摘要
研究了挠性航天器高精度姿态控制问题。考虑被控对象的非线性、外部干扰以及挠性结构和惯量参数不确定性,设计了直接自适应姿态控制律。通过对经典直接自适应控制中参数自适应律的改进,进一步提高了姿态控制系统性能。该控制系统不仅考虑了挠性结构和惯量参数不确定性,同时考虑了系统非线性特性及外部干扰,且参考模型阶数小于实际被控对象阶数,控制系统结构简单。仿真结果验证了其有效性。
The flexible spacecraft direct adaptive control system is studied in this paper. By considering the nonlinearity, the disturbance and the uncertainties of flexible structures and inertia moment, a direct adaptive control law that only requires the attitude angle measurement is designed. The parameter adaptive law in classical directed adaptive control is improved, which contributes to the precision of attitude control enhanced. The order of reference model is less than that of the real system, therefore the structure of the control system is simpler. The simulation results validate the effectiveness of the proposed direct adaptive control algorithm.
出处
《航天控制》
CSCD
北大核心
2011年第5期35-39,47,共6页
Aerospace Control
关键词
挠性航天器
不确定性
姿态控制
自适应控制
高精度
Flexible spacecraft
Uncertainty
Attitude control
Adaptive control
High precision
