The rendezvous and docking in lunar orbit is critical during sampling return mission. The paper proposes anautonomous determination approach for chaser spacecraft during rendezvous and docking process in lunar orbit. Theapproach estimates the absolute orbit parameters of chaser spacecraft during whole rendezvous and docking processby comprehensively utilizing the measurements of imaging sensor, rendevous radar and star sensor, as well as targetspacecraft orbit extrapolation, integrating absolute orbit dynamics model, and designing a navigation filter by UKFalgorithm. The approach provides the theoretical reference for rendezvous and docking project in lunar orbit.
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