BTT飞行器需要在环境与模型存在不确定性的情况下,满足攻角幅值、倾侧角转率等多约束条件,实现带终端角度约束的高精度制导.针对该问题提出了一种多目标最优鲁棒制导方法.建立含干扰输入描述的制导律设计模型,将制导问题转化为鲁棒制导律设计与制导律参数多目标综合优化两个子问题.采用基于L2性能指标的鲁棒控制方法设计制导律,将其中的参数作为待优化变量.建立多目标综合优化模型,基于遗传算法,优化制导律参数.数学仿真结果表明,提出的制导方法可以满足带终端角度约束的多目标制导任务要求.%In order to fulfill high precision guidance with terminal angular constraint for missile under environment and model uncertainties and other multiple constraints, a guidance approach was proposed. Robust guidance law design and guidance law parameters optimization were solved separately as two sub-problems. Geometry relationship between missile and target was derived and robust guidance law based on L2 gain performance theory was presented. The guidance law parameters were optimized using genetic algorithm with the weighted square sum of terminal angular error, position error and control variables as the optimal performance function. Simulation results show that the proposed approach is an effective way to design guidance law with terminal angular constraint while satisfying multiple objectives.
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