Abstract
Attitude stabilization and attitude maneuvers of agile small spacecraft were studied using SGCMG as the attitude control actuator during the failure of some of the control moment gyros (CMGs). This study analyzed the effects of configurable variations and the effects on the angular momentum envelope and output torque caused by one SGCMG failure of pyramid configuration (PC). An optimization and coordinate conversion method was designed to utilize the maximum workspace after CMG failure to generate larger torques. Simulations of the responses of the attitude control system of a small spacecraft during slewing show that the small spacecraft can change its attitude to carry out its mission in case of failure, with the design method giving reasonable results.
| Original language | English |
|---|---|
| Pages (from-to) | 307-311 |
| Number of pages | 5 |
| Journal | Qinghua Daxue Xuebao/Journal of Tsinghua University |
| Volume | 50 |
| Issue number | 2 |
| Publication status | Published - Feb 2010 |
Keywords
- Angular momentum envelope
- Failure
- Micro control moment gyro (MCMG)
- Output torque
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