摘要
随着惯导技术的发展,机载主惯导逐渐用捷联惯导替代平台式惯导,由此带来了火控系统计算导弹姿态算法的变化。本文研究了惯性导航系统算法,总结出基于机载捷联主惯导的导弹姿态算法。通过仿真验证,该算法计算精度满足要求,可以用于空空导弹导航系统初始化。
With the development of inertial navigation technology,airborne platform inertial navigation system is substituted gradually by SINS,which causes the change of missile attitude algorithm calculated by fire control system. Research on the inertial navigation system algorithm is done and the attitude algorithm base on airborne SINS is summarized. The calculation accuracy of the algorithm meets the requirement and it can be used in the initialization of air-to-air missile navigation system.
出处
《航空兵器》
2016年第2期29-31,共3页
Aero Weaponry
关键词
空空导弹
捷联惯导
初始校准
导弹姿态
算法设计
air-to-air missile
SINS
initial alignment
missile attitude
algorithm design
