带落角落速约束的导弹虚拟期望落角末制导律

为解决导弹末制导阶段同时考虑落角和落速约束时带来的过载需求大、落速散布广的问题,提出一种基于虚拟期望落角的末制导律。首先,提出虚拟期望落角的概念,设计过渡函数降低末制导初期过载需求；然后,分析过渡函数各参数对落角、落速影响,设计预测-校正算法计算期望参数；为了提高预测效率与精度,使用深度神经网络离线训练弹道数据集。实际飞行中,基于扩展卡尔曼滤波在线辨识气动参数摄动,提高算法的适应性。蒙特卡洛仿真结果表明,所提出的算法能够降低末制导初期过载需求。在满足落角约束与位置精度的前提下,落速控制精度在±15 m/s以内。

Terminal Guidance Law for Missile with Speed and Angle Constraints Considering Virtual Expected Impact Angle

To solve the problems of large overload demand and wide distribution of impact speed caused by the consideration of both impact angle and impact speed constraints in the terminal guidance stage of a missile, a terminal guidance law based on virtual expected impact angle is proposed. Firstly, the concept of virtual expected impact angle is defined, and the transition function is designed to reduce initial the overload demand of terminal guidance. Then, the influence of transition function parameters on the impact angle and impact speed is analyzed, and the predictor corrector method is designed to calculate the expected transition function parameters. In order to improve the prediction efficiency and accuracy, the deep neural network is used to train the trajectory data set offline. In actual flight, the extended Kaman filter algorithm is used to identify aerodynamic parameter perturbation online to improve the adaptability. Monte Carlo simulation results show that the proposed algorithm can reduce the overload requirement at the initial stage of terminal guidance, and the impact speed accuracy is within ±15 m/s on the premise of satisfying the impact angle constraint and position accuracy.