【作者】 姚郁； 毕永涛； 王宇航；

【Author】 Yu Yao,Yongtao Bi,Yuhang Wang Control and Simulation Center,Harbin Institute of Technology,Harbin 150080,China

【机构】 哈尔滨工业大学控制与仿真中心；

【摘要】 针对大气层内直接侧向力控制拦截导弹末段修正能力分析问题,建立了姿控式直接侧向力控制拦截弹和轨控式直接侧向力控制拦截弹数学模型。考虑了不同飞行条件下,导弹过载响应时间、脉冲发动机消耗量以及直接侧向力启控剩余飞行时间对这两种拦截导弹末段修正能力的影响,给出了姿控式拦截弹和轨控式拦截弹在末制导末段跟踪阶跃过载指令时横向修正距离的表达式。最后考虑直接侧向力启控剩余飞行时间,仿真分析了这两种导弹在典型配置条件下能够充分发挥各自修正能力的作战空域。更多还原

【Abstract】 In order to analyze the divert ability of atmospheric interceptors controlled by lateral jet thrusters,the models of two kinds of atmospheric interceptors are established:one is with attitude control thrusters,the other is with divert thrusters.Considering overload response time,consumptions of thrusters and time-to-go,maximal terminal divert distances are formulated for tracking a step input under several flight conditions.Finally,based on the above results, considering two types of missiles with typical parameters,their corresponding battle skies,where their divert abilities can be utilized,are given.更多还原