多约束下铰链力矩最优俯冲制导方法

Multi-Constrained Diving Guidance with Optimal Hinge Moment

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。

To solve the problem of high hypersonic vehicle hinge moment in dive phase, terminal impact point and falling angle constrained diving guidance method with minimum hinge moment is proposed. First of all, by building the linear relationship of hinge moment and overload by transient equilibrium assumption, hinge moment is described indirectly by overload. Secondly, the state space equation of relativity motion is established by selecting overload as control variable. Finally, based on optimal control theory with the optimal index of minimum overload and the pseudo control variable involved, the optimal analytic form guidance law is inferred with minimum overload. The simulation result shows that terminal impact point and falling angle constraints with high precision can be achieved, maximum overload can be reduced and the hinge moment can be decreased obviously by using this algorithm.