攻击角度约束的直升机载空空弹滑模中制导律  

Midcourse Sliding-Moding Guidance for Air-to-Air Missile on Helicopter with Intercept Angle

作　　者：杨杨[1] 梁晓庚[1,2] 吴震[1] 张金鹏[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009 [2]西北工业大学自动化学院,西安710072

出　　处：《四川兵工学报》2015年第6期41-44,共4页Journal of Sichuan Ordnance

基　　金：航空科学基金(2013ZC12)

摘　　要：基于虚拟目标的概念,设计了一种直升机载空空导弹滑模中制导律;首先,针对直升机载空空导弹在中末制导交接过程中,导弹低空飞行存在地物背景干扰及坠地等问题,提出了一种基于虚拟目标概念的弹道规划方案并给出了虚拟目标的计算公式;其次,基于变结构理论,选择导弹与虚拟目标的脱靶量及终端角度约束作为滑模面设计了制导律;最后,在MATLAB环境下进行仿真分析,并与最优制导律做比较,结果表明:提出的制导律具有更快的收敛速度,具有一定的工程实际意义,且该制导律易于理解,便于工程应用。A midcourse virtual target-based guidance was proposed to be applied for air-to-air missile on helicopter. First, the virtual target-based vertical trajectory programming technology was put forward to set- tle the long range low-altitude flight collision and the ground clutter abatement in the course of handover of guidance from the midcourse the terminal. Second, the miss distance between the missile and the virtual target which was derived by a new method were chosen as sliding mode and then the sliding mode control theory was employed to design the guidance law. Finally, representative simulation with MATLAB （Simu- link） results and their analysis show preliminarily that the new guidance not only meets the requirement, but also converges quickly compared with the optimal guidance law. Furthermore this midcourse guidance law is easy to realize in engineering.

关 键 词：直升机载空空弹 中制导律 攻击角度 滑模变结构控制 虚拟目标 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]