面向可打击区域的高超声速飞行器制导控制一体化方法研究
Research on Integrated Guidance and Control Method for Hypersonic Vehicles for Striking Area
赵良玉 1时皓铭 1王建华 2崔磊3
作者信息
- 1. 北京理工大学 宇航学院,北京 100081
- 2. 航天工程大学 宇航科学与技术系,北京 101416
- 3. 天津大学 电气自动与信息工程学院,天津 300072
- 折叠
摘要
针对高超声速飞行器制导和控制系统分离设计方法的不足,提出通过制导控制一体化设计提升其可打击区域的方法.首先,在建立高超声速制导控制一体化模型的基础上,揭示了其通过控制弹体坐标系与地面坐标系的牵连加速度来跟踪制导指令的工作原理.其次,通过典型弹道的数值仿真,对比分析了制导控制一体化设计相较于分离设计的控制信号差异.最后,通过确定制导控制分离设计及一体化设计的高超声速飞行器可打击区域的方式,从大样本仿真角度体现制导控制一体化的优势.结果表明,制导控制一体化设计可以放宽对可用过载的需求且有助于提升高超声飞行器的可打击区域.
Abstract
Aiming at the shortcomings of the separation design of guidance and control systems,a method of improving the striking area through integrated design of guidance and control is proposed.Firstly,based on the establishment of an integrated guidance and control model for hypersonic vehicle,the working principle which tracks acceleration commands by controlling the implicated acceleration between the body coordinate sys-tem and the ground coordinate system is revealed.Secondly,through numerical simulation of typical trajecto-ries,the ability of integrated guidance and control design to reduce required overload compared to separate de-sign is compared and analyzed.Finally,by determining the separation and integration design of guidance and control in the striking area of hypersonic vehicle,the advantages of integrated guidance and control are reflected from the perspective of large-scale simulation.The results indicate that the integrated guidance and control can relax the demand for available overload and improve the striking area of hypersonic vehicle.
关键词
制导控制一体化/大样本仿真/可打击区域/高超声速飞行器/过载约束Key words
integrated guidance and control/large-scale simulations/striking area/hypersonic vehicles/overload constraint引用本文复制引用
基金项目
国家自然科学基金(12072027)
河南省通用航空技术重点实验室开放基金(ZH-KF-230201)
出版年
2024
国家科技期刊平台
NSTL
万方数据