Ballistic analysis for the manned mission to Mars with the use of solar electric propulsion system

Paper number

IAC-06-A5.P.08

Author

Prof. Garri Popov, RIAME MAI, Russia

Coauthor

Dr. Vladimir Obukhov, RIAME MAI, Russia

Coauthor

Dr. E.L. Akim, Keldysh Research Center, Russia

Coauthor

Dr. Grigory Zaslavsky, Keldysh Research Center, Russia

Coauthor

Dr. Sergey Klimov, Central Research Institute of Machine Building (TSNIIMASH), Russia

Coauthor

Prof. Mikhail S. Konstantinov, Moscow Aviation Institute (MAI), Russia

Coauthor

Mr. Gennady G. Fedotov, Moscow Aviation Institute (MAI), Russia

Coauthor

Dr. Yuri Vasiliev, RIAME MAI, Russia

Coauthor

Dr. Alexander Pokryshkin, RIAME MAI, Russia

Coauthor

Mrs. Victoria Svotina, RIAME MAI, Russia

Coauthor

Dr. Vladimir Letin, Russia

Year

2006

Abstract

Ballistic calculations for the manned mission to Mars are made in the scope required for defining performance specification for the Martian expedition complex (MEC) equipped with the solar electric propulsion system (SEPS). SEPS is used at all mission stages from MEC assembling in the near-earth orbit to the delivery of return module (RM) with crew to the Earth. Two MEC options are proposed: modern and perspective. SEPS development for modern MEC may be implemented during several coming years, while for the perspective one – in the nearest future. Basic MEC characteristics for both options are the fallowing:
	                      Modern MEC/Perspective MEC
MEC mass at the moment of rev-up start near Earth, ton                                             560/560
SP electric power at the moment of start, MW    5.0/5.5
EP specific impulse, m/s                    30000/35000
EP efficiency                                 0.60/0.65
Material, on the basis of which SP is developed	            amorphous silicon/amorphous silicon
MEC mass at the moment of rev-down completion 
near Earth, ton	                             158.9/188.1
Mass of return module (RM), ton	                   60/90
Propellant mass on board spacecraft at the moment
of rev-up start near Earth, ton	             304.4/277.7
SEPS specific mass, kg/kW	             18.02/16.29
Total flight time, days	                       1277/1290
Total period of EPS active operation, hour   20000/21100
Total increment for the spacecraft characteristic velocity, m/s                                26700/26700
Total SEPS thrust impulse, MNs                 9250/9750
The problem of photovoltaic cell radiation resistance, that displays itself at the stage of rev-up near Earth, predetermined selection of amorphous silicon as the SP material and respective level of SEPS quality index within 16 – 18 kg/kW. Primary conclusion for this work: even at the modern level of space engineering in view of the immediate perspectives such complicated expedition as manned mission to Mars may be considered as quite realizable.

Abstract document

IAC-06-A5.P.08.pdf

Manuscript document

IAC-06-A5.P.08.pdf (🔒 authorized access only).

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