A study of the Attitude Control System (ACS) is made for a solar electric propulsion geosynchronous transfer mission. The basic mission considered is spacecraft injection into a low altitude, inclined orbit followed by low thrust orbit changing to achieve geosynchronous orbit. Because of the extended thrusting time, the mission performance is a strong function of the attitude control system. Two attitude control system design options for an example mission evolve from consideration of the spacecraft configuration, the environmental disturbances, and the probable ACS modes of operation. The impact of these design options on other spacecraft subsystems is discussed. The factors which must be considered in determining the ACS actuation and sensing subsystems are discussed. The effects of the actuation and sensing subsystems on the mission performance are also considered.
Spacecraft attitude control for a solar electric geosynchronous transfer mission
11th Elec. Propulsion Conf ; 1975 ; New Orleans, LA, United States
1975-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Magnetic attitude control for geosynchronous spacecraft
AIAA | 1978
|Magnetic attitude control for geosynchronous spacecraft
Tema Archiv | 1978
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