巡航导弹红外成像导引头辅助导航技术研究  

Research on aided navigation technology for cruise-missile IR imaging seeker

作　　者：朱学平[1] 杨军[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《战术导弹控制技术》2013年第4期32-36,共5页

基　　金：基金项目：西北工业大学基础研究基金（基金号JC20110239）

摘　　要：针对巡航导弹中制导段飞行时间长、纯惯性导航精度低、中／末制导交接班困难的问题，提出了一种基于红外成像导引头／捷联惯导的新组合导航方案。巡航导弹中制导段红外成像导引头识别并跟踪已知坐标的地标点（或地物），采用卡尔曼滤波算法实现导引头和捷联惯导的信息融合，从而获取较高精度的导航信息。本文建立了红外成像导引头／捷联惯导组合导航系统的数学模型，给出了一种基于无迹卡尔曼滤波（UKF）的信息融合算法并进行了数字仿真。仿真结果表明，该方案可以实现巡航导弹中制导段高精度导航。A new integrated navigation scheme is put forward based on IR imaging seeker/strap-down inertial navigation re- garding the problems of long flight time in midcourse guidance phase for cruise-missile, low inertial navigation accuracy and difficulty in midcourse/terminal guidance handover. Cruise-missile IR imaging seeker identifies and tracks landmark points （or surface features） by known coordinate in midcourse navigation phase, and employs Kalman filtering algorithm to carry out information fusion between seeker and strap-down inertial navigation, then it gains navigation information with high ac- curacy. The mathematical model of integrated navigation system is established and an information fusion algorithm based on UKF is drawn out with mathematical simulation. The simulation results show that this scheme can realize navigation with high accuracy in cruise-missile midcourse phase.

关 键 词：巡航导弹 红外成像导引头 捷联惯导 组合导航 卡尔曼滤波 

分 类 号：V249[航空宇航科学与技术—飞行器设计]