大气层内动能拦截器微型脉冲发动机点火算法  

Ignition Algorithm of Micro Pulse Engines for the Endo-atmosphere Kinetic Kill Vehicle

作　　者：董杰[1] 王法栋[1] 刘宗福[1] 

机构地区：[1]中国人民解放军92785部队

出　　处：《导弹与航天运载技术》2013年第2期46-49,共4页Missiles and Space Vehicles

摘　　要：为提高拦截精度并减少消耗数量,对大气层内末端飞行动能拦截器的微型脉冲发动机点火控制进行分析和研究。给出了弹体滚转角速度效能公式,优化滚转圈数;依点火时刻弹体是否滚转,从直接力响应时态和滚转扇扫点火算法分析影响耗散数量的因素;建立直接力环节被控模型,采用补偿偏差方法修正偏差。仿真结果表明,该控制策略能保证理想动态响应,节省需点火的微型脉冲发动机数量。In order to improve the intercept precision and reduce the consumption, the micro pulse motor＇s ignition control for kinetic kill vehicle during the terminal flight in the atmosphere was analyzed and researched. The efficiency formula of rolling missile＇s angular velocity was proposed to optimize the number of turns. Based on whether the missile body was rolling or not, the influence factor on consumption was analyzed from the direct thrust＇s response tense and the sector scanning ignition algorithm of rolling. With the controlled model for the direct force, deviation compensation method was applied to reduce the error. The simulation results showed that the control strategy can ensure the ideal dynamic response and reduce the quantity of micro pulse motors that needed to be ignited.

关 键 词：动能拦截器 微型脉冲发动机 点火算法 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]