助推段拦截导弹制导律的设计与仿真分析  

Design and Simulation Analysis of Guidance Law for Boost Phase Interceptor Missile

作　　者：张旭 曾鹏 李旭[1] 郑学合 薛建恒 王超 Zhang Xu;Zeng Peng;Li Xu;Zheng Xuehe;Xue Jianheng;Wang Chao(Beijing Institute of Electronic System Engineering,Beijing 100854,China;China Changfeng Mechanics and Electronics Technology Academy,Beijing 100854,China)

机构地区：[1]北京电子工程总体研究所,北京100854 [2]中国长峰机电技术研究设计院,北京100854

出　　处：《系统仿真学报》2025年第2期335-344,共10页Journal of System Simulation

摘　　要：助推段拦截时间窗口极短,要求导弹须具备高速、高加速能力,同时由于目标弹道导弹在助推阶段仍在加速,要求拦截导弹的制导方案需具备应对目标机动的能力。通过分析助推段拦截导弹的特性,建立弹道仿真模型,并依据拦截导弹飞行全过程要求的制导机制性能,详细设计助推段拦截导弹在初制导、中制导、末制导阶段下的制导律,研究不同制导方案对导弹拦截性能的影响,并分析了不同导弹最大速度的拦截效果。结果表明:助推段拦截导弹的中制导采用预测命中点导引律能够降低视线角速率,使弹道更为平直,末制导采用修正比例导引律可以降低需用过载,提高拦截性能;能量越高的导弹,其速度特性、飞行性能越高,同时所需拦截时间越短,拦截效果越好。The intercept time window in the boost phase is very short,which requires the missile to have high speed and high acceleration capability,at the same time,because the target ballistic missile is still accelerating in the boost phase,the guidance scheme of the interceptor missile needs to have the ability to cope with the characteristics of the booster phase interceptor missile.The trajectory simulation model is established,and the guidance law of the boost phase interceptor missile in the initial guidance,mid-guidance and final guidance stage are designed in detail according to the performance of the guidance mechanism required by the interceptor missile during the whole flight process.The influence of different guidance schemes on the interceptor performance is studied,and the interception effect of different maximum velocities of the missile is analyzed.Experimental results show that the guidance law of forecast point of impact can reduce the line-of-sight rate and make the trajectory flatter,and the modified proportional guidance law can reduce the required overload and improve the intercepting performance.At the same time,the higher the energy of the missile,the higher the speed characteristics,the higher the flight performance,and the shorter the interception time required,the better the interception effect.

关 键 词：弹道导弹防御 助推段拦截 制导律设计 拦截性能 弹道仿真 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术] TJ765.4[自动化与计算机技术—计算机科学与技术]