Publication Date:
2019-07-13
Description:
The attitude determination sensing and processing of the system are considered, and inertial reference units, star trackers, and beacons and landmarks are discussed as well as an extended Kalman filter and expected attitude-determination performance. The baseline controller is overviewed, and a spacecraft motion compensation (SMC) algorithm, disturbance environment, and SMC performance expectations are covered. Detailed simulation results are presented, and emphasis is placed on dynamic models, attitude estimation and control, and SMC disturbance accommmodation. It is shown that the attitude control system employing gyro/star tracker sensing and active three-axis control with reaction wheels is capable of maintaining attitude errors of 1.7 microrad or less on all axes in the absence of attitude disturbances, and that the sensor line-of-sight pointing errors can be reduced to 0.1 microrad by SMC.
Keywords:
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Type:
AIAA PAPER 91-2832
,
AIAA Guidance, Navigation and Control Conference; Aug 12, 1991 - Aug 14, 1991; New Orleans, LA; United States
Format:
text
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