一种适于典型发动机故障的自适应制导方法  

An adaptive guidance method of the typical engine fault

作　　者：王继平[1] 魏诗卉[1] 林红斌[1] 王安民[1] 

机构地区：[1]第二炮兵装备研究院,北京100094

出　　处：《固体火箭技术》2015年第3期308-313,共6页Journal of Solid Rocket Technology

基　　金：宇航智能控制技术国家级重点实验室开放基金

摘　　要：为尽可能避免导弹固体发动机故障引发全弹自毁造成飞行失败,针对固体发动机喷管和喉衬故障常出现在关机附近的情况,采用子级弹体自毁方案,提出一种适用此方案的自适应制导方法,对导弹上面级发动机能量进行最优管理,在能量充足时确保导弹仍能成功完成打击任务。仿真结果表明,该自适应制导能量管理有效,方法误差小,证明了方法的正确性。Self-destruction of whole missile and flight failures resulted from by the fault of the solid engine of missile should be avoided to the largest extent.In the paper,for the nozzle and throat insert fault of the solid engine,a safety self-destruction project of the missile substage body and the adaptive guidance method for it were put forward,by optimization of energy management for the upper stage engine,which ensue that the missile can still accomplish the impact task when the engine energy of the upper stage engine is enough.The results show the energy management of the adaptive guidance method is valid and there is little error by simula-tion calculation.

关 键 词：安全自毁 自适应制导 发动机能量 

分 类 号：V448[航空宇航科学与技术—飞行器设计]