直升机载空空导弹射后截获误差源研究  

Study on Error Source of Lock-on after Launch of Helicopter Borne AAM

作　　者：吕振瑞 任宏光[1] 王涛[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471099

出　　处：《弹箭与制导学报》2017年第1期169-172,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：航空科学基金(20150112002)资助

摘　　要：新一代直升机载空空导弹将采用复合制导体制,为提高导弹中末制导交接时刻的截获概率。文中对影响红外型直升机载空空导弹中末交接时刻截获概率的主要误差源进行了详细分析,在确定各个误差源范围的基础上,通过一种工程实际应用的数学模型对截获概率进行了仿真计算,进一步分析了误差源对截获概率的影响,为直升机载空空导弹武器系统的误差分配提供了重要理论依据。The new generation of helicopter borne air to air missile would adopt the composite guidance system, in order to improve the intercept probability at terminal guidance handover time. The main error sources of intercept probability befor the final handover time, which influenced infrared helicopter air to air missile were analyzed in detail. Based on determining the scope of the each error source, the intercept probability was analyzed through the mathematical model of practical engineering application, and the effect of error sources on intercept probability was further analyzed. It provided an important theoretical basis for the error distribution of helicopter borne air to air missile weapon system.

关 键 词：射后截获 截获概率 误差源 数学模型 直升机载空空导弹 

分 类 号：TJ013.2[兵器科学与技术—兵器发射理论与技术]