摘要
针对攻击型临近空间飞行器的跳跃机动突防对常规拦截导弹提出的挑战,本文首先建立了视线坐标系下的三维弹-目相对运动方程,引入目标跳跃幅度变化率估计目标跳跃机动的能力,基于滑模变结构控制理论,设计了随弹-目距离和目标跳跃幅度变化率自适应调节的滑模趋近律,推导了视线坐标系下导弹的三维制导律。其次,采用轨控直接力控制技术,设计了直接力/气动力复合控制的分配方案。仿真结果表明:采用该制导律与控制策略的拦截弹能够精确拦截高速、大机动目标,同时拦截弹弹道平缓,需用过载和能量消耗均较小。
A nonlinear guidance law is proposed to confront the challenge of offensive near-space vehicles. Firstly,3-D relative motion equations of missile and target are built in sight coordinate system.The gradient of target jump range is introduced to estimate its maneuverable capability. An adaptive sliding mode reaching law varying with the gradient of target jump range and the distance between missile and target is designed. 3-D guidance law in sight coordinate system is got based on sliding mode control theory. Secondly,the allocation strategy of reaction-jet / aerodynamic multi-control is designed and trajectorycontrol lateral-jets control technology is used in the terminal phase. Simulation results show that interceptor using this guidance law and control strategy can hit hypersonic and high maneuvering target accurately.Meanwhile the flight ballistics is smoother and required overload is lesser as well as energy consumption.
出处
《航空兵器》
2015年第5期23-27,共5页
Aero Weaponry
基金
航空科学基金项目(20140152002)
南京航空航天大学研究生创新基地(实验室)开发基金
中央高校基本科研业务费专项基金项目(kfjj201458)
