基于加速度信息的导航卫星轨控期间自主定轨方法  

Autonomous orbit determination method for navigation satellite during orbit maneuver based on accelerometer

作　　者：黄河[1] 周军[1] 刘莹莹[1] 王洋[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《系统工程与电子技术》2014年第2期331-336,共6页Systems Engineering and Electronics

基　　金：国家高技术研究发展计划(863计划)(2012AA120602)资助课题

摘　　要：为了降低对地面测控站的依赖,提升导航卫星自身的自主运行能力具有重要意义。导航卫星在轨道控制期间,自主定轨误差将会产生重大偏差,为了能够快速恢复星历,提升导航系统的应用效率,针对导航卫星轨控期间的自主轨道确定技术进行了研究。首先,在传统的天文导航的基础上引入了加速度信息,然后根据加速度计测量以及估计误差判断,选择合适的时机在轨控期间对估计误差方差阵进行重置。仿真结果表明,基于加速度信息的自适应导航滤波算法,能够有效降低导航误差收敛时间,同时降低估计误差峰值。In order to reduce the dependence of the ground station, it is of great importance to improve the autonomous operation ability of the navigation satellite. During the orbit maneuver, the autonomous orbit deter- mination error of the navigation satellite will be enlarged. In order to resume the precise ephemeris of the navi- gation satellite quickly, which can enhance the application efficiency of the navigation satellite system, a new au- tonomous orbit determination method for the navigation satellite is presented. The proposed method is an im- provement of the traditional celestial navigation method, in which the accelerometers are used. The acceleration value will be added to the orbit dynamics function. Meanwhile, the estimation error square matrix of the ex- tended Kalman filter will be reset during the orbit maneuver phase. Simulation results show that the conver- gence time and estimation error will be reduced effectively by the proposed method.

关 键 词：导航 自主定轨 自适应扩展Kalman滤波 加速度 导航卫星 轨道机动 

分 类 号：V44[航空宇航科学与技术—飞行器设计]