基于恒星光行差效应的地月空间航天器自主导航方法  

An Autonomous Navigation Method for Spacecraft in Cislunar Space Using Stellar Aberration Observation

作　　者：刘付成[1,2] 李木子 彭杨 孙俊 刘景熙 LIU fucheng;LI Muzi;PENG Yang;SUN Jun;LIU Jingxi(Shanghai Academy of Spaceflight Technology,Shanghai 201199,China;Shanghai Aerospace Control Technology Institute,Shanghai 201199,China;Shanghai Key Laboratory of Aerospace Intelligent Control Technology,Shanghai 201199,China)

机构地区：[1]上海航天技术研究院,上海201199 [2]上海市空间智能控制技术重点实验室,上海201199 [3]上海航天控制技术研究所,上海201199

出　　处：《深空探测学报（中英文）》2023年第2期159-168,共10页Journal Of Deep Space Exploration

基　　金：国防科技卓越青年科技基金。

摘　　要：为提高地月往返航天器导航效率与在轨生存能力、减小地面测控负担,提出了一种仅利用背景恒星成像观测的地月空间自主导航方法。根据恒星光行差效应建立观测模型,结合轨道动力学模型及扩展卡尔曼滤波(ExtendedKalman Filter,EKF)实现对航天器轨道状态量的估计。针对识别出的大天体引力场干扰及小视场约束下导航精度下降问题,提出了基于模型预测的大天体引力场处理模型及多视场协同自主导航精度提升方法。Monte-Carlo仿真试验表明,提出的方法可有效修正大行星引力场引起的光线偏折及小视场对导航精度的影响,实现了地月空间长时导航位置精度RMS优于3km,速度精度RMS优于0.2m/s。Exploration and utilization of the cislunar space is of great significance to the future development of human society.In order to improve navigation efficiency and survivability of spacecraft in cislunar space and reduce the burden of ground measurement and control,an autonomous navigation method only using star imagery was presented.In the method,the observation model was constructed based on stellar aberration effect.With the help of the orbit dynamic model and an extended Kalman filter,spacecraft orbit was estimated.For the problems of gravitational field interference from large celestial bodies and navigation accuracy decline under the constraints of small field of view,a gravitational field processing model based on dynamical model prediction and a multi-field collaborative observation method were proposed.Finally,the Monte-Carlo simulation results demonstrate the feasibility of the proposed method,and show that a navigation precision RMS better than 3 km and 0.2 m/s can be achieved.

关 键 词：光行差 自主导航 天文导航 地月空间 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]