空间平台机动变轨自主导航研究

针对空间平台在高轨道机动变轨过程中自主导航的需求,采用了基于Kalman滤波器的捷联惯导与星敏感器的组合导航方案。结合Kalman滤波中协方差更新的误差分配分析方法,分析了影响空间平台状态估计误差的主要因素。采用适用于高轨道的球谐重力模型,运用STK工具包设计了变轨机动轨迹,将该轨迹应用于组合导航方案的仿真验证。仿真结果表明,量测噪声是影响空间平台姿态精度的主要因素,加速度计零偏对变轨过程速度精度有决定性影响,改善两者的精度可以实现空间平台机动变轨的高精度自主导航。

Research on Autonomous Navigation of Maneuverable Orbit on Space Platform

Based on Kalman filter, strapdown inertial/star sensor integration navigation algorithm is adopted for the autonomous navigation of space platform during high orbit maneuvering. Combined with the error distribution algorithm for navigation systems based on the process of Kalman filter covariance update, the main factors affecting the error of state estimation of space platform are analyzed. Furthermore, the spherical harmonic gravity model suitable for high orbit is adopted, and a simulation test system for trajectory of orbital maneuver is designed using the STK. The simulation results show that the measuring noise is the main factor affecting the attitude accuracy of the space platform. The accelerometer bias has a decisive influence on the accuracy of the trajectory change process, and by improving the accuracy of the two by the high-precision autonomous navigation of the maneuverable orbit change can be achieved.