地月平动点导航仿真程序设计及可行性验证

Simulation Program Design and Feasibility Verification of Navigation for Earth-Moon Libration Point

由于我国地面测控资源有限和全球导航卫星系统对深空导航覆盖效果不足,有必要寻找自主导航方式。平动点导航是一种利用星间测距的深空自主导航方式。本文设计了包含4个模块的仿真程序,并利用仿真程序进行可行性仿真。地月L1Halo轨道卫星与绕月轨道卫星进行测距测速滤波导航定轨,平动点轨道卫星综合位置误差小于50m,绕月轨道卫星综合位置误差小于20m,验证了平动点导航的可行性。

Due to the limited ground TT&C resources and the insufficient coverage of GNSS for deep space navigation,it is necessary to find an autonomous navigation mode.Libration point navigation is a deep space autonomous navigation method using inter-satellite ranging.A simulation program with four modules is designed,and the feasibility simulation is carried out by using the simulation program.Halo orbiting satellite and lunar orbiting satellite with an inclination of 200 km and an angle of 45 degrees are used for ranging,velocity measurement,filtering,navigation and orbit determination.The integrated position error of Halo orbiting satellite is 50 m and that of lunar orbiting satellite is 20 m.This verifies the feasibility of libration point navigation.