基于无迹卡尔曼滤波的导航星座并行式自主定轨

针对卫星轨道动力学模型的高度非线性及星座自主定轨的高精度需求，基于星间双向测距观测信息，提出了采用无迹卡尔曼滤波（Unscented Kalman Filter, UKF）作为星载算法的导航星座并行式自主定轨方案，并且给出了UKF算法中可见星先验信息引入的额外方差矩阵，以保证滤波的稳定性.仿真结果表明，该方案可以实现星座的长期自主定轨并维持一定精度.

Autonomous Orbit Determination of Satellite Navigation System Based on Unscented Kalman Filter

In accordance with the highly nonlinear of orbit dynamics and the precision requirement of the autonomous orbit determination for navigation constellation,a parallel autonomous orbit determination method based on the dual direction range measurement was proposed.In this method,the unscented Kalman filter is used as the onboard estimation algorithm for each satellite to get its own state and the extra covariance used in this filter which is introduced by the priori orbit is given to ensure the filter stabili...