惯导/数据链组合导航技术在诱饵导弹中的应用  

Integrated SINS/Data Link Navigation Technology Applied to Decoy Missiles

作　　者：温琦[1] 陈凯[1] 闫杰[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《弹箭与制导学报》2016年第3期4-7,14,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家自然科学基金(90816027);航空科学基金(20135853037);航天技术支撑基金(2013-HT-XGD-15)资助

摘　　要：针对作战飞机在突入敌方防空范围时,会面临地面防空武器和空空导弹拦截的问题,提出诱饵导弹基于惯导/数据链组合导航的编队飞行模式来提高飞机生存概率。考虑该编队由领机和诱饵导弹组成,诱饵导弹通过伪距测量,利用卡尔曼滤波器,得到自身的精确相对位置。采用编队飞行轨迹发生器产生运动轨迹,通过系统仿真表明:纬度和经度误差均小于5 m(1σ),高度误差小于20 m(1σ)。仿真结果证明了该方法的有效性与可行性。Since combat aircrafts are faced with ground-air defense weapons and air-to-air missile interception when assaulting enemy anti-aircraft range, a method using decoy missiles9 formation flight was proposed, which is based on integrated SINS/data link navigation, to increase combat aircrafts ’ survival probability. Considering the formation is composed of leader fighters and decoy missiles, decoy missiles obtain pseudo range measurements from data link. Combining with Kalman filtering method, decoy missiles get its precise relative position. The trajectory is generated by the formation trajectory generator, and the results of digital simulation show that the latitude and longitude error are less than 5 m（ 1σ） , and the height error is less than 20 m（ 1σ）. Effectiveness and feasibility of the method have been verified.

关 键 词：数据链 伪距 组合导航 

分 类 号：V249.3[航空宇航科学与技术—飞行器设计]