|
|||||
|
|
| GPS/SINS组合导航系统在运载火箭中的应用 | |
| 引用本文： | 蒋金龙,穆荣军,王刚,崔乃刚.GPS/SINS组合导航系统在运载火箭中的应用[J].中国惯性技术学报,2007,15(4):442-444. |
| 作者姓名： | 蒋金龙 穆荣军 王刚 崔乃刚 |
| 作者单位： | 1. 三江航天设计所,武汉,430000 2. 哈尔滨工业大学,哈尔滨,150001 3. 中国运载火箭技术研究院,北京,100076 |
| 摘 要： | 针对运载火箭特点,着重研究在发射惯性坐标系下,位置、速度组合模式的GPS/SINS组合导航算法,推导了该坐标系下的惯导一阶误差传播方程,建立了该坐标系下GPS/SINS组合导航系统的状态方程和观测方程,并进行了相关数学仿真验证。仿真结果表明,在该坐标系中,GPS/SINS组合导航算法能较准确地给出运载火箭的位置、速度和姿态信息,提高运载火箭制导精度。 |
| 关 键 词： | 组合导航系统 发射惯性系 卡尔曼滤波器 |
| 文章编号： | 1005-6734(2007)04-0442-03 |
| 修稿时间： | 2007年3月8日 |
Application of GPS/SINS integrated navigation system in launching vehicle |
|
| JIANG Jin-long,MU Rong-jun,WANG Gang,CUI Nai-gang.Application of GPS/SINS integrated navigation system in launching vehicle[J].Journal of Chinese Inertial Technology,2007,15(4):442-444. | |
| Authors: | JIANG Jin-long MU Rong-jun WANG Gang CUI Nai-gang |
| Abstract: | In view of the characteristics of the launching vehicle, the GPS/SINS integrated navigation algorithm based on position-velocity combined mode in the launching inertial coordinate was studied. The first-order error spread equations were derived: both of the state equations and measurement equations were studied. The simulation results indicate that the GPS/SINS algorithm can accurately provide position, velocity and attitude information of the launching vehicle, so the guidance precision can be increased. |
| Keywords: | GPS/SINS |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ | |