- 期刊
- OpenAccess
Attitude Control Design for an NSPO Microsatellite
並列摘要
An attitude control subsystem for an National Space Program Office (NSPO) microsatellite is conceptually designed to meet the weight and power constraints. Attractive features of the proposed design include: a) a control scheme for initial attitude acquisition, which provides a fully autonomous attitude hold, no duration limit and adequate attitude for power generation and b) a feasible implementation for a microsatellite which has mission demands such as practical weight and power constraints. The proposed control schemes for the two control modes and the spacecraft attitude dynamics are analyzed to demonstrate the satisfaction of the designated mission goals.
延伸閱讀
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