The optimization of satellite orbits between the Earth and an asteroid when the satellite is powered by a low thrust ion drive or solar power unit was studied. It was assumed that the satellite is launched by an Ariane type launch vehicle. A hybrid Pontryagin/recursive quadratic programming approach was used. The software was developed on DEC System-10 computer and implemented on the ESOC Siemens 7865 Computer System. Results for 13 mission simulations are discussed.
Low Thrust Orbit Optimization for Interplanetary Missions, Volume 1
1983
117 pages
Report
No indication
English
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