多高超声速飞行器双阶段协同俯冲制导律设计方法研究  

Research on design method of dual-stage cooperative dive guidance law for multiple hypersonic vehicles

作　　者：刘聪 刘俊彤 聂文田 刘凯 Liu Cong;Liu Juntong;Nie Wentian;Liu Kai(School of Aeronautics and Astronautics,Dalian University of Technology,Dalian 116024,China;School of Aeronautics and Astronautics,Zhejiang University,Hangzhou 310058,China;Beijing Institute of Aerospace Technology,Beijing 100074,China)

机构地区：[1]大连理工大学航空航天学院,大连116024 [2]浙江大学航空航天学院,杭州310058 [3]北京空天技术研究所,北京100074

出　　处：《战术导弹技术》2022年第4期41-49,共9页Tactical Missile Technology

基　　金：国家自然科学基金联合基金重点项目(NSFC U2141229)。

摘　　要：以高超声速飞行器协同攻击需求为研究背景,开展了下滑段-末段导引段“双阶段”协同制导方法研究。在下滑段,提出了以倾侧角符号切换控制位置偏差、以倾侧角幅值调节控制时间、以攻角调节控制能量的时间协同下滑制导方法,兼顾了高度/速度/位置/时间协同需求,为末段导引段实现高精度协同制导提供支撑。在末段导引段,通过引入末段初速度依赖偏置比例导引项,给出了改进的协同时间/角度末段导引律设计方法,兼顾了落角/时间协同需求。通过仿真,验证了双阶段协同俯冲制导律应用于高超声速飞行器协同制导问题的有效性。Based on the research background of the cooperative attack requirement of hypersonic vehicles,it is carried out the research on the"two-stage"coordinated guidance method of the gliding section and the terminal guidance section.In the gliding section,a time coordinated gliding guidance method is proposed,by using the sign of the tilt angle to switch the control position deviation,the amplitude of the tilt angle to adjust the control time,and the angle of attack to adjust the energy,which can support to realize highprecision coordinated guidance in the terminal guidance section.In the terminal guidance section,an improved design method of coordinated time/angle terminal guidance law is given by introducing the initial velocitydependent bias proportional guidance term of the terminal section,taking into account the needs of angle/time coordination.The simulation results verify the effectiveness of the dual-stage cooperative dive guidance law applied to the hypersonic vehicle cooperative guidance.

关 键 词：高超声速飞行器 双阶段制导 协同下滑制导 初速度依赖偏置导引 下滑段 末段导引 时间协同 

分 类 号：TJ76[兵器科学与技术—武器系统与运用工程]