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针对高超声速飞行器俯冲段铰链力矩过大问题,提出一种考虑终端落角和落点约束的铰链力矩最优俯冲制导方法。首先通过瞬时平衡假设建立铰链力矩与过载的线性关系,以过载量间接表征铰链力矩;其次以过载为控制量,将俯冲段相对运动方程化为显含过载的状态空间形式;最后,利用最优控制理论,以过载最小为性能指标,引入伪控制量,求解出过载最小的解析最优制导律。仿真结果表明该方法能高精度的满足终端落角和落点约束,并且过载峰值降低,铰链力矩最大值显著减小。
In order to solve the problem of hypereutectic hypersonic vehicle hinge moment, this paper proposes a method of optimal moment of subduction guidance considering the terminal falling angle and falling point constraints. Firstly, the instantaneous equilibrium assumption is used to establish the linear relationship between the hinge moment and overload, and the hinge torque is indirectly characterized by the overload. Secondly, the overload is used as the control variable to convert the relative motion equation of the dive section into the state space form that contains overload. Finally, Control theory, the minimum overload as the performance index, the introduction of pseudo-control volume, solve the minimum overload analysis of the optimal guidance law. The simulation results show that the method can meet the terminal falling angle and falling point constraints with high precision, and reduce the overload peak, the maximum hinge torque significantly reduced.