高超声速飞行器操纵性/控制律一体化设计方法

Integrated design method for manipulability and control law of hypersonic vehicle

高超声速飞行器主要飞行阶段包括助推分离段、巡航段和下降段,在分离段操纵面的任务是快速抑制分离扰动,而巡航段主要用于高精度姿态控制。针对分离段和巡航段对舵面操纵性要求差别较大的特点,本文探讨从满足控制要求的角度对操纵面尺寸进行优化设计的方法,即操纵性/控制律一体化设计。采用最优控制方法对飞行器自动驾驶仪增益进行优化,并基于多目标遗传算法的并行子空间优化方法,得到了高超声速飞行器最优舵面外形尺寸和相应的控制律。仿真结果表明,最优舵面在分离段能够快速抑制分离扰动对飞行器姿态的影响,并将飞行器姿态迅速调整到发动机点火窗口;在巡航段能够快速抑制阵风干扰对飞行器姿态的影响,稳定飞行器姿态,为高超声速飞行器操纵性设计提供了依据。

The main flight phases of a hypersonic vehicle include propulsion-assisted separation phase,cruise phase and descent phase. In the separation phase,the task of control surface is to suppress the separation perturbation of the hypersonic vehicle quickly,but in the cruise phase,the task is to achieve the high-precision control of its attitude. During these two phases,the requirements for the manipulability of the rudder surface are rather different. To satisfy the control requirements,this paper explores the control surface dimension optimization and design method,namely the manipulability and control law integrated design method. It uses the optimal control method to optimize the gains of the autopilot of the hypersonic vehicle and then optimizes the boundary dimensions of its optimal rudder surface and its control law with the parallel subspace optimization method of the multi-objective genetic algorithm.The simulation results show that,during the separation phase,he optimal rudder surface can quickly suppress the influence of separation perturbation on the attitude of the hypersonic vehicle and quickly adjust its attitude to the engine ignition window and that,during the cruise phase,the optimal rudder surface can quickly suppress the influence of gust interference on the attitude and thus stabilize it. This exploration sheds light on a hypersonic vehicle＇s manipulability design.