摘要
This paper proposes a new gyro and star sensor fault diagnosis architecture that designs two groups of cascade H∞ optimal fault observers using LMI for spacecraft attitude control systems.The basic idea of the approach is to identify the gyro fault to good effect first and then makes a further diagnosis for the star sensor based on the former.The H∞ optimal fault observer in design has the robustness with respect to model uncertainties and diagnosis uncertainties.Its robustness to unknown inputs is as a special study in frequency domain.Finally,simulation results demonstrate the effectiveness and feasibility of the proposed control algorithm.
This paper proposes a new gyro and star sensor fault diagnosis architecture that designs two groups of cascade H∞ optimal fault observers using LMI for spacecraft attitude control systems. The basic idea of the approach is to identify the gyro fault to good effect first and then makes a further diagnosis for the star sensor based on the former. The H∞ optimal fault observer in design has the robustness with respect to model uncertainties and diagnosis uncertainties. Its robustness to unknown inputs is as a special study in frequency domain. Finally, simulation results demonstrate the effectiveness and feasibility of the proposed control algorithm.
基金
Sponsored by the National Natural Science Foundation of China(Grant No. 60774062)
the CAST Innovation Funding Project(Grant No. 20090604)
