基于数据驱动方法的撞击时间和角度约束指导法

Wenjie Cao, Jia Huang, Sijiang Chang
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引用次数: 0

摘要

为了提高飞行器的打击效率和杀伤力,有必要考虑飞行器在撞击时间和角度限制方面的制导法则。在本研究中,利用数据驱动方法和比例导航制导,分两个阶段提出了一种新颖而简单的撞击时间和角度控制制导法则,该法则与飞行时间和小角度近似值无关。首先,为第二阶段设计了基于比例导航制导的撞击角控制制导法则。其次,从冲击角控制制导仿真的各种初始条件中获取输入和输出数据集,从而建立映射网络。利用神经网络技术,为第一阶段的撞击时间控制构建一个可输出飞行中理想飞行路径角度的映射网络模型。当飞行路径角误差收敛为零时,所提出的撞击时间和角度控制制导法则将简化为比例导航制导法则。仿真结果表明,所提出的制导法则在各种条件下(包括协同攻击)都能提供出色的性能,并且与冲击时间和角度控制制导法则相比,具有更好的加速性能和更少的控制能量。本研究的成果有望对现有文献中总结的解决撞击时间和角度控制制导问题的各种范式的探索起到补充作用。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Data-Driven-Method-Based Guidance Law for Impact Time and Angle Constraints
To increase the hit efficiency and lethality of a flight vehicle, it is necessary to consider the vehicle’s guidance law concerning both impact time and angle constraints. In this study, a novel and straightforward impact time and angle control guidance law that is independent of time-to-go and small angle approximations is proposed with two stages using a data-driven method and proportional navigation guidance. First, a proportional navigation guidance-based impact angle control guidance law is designed for the second stage. Second, from various initial conditions on the impact angle control guidance simulation with various initial conditions, the input and output datasets are obtained to build a mapping network. Using the neural network technique, a mapping network model that can output the ideal flight path angle in flight is constructed for impact time control in the first stage. The proposed impact time and angle control guidance law reduces to the proportional navigation guidance law when the flight path angle error converges to zero. The simulation results show that the proposed guidance law delivers excellent performance under various conditions (including cooperative attack) and features better acceleration performance and less control energy than does the comparative impact time and angle control guidance law. The results of this research are expected to supplement those exploring various paradigms to solve the impact time and angle control guidance problem, as concluded in the current literature.
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