论文部分内容阅读
近年来,使用星敏感器的导弹、火箭惯性组合导航成为国内外研究的热点。本文对捷联惯性/大视场星光组合导航方法进行了研究,建立了卡尔曼滤波方程,并利用SINS误差转移矩阵方法估计主动段导航误差。数学仿真表明:捷联惯性/大视场星光组合导航方法不仅可以修正姿态角偏差和陀螺常值漂移,还可以对主动段的速度、位置误差有很好的估计效果。
In recent years, the use of star-sensitive missiles, rocket inertial integrated navigation has become a hot spot at home and abroad. In this paper, the strapdown inertial / large field of view star combination navigation method is studied, Kalman filter equations are established, and the SINS error transfer matrix method is used to estimate the active segment navigation error. The mathematical simulation shows that the strapdown inertial / large field of view star combination navigation method can not only correct the attitude deviation and gyro drift, but also have a good estimation effect on the velocity and position error of the active section.