反吸气式临近空间飞行器空基拦截弹制导律设计  

Design of air-based interceptor's guidance law for airbreathing hypersonic vehicle in near space

作　　者：于志鹏[1,2,3] 陈刚[1,3] 李跃明[1,3] 

机构地区：[1]西安交通大学机械结构强度与振动国家重点实验室,陕西西安710049 [2]中国西昌卫星发射中心,海南文昌571300 [3]陕西省先进飞行器服役环境与控制重点实验室,陕西西安710049

出　　处：《飞行力学》2017年第1期66-69,74,共5页Flight Dynamics

基　　金：国家自然科学基金资助(11272005;11511130053);中央高校基本科研业务费项目资助(2014xjj126)

摘　　要：临近空间高超声速飞行器的出现和应用,为传统防空系统提出了新的挑战。提出了一种反临近空间高超声速吸气式飞行器巡航段空基拦截方案,并设计了基于末角约束比例导引法的中制导律和空基拦截弹复合制导律。仿真结果表明,改进末角约束比例导引法能充分利用拦截弹中制导段过载承受能力,有效地加快了拦截弹达到期望末视线角的速度,改善了中末交班性能;所设计的拦截方案能够对典型机动目标实施有效拦截。The emergence and application of the near space hypersonic vehicle has brought new challenges to the traditional air defense systems. An air-based interception scheme was proposed for the airbreathing hypersonic vehicle in the cruse phase. Based on the terminal angle constraint proportional navigation method,the mid-course guidance law and the compound guidance law for the air-based interceptor missile were designed. Simulation results show that the improved angle-restrained proportional navigation method can fully utilize the overload capacity of the guided interceptor,and effectively accelerate the speed of the interceptor to reach the desired angle of the line-of-sight,and obviously improve the mid-end shift performance. The proposed intercepting scheme can effectively intercept the typical maneuvering targets.

关 键 词：临近空间 复合制导律 比例导引法 空基拦截 

分 类 号：V448.23[航空宇航科学与技术—飞行器设计]