再入飞行器大攻角飞行时的姿态控制律设计  

The Attitude Controller Design for the Reentry Vehicle Flying with High Angle of Attack

作　　者：成高[1] 刘满国[1] 李宪强 张翔[1] 李苑青[1] 

机构地区：[1]西安现代控制技术研究所,西安710065 [2]北京空间技术研制试验中心,北京100094

出　　处：《宇航学报》2017年第8期847-854,共8页Journal of Astronautics

摘　　要：再入飞行器大攻角飞行时,会造成方向舵失效,且较小的滚转角速度,就可能导致舵偏指令饱和,对此,本文设计了一种在方向舵失效情况下的抗饱和姿态控制律。该控制律首先基于时标分离假设,将再入飞行器大攻角飞行时的姿态运动模型分解成快、慢回路子系统,然后采用新型的高阶滑模控制律,设计出了一种有限时间收敛且连续可导的慢回路控制器;针对快回路子系统,结合分层滑模控制理论和自适应控制理论,设计了具有抗输入饱和功能的自适应分层滑模控制器。对以上控制器进行仿真验证,结果表明该控制律在大攻角飞行造成偏航舵失效情况下,具有良好的抗饱和姿态控制能力。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.

关 键 词：再入飞行器 大攻角 滑模控制 抗饱和 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]