高超声速飞行器非线性自适应姿态控制

摘要

分析了影响高超声速飞行器姿态运动的关键要素和不确定性,提出了包括动压关联输出变换、非线性黄金分割自适应控制律Ⅲ、积分器以及可选择的前馈控制在内的一种高超声速飞行器姿态控制新方案,解决了飞行过程中气动动压快速变化对姿态控制系统稳定性和控制精度影响的问题,提高了系统对关键参数不确定性如气动参数偏差、气动阻尼系数偏差、大气密度偏差、惯量偏差以及初始条件偏差的鲁棒性和适应性;所提方案用于高超声速飞行器再入过程高度、速度快速变化导致动压急剧变化的下压段的姿态控制系统设计中.仿真结果表明,在标称和多种偏差组合条件下,性能指标满足要求,控制量满足约束条件.%The key factors and uncertainties that affect the attitude movement of a hypersonic vehicle are analyged and a new scheme of hypersonic vehicle attitude control is proposed,including pressure correlation output transformation,nonlinear golden section adaptive control law Ⅲ,integrator and optional feedforward control.The new scheme solves the influence of the rapid change of aerodynamic pressure on the stability and control precision of the attitude control system during flight,and improves the robustness and adaptability of the critical parameters of the system such as aerodynamic parameter deviation,aerodynamic damping coefficient deviation,atmospheric density deviation,inertia deviation and initial conditional deviation.The new scheme is applied to the attitude control of the dive phase of a hypersonic vehicle with the rapid variance of altitude and velocity,resulting in sharp variance of dynamic pressure.The mathematical simulation shows that the performance index satisfies the requirement and the control output satisfies the restriction.