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提出一种利用X射线脉冲星的晕轨道自主导航方法。以高精度星历轨道动力学模型构建晕轨道状态方程,并利用二级微分修正方法获取惯性系下晕轨道的标称轨道。基于微分修正原理,利用X射线脉冲星的导航结果和小推力推进器,对晕轨道探测器进行轨道维持和控制,并以地月系L2点晕轨道为例进行了仿真实验。结果表明,该方法能够有效完成地月系L2点晕轨道探测器的自主导航和轨道维持任务。
A method of autonomous orbital halo navigation using X-ray pulsar is proposed. The halo orbital equation of state is constructed with a high-precision ephemeris orbit dynamics model and the nominal orbit of the halo of the inertial system is derived using a second-order differential correction method. Based on the principle of differential correction, the X-ray pulsar navigation results and thrust thruster are used to maintain and control the halo orbit detector. The simulation experiment is carried out by taking the L2 halo of earth and moon system as an example. The results show that this method can effectively accomplish the autonomous navigation and orbital maintenance tasks of the lunar system L2 halo corridor track detector.