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。
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.
出处
《中国惯性技术学报》
EI
CSCD
2007年第4期442-444,共3页
Journal of Chinese Inertial Technology
基金
航天科技创新基金资助项目(HT05014)
