利用SINS/GPS组合导航修正不完全轨道技术研究  

Research on Technology for Correction of Incomplete Orbit Based on SINS/GPS

作　　者：张志国[1] 张慧娟[1] 周欣明[1] ZHANG Zhiguo;ZHANG Huijuan;ZHOU Xinming(No.91550Troops of PLA,Dalian 116023)

机构地区：[1]91550部队,大连116023

出　　处：《计算机与数字工程》2018年第6期1120-1122,1134,共4页Computer & Digital Engineering

摘　　要：在飞行器试验GPS事后数据处理中,由于飞行器的高动态环境或级间分离,都将导致GPS数据的丢失,从而导致外测轨道的不完整,对脱靶量的推算也将因为外推时间过长而无法准确计算。而载体上捷联惯导数据也因为漂移较大而无法单独使用。文中将利用组合导航原理,将捷联惯导数据和GPS数据联合处理,从而得到全轨道。In the GPS data processing of aircraft test,due to the highly dynamic environment or the interstage separation ofthe aircraft,the GPS data will be lost. The lost data leads to the incompleteness of external measurement orbit,and the miss dis-tance will also not be calculated accurately due to long time extrapolation. At the same time,the carrier＇s SINS data cannot be usedalone because of large data drift. The article will use the principle of integrated navigation to get full orbit combining the SINS dataand GPS data.

关 键 词：组合导航 不完全轨道 高动态 脱靶量 

分 类 号：TN967[电子电信—信号与信息处理]