec. velocity; Searching the Sun. RV solar orientation; 13. RV PS gives the solar directed impulse and RV is inserted into parking orbit; 14. Giving out velocity impulse and RV moving into basic orbit; 15. SC acceleration by RV PS into 3 days parking orbit; 16. Start of RV flight to Earth; 17. Mars – Earth cruise. TCMs; 18. RV flight through the Earth incidence, forming of descent module reentry trajectory; 19. Descent module separation, aerocapture, aerobraking and SC landing at inhabited landing area at specified landing point 20.Descent module search and evacuation.
Co-authors: Dr.Pichkhadze, pichkhadze@laspace.ru Maxim Martynov, maxsim.martynov@laspace.ru
Lavochkin Association 24, Leningradskaya st., Khimki, 141400, Moscow region, Russia, tel /fax: +7 495 573 92 56, E-mail vorontsov@laspace.ru
- Abstract document