弹道学报2016，Vol.28Issue(1)：39-44,6.
高旋火箭弹GPS/SINS组合测姿方法
GPS/SINS Attitude Measurement Method of High-spin Rocket
摘要
Abstract
According to the attitude-algorithm problem of GPS/SINS applied to high-spin rocket such as the difficulty of initial alignment and the error accumulation, a correction technique of initial roll angle using segment filtering and advance-retreat technology was proposed by the aid of velocity angles. The initial roll angle of segments was constantly corrected to drive the result of SINS close to the reasonable value,and the error accumulation caused by high-spin rate was removed by velocity angles. More accurate attitude-information was obtained by Kalman filtering. The simulation result shows that more accurate attitude-information can be obtained by the correction technique of initial-roll-angle using segment filtering. The technology can be used in practical engineering,and the solved attitude information satisfies project requirement.关键词
高旋火箭/分段滤波/进退法/速度角修正/GPS/SINS组合测姿Key words
high-spin rocket/segment filtering/advanc-retreat technology/trajectory angles correction/GPS/SINS attitude measurement分类
军事科技引用本文复制引用
安亮亮,王良明..高旋火箭弹GPS/SINS组合测姿方法[J].弹道学报,2016,28(1):39-44,6.基金项目
国防973项目 （）
