发射后截获制导律研究  

Lock-on-after-Launch Guidance for Air-to-Air Missile

作　　者：唐成师[1] 侯明善[1] 葛志远[1] 罗欢[1] 

机构地区：[1]西北工业大学自动化学院,西安710072

出　　处：《火力与指挥控制》2013年第2期55-58,共4页Fire Control & Command Control

基　　金：航空基金资助项目(2008ZC53021)

摘　　要：研究了发射后截获制导律设计问题。为了保证导引头顺利截获目标,提出了一种包含离轴角增益控制比例导引项、变系数追踪项和导弹纵向加速度补偿项的组合制导律。比例项主要稳定视线角速度,保证弹目距离收敛;变系数追踪项控制导弹前置角,能有效克服前置角震荡,增大导引头视场角截获概率并保证导引头尽早截获目标;导弹纵向加速度补偿项消除弹体纵向加速度变化对制导的不利影响。仿真验证结果表明,提出的制导律在大离轴角发射条件下能够满足发射后截获要求,简单易行。A combined midcourse guidance law is proposed for lock-on-after-launch air-to-air missies. The guidance law has three parts, including Proportional Navigation with navigation ratio adjusted by off-boresight angle, the pursuit term with varying coefficient and the compensation of missile longitudinal acceleration. The PN is used to stablize the line of sight angular velocity when large off-boresight angles occur. The pursuit guidance with varying coefficient can quickly reduce the missile off-boresight angle and make it stable, thereby the condition for the seeker＇s angle interception can be achieved as early as possible. The third part is used to eliminate the adverse effect of missle＇s longitudinal acceleration on guidance performance in the initial phase. The simulation results show that the proposed guidance law is very effective in large off-boresight angle launch conditions.

关 键 词：发射后截获 组合制导 比例导引 追踪导引 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]