轨道机动航天器SINS/GPS自主组合导航算法

Autonomous SINS/GPS for orbital transfer vehicle

为了实现空间机动目标的自主导航,提出了一种基于地心惯性坐标系的轨道机动航天器SINS/GPS自主组合导航算法.首先分析了轨道机动航天器的特点,选取地心惯性坐标系作为导航坐标系.然后建立了导航滤波器的状态方程以及量测方程,其中考虑了SINS系统平台失准角、加速度计误差、陀螺仪误差和加速度计的安装位置和航天器质心之间偏差的影响.最后进行了相关的数学仿真验证,仿真结果表明,该算法可以较准确地给出位置和速度导航信息.

In order to achieve the purpose of autonomous navigation for orbital transfer vehicle,an autonomous SINS/GPS integrated navigation algorithm in ECI coordinate system is researched in detail.The ECI coordinate system is selected to be navigation coordinate system by analyzing the characteristic of orbital transfer vehicle firstly.The navigation filter is established.The effects of angular misalignment of SINS,accelerometer errors,gyro errors and offset between fixed position of accelerometer and center of mass of orbital transfer vehicle are considered in this navigation filter.An associated simulation is carried out and the simulation result shows that this algorithm can be used to provide high accuracy of position and velocity information for orbital transfer vehicle.