空基动能拦截弹制导控制系统建模与仿真  

Modeling and Simulation of Guidance and Control System of Air-Borne Kinetic Energy Interceptor

作　　者：肖增博[1] 雷虎民[1] 张蓬蓬[2] 冯璐 

机构地区：[1]空军工程大学导弹学院 [2]中国空空导弹研究院 [3]94897部队

出　　处：《航空兵器》2012年第2期9-15,共7页Aero Weaponry

基　　金：航空科学基金(20090196005)

摘　　要：为研究用于弹道导弹助推段拦截的空基动能拦截弹的制导控制系统,探讨了弹道导弹助推段拦截的作战过程,建立了弹道导弹助推段飞行的弹道模型;根据弹道导弹在助推段的飞行特点,建立了动能拦截弹制导控制系统模型,其中包括拦截弹结构模型、动力学与运动学模型、相对运动模型、传感器测量模型、复合制导模型和直接力/气动力控制模型。在Matlab/Simulink环境下开发了弹道导弹助推段拦截的数字仿真系统,并对仿真结果进行了分析。仿真结果验证了模型的合理性,可为空基拦截弹制导控制系统的设计提供参考。To study the guidance and control system of air-borne kinetic energy interceptor （KEI）, the engagement process for boost phase ballistic missile interception is explored, and the trajectory model of a ballistic missile during the boost phase is established. According to the boost phase flight characteristics of ballistic missile, the guidance and control system models of KEI are constructed, including the structural model, the dynamic and kinetic model, the relative movement model, the measurement model, the compound guidance model and the direct force/aerodynamic force control model. Under the environment of Matlab/Simulink, the digital simulation system is developed. The simulation results prove the fea- sibility and practicability of the model.

关 键 词：弹道导弹 助推段拦截 空基动能拦截弹 制导控制 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] V448.2[航空宇航科学与技术—飞行器设计]