落角约束下的高超声速变体飞行器末制导方法
Terminal guidance method with impact angle constraints for hypersonic morphing vehicle
万泱泱 1郭杰 1王浩凝 1葛健豪 1唐胜景1
作者信息
- 1. 北京理工大学宇航学院,北京 100081
- 折叠
摘要
针对高超声速变体飞行器末段制导问题,提出了一种基于比例控制和预测-校正思想的末制导方法,在满足落角约束的条件下,提升飞行效果.以高超声速飞行器动力学方程为基础、三维偏置比例导引法为框架,构建末制导指令的数学表达.通过实时预测飞行器落角与目标值的偏差,在线校正导引律的偏置项.开展标称条件和任务变更条件下的仿真测试,并在扰动条件下完成蒙特卡洛打靶仿真试验.仿真结果表明,该末制导方法具有较高的制导精度和较强的抗扰动能力,且具有一定的自主性,能够适应任务变更的情况;该制导律发挥了变体飞行器的优势,相比传统飞行器具有更好的末段飞行性能.
Abstract
Aimed at solving the terminal guidance problem of hypersonic morphing vehicles,a ter-minal guidance method based on proportional control and predictor-corrector concept is proposed,which can enhance the flight effect under the constraints of impact angle.Based on the dynamic e-quations of hypersonic flight vehicles,the mathematical representation of guidance command was constructed with the framework of three-dimensional biased proportional guidance method.The bias terms of the guidance law were corrected online by predicting the deviation of the impact angle and target angle in real time.Simulation tests under nominal and mission-change conditions were carried out.Targeting simulation experiments were completed under Monte Carlo disturbance conditions.The simulation results show that the terminal guidance method has high accuracy and strong anti-dis-turbance capability.It has autonomy and can adapt to the mission-change condition.The guidance law takes advantage of the morphing vehicles,which has a better terminal flight effect compared with traditional vehicles.
关键词
高超声速变体飞行器/三维偏置比例导引/预测-校正法/落角约束Key words
hypersonic morphing vehicle/three-dimensional biased proportional guidance/predic-tor-corrector method/impact angle constraints引用本文复制引用
出版年
2024
NETL
NSTL
万方数据