再入飞行器大攻角飞行时的姿态控制律设计.

When a reentry vehicle flying with high angle of attack, there is always a failure of the yaw rudder. And the pitch rudder and the roll rudder are also easy to be saturated, even with a small roll angular speed. To solve this problem, an anti-windup attitude controller is presented under the failure of the yaw rudder. In the design process, based on the time-scale separation, the attitude model is separated into a fast-loop subsystem and a slow-loop subsystem firstly. Secondly, a sliding mode controller, which is differentiable and with finite-time convergence, is designed for the slow-loop subsystem through using a novel high-order sliding mode control theory. For the fast-loop subsystem, an adaptive hierarchical sliding mode controller with anti-windup capacity is designed through employing the sliding mode control theory and adaptive control theory. Finally, the presented controller is verified through simulation, and the results show that the controller has a good anti-windup capability under the failure of the yaw rudder caused by high angle of attack. [ABSTRACT FROM AUTHOR]