高超声速飞行器再入姿态鲁棒控制

Robust Attitude Control of Hypersonic Vehicles in Reentry Phase

中文关键词  姿态控制  再入  气动参数不确定性  自适应  鲁棒性  控制分配  

英文关键词  attitude control  reentry  aerodynamic parameter uncertainties  adaptive control  rubustness  control allocation  

中文摘要

      本文针对气动参数和惯性参数不确定性, 同时考虑反作用控制系统(RCS)参与控制, 设计高超声速再入飞 行器的鲁棒自适应控制器. 根据奇异摄动理论将整个控制系统分为快、慢两个回路分别进行设计, 将各回路的不确 定参数写成矢量的形式, 并用自适应估计器进行在线估计, 从而使得控制器实现在线自适应调整. 利用非线性干扰 观测器来处理控制系数矩阵的不确定性部分. 提出一种改进的控制分配权重函数, 并将总控制力矩分配到气动舵 面偏角指令和RCS 所需提供的控制力矩指令. 利用Lyapunov稳定性理论来分析整个闭环系统的稳定性. 最后, 通过 仿真验证该控制方案能够有效抑制不确定参数引起的干扰.

英文摘要

      An attitude-tracking controller involving a reaction control system (RCS) is designed for the hypersonic reentry vehicle with uncertainties in the aerodynamic parameters and rotational inertia coefficients. The whole control system is partitioned into the fast and slow loops according to the singular-perturbation principle. In each loop, the uncertain parameters are lumped into a vector for the convenience of online estimation by constructing an adaptive estimator. To enhance the robustness of the attitude-tracking controller, a nonlinear disturbance observer is introduced to estimate the uncertainties appeared in the control-coefficient matrix. An improved control-allocation strategy is also proposed to efficiently assign the total control moment to the pneumatic rudders and RCS, respectively. The stability of the closed-loop system is proved by means of Lyapunov stability theory. The numerical simulation shows that the proposed control method is effective in suppressing the disturbances caused by parameter variations.