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- W2361756687 abstract "Considering the characteristics of orbital motion of the target vehicle and the tracking spacecraft in the rendezvous and docking mission,three kinds of space object collision avoidance strategy calculation methods were proposed according to the engineering practice,including height avoidance method,time avoidance method and combination with normal orbit control method. Height avoidance calculation method was based on the principle of Lambert flight. A simplified two-body kepler' s equation was used instead of the high precision orbit prediction method. Avoidance maneuver velocity increment was solved by iterating and the optimal solution of the velocity increment could be obtained by constraining the radial distance difference between the intersection point of target and space debris. Time avoidance calculation method was based on the relationship between velocity increment and orbital period and the optimal solution of the velocity increment could be obtained by constraining the time difference between the intersection point of target and space debris. The combination with normal orbit control method was based on the redundancy control in the normal control. A small modification to the control time point or along-track velocity increment in control strategy could realize collision avoidance by staggering the collision point or radial distance. It not only saves fuel,but also has little effect on the mission. The simulation analysis of the three methods showed that all the three methods were suitable for the rendezvous and docking mission and could provide technical support for the safety of China' s manned space flight missions." @default.
- W2361756687 created "2016-06-24" @default.
- W2361756687 creator A5005917175 @default.
- W2361756687 date "2014-01-01" @default.
- W2361756687 modified "2023-09-27" @default.
- W2361756687 title "Research on Avoidance Strategy for Rendezvous and Docking Mission" @default.
- W2361756687 hasPublicationYear "2014" @default.
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