空基动能拦截弹寻的制导系统性能分析

摘要

This paper investigated the modeling and simulation of guidance system of airborne kinetic energy interceptor ( KEI) , with respect to the interception of boost phase ballistic missile .According to the requirement of guidance system for boost phase intercept , the homing guidance model and adjoint model are established .By means of a number of simulations , the guidance performance is analyzed which influenced by acceleration saturation , initial aimpoint displacement , trajectory-control lateral-jets, target maneuver and terminal guidance time .The differences between augmented proportional navigation ( APN) and traditional proportional navigation ( PN) are also analyzed and compared .The analysis results can pro-vide a basis for preliminary design on KEI guidance system .%针对弹道导弹助推段的拦截问题，对空基动能拦截弹的寻的制导系统进行建模和仿真分析。分析了弹道导弹助推段拦截对拦截弹制导系统的需求，建立了寻的制导系统模型和伴随模型。通过大量仿真实验，研究了加速度饱和限制、目标位置初始误差、轨控直接侧向力、目标机动以及末导时间等各种因素对拦截弹制导性能的影响，比较了比例导引与增强型比例导引的性能差异。所得结果可为空基动能拦截弹制导系统的初步设计提供参考。