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A two-step method to detect broadcast ephemeris unavailable periods caused by BeiDou satellite orbital maneuvers

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Geodesy and Geodynamics 2023年第5期14卷 456-466页

作者： Jingjing Wang Chao Zhou Zhixuan Sun School of Architectural Engineering Weifang University of Science and TechnologyWeifang 262700China Faculty of Infrastructure Engineering Dalian University of TechnologyDalian 116024China College of Mechanical and Electronic Engineering Shandong Agricultural UniversityTaian 271018China

The space constellation of the BeiDou navigation satellite system(BDS) is a hybrid constellation containing medium earth orbit(MEO) satellites, geostationary earth orbit(GEO) satellites, and inclined geosynchronous orbit(IGSO) satellites. Due to the geosynchronous characteristics of GEO and IGSO, GEO satellites and IGSO satellites often need to perform orbital maneuvers, which can affect the signal-inspace(SIS) availability performance of BeiDou satellites. A two-step detection method for BeiDou satellite orbital maneuvers has been proposed in this paper. The first step is to identify orbital maneuvers based on time series analysis of broadcast ephemeris, and the second step is to verify orbital maneuvers based on bidirectional orbit prediction. The two-step detection method was used to detect the orbital maneuvers of BeiDou satellites in 2019. Through the double guarantees of identification and verification,the detection accuracy of BeiDou satellite orbital maneuvers has been effectively improved. And the orbital maneuver detection results are continued to be used to assess the SIS availability of BeiDou satellites. The results show that the availability loss of GEO satellite orbital maneuvers is about 0.45%-1.07%, and the availability loss of IGSO satellite orbital maneuvers is about 0.12%-0.19%.

关键词： BDS orbital maneuver Signal-in-space Availability Time series analysis

Research on the strategy of angles-only relative navigation for autonomous rendezvous

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Science China(Technological Sciences) 2011年第7期54卷 1865-1872页

作者： LI JiuRen LI HaiYang TANG GuoJin LUO YaZhong College of Aerospace and Material Engineering National University of Defense Technology Changsha 410073 China

This paper considers the problem of angles-only relative navigation for autonomous rendezvous. Methods for determining degree of observability （DO0） and latent range information of orbital maneuver are proposed for analyzing and enhancing the precision of relative position and velocity estimation. The equations of angles-only relative navigation are set forth on the con- dition that optical camera is the only viable sensor for relative measurement, and expressions for the DO0 of relative navigation are obtained by using the Newton iterative method. The latent range information of orbital maneuver is analyzed, which is employed to enhance the DOO of angles-only relative navigation. Simulation result shows that DOO is effective to describe the observability level of relative position and velocity, and the latent range information is useful in enhancing the DOO of the angles-only relative navigation.

关键词： autonomous rendezvous relative navigation angles-only degree of observability orbital maneuver

Effectiveness-based orbital optimization for servicing spacecraft

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Journal of Harbin Institute of Technology(New Series) 2011年第2期18卷 113-118页

作者：蔡远文申功勋于小红李岩 School of Astronautics Beijing University of Aeronautics and Astronautics Academy of Equipment Command & Technology

Effectiveness-based system development is an essential technology developing concept advanced by some countries,such as the *** use of Analytic Hierarchy Process,this paper brings forward a methodology for orbital optimization based on effectiveness in the case of the orbital deployment for the Servicing Spacecraft(SSC),which needs to accomplish many types of tasks and whose orbit is affected by kinds of factors with contradictions in orbital parameter ***,the possible tasks of SSC are decomposed and their degrees of importance are given by the times,probabilities,values of their ***,the supporting capabilities are discussed from the viewpoint of orbit design,and the determination of their weights is put ***,the relationships between the orbital parameters and the effectiveness are established by using effective function,and three synthesizing methods for a single task and its capabilities are presented.

关键词： servicing spacecraft orbital deployment orbital maneuver effective function Analytic Hierarchy Process

A Method Based on the orbital Error Correction of the Wide Area Differential Positioning Algorithm

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A Method Based on the Orbital Error Correction of the Wide A...