A method is presented for open loop guidance of a solar electric propulsion spacecraft to geosynchronous orbit. The method consists of determining the thrust vector profiles on the ground with an optimization computer program, and performing updates based on the difference between the actual trajectory and that predicted with a precision simulation computer program. The motivation for performing the guidance analysis during the mission planning phase is discussed, and a spacecraft design option that employs attitude orientation constraints is presented. The improvements required in both the optimization program and simulation program are set forth, together with the efforts to integrate the programs into the ground support software for the guidance system.
Development of a unified guidance system for geocentric transfer
American Institute of Aeronautics and Astronautics, Electric Propulsion Conference ; 1975 ; New Orleans, LA
1975-03-01
Conference paper
No indication
English
Solar-electric geocentric transfer
NTRS | 1979
|Optimal low thrust geocentric transfer
AIAA | 1973
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