Orbit design method for spacecraft lunar orbit rendezvous and docking

Abstract

The invention relates to an orbit design method for spacecraft lunar orbit rendezvous and docking, which comprises the following steps: a, establishing an orbit maneuvering mathematical model for spacecraft lunar orbit rendezvous and docking by adopting an orbit descending rendezvous mode of pulse orbit transfer; b, determining the height of a spacecraft rendezvous and docking initial orbit lunarpoint through phase modulation range analysis; c, estimating an initial value of the pulse orbital transfer maneuver under the two-body model, and ensuring that the initial value is quickly convergedunder an accurate model consisting of the two-body model and a perturbation force model; d, performing in-plane orbital transfer planning under the accurate model, and obtaining orbital transfer parameters of in-plane orbital transfer through calculation; e, performing out-of-plane orbital transfer planning under the accurate model, and orbital transfer parameters of out-of-plane orbital transferare obtained through calculation; and f, performing comprehensive orbit transfer planning under the accurate model, updating orbit transfer parameters of in-plane orbit transfer after out-of-plane orbit transfer, and obtaining a lunar orbit rendezvous and butt joint orbit.

Description

technical field [0001] The invention relates to the technical field of manned spacecraft rendezvous and docking orbit design, and relates to an orbit design method for orbital rendezvous and docking of spacecraft around the moon, in particular to the full-phase rendezvous and docking orbit design for the mission of orbital rendezvous and docking in the process of spacecraft flying to the moon method. Background technique [0002] According to the experience of the Apollo moon landing project, if the manned moon landing mission adopts the single launch mode, a rocket with a carrying capacity of LEO 100 tons is required, which greatly increases the difficulty of the development of the launch vehicle. In order to increase the feasibility of the task, the carrying capacity of the launch vehicle can be reduced, but the manned lunar landing vehicle needs to be divided into two parts: the manned spacecraft and the lunar surface lander, which are sent to the earth-moon transfer orbi...

AI Technical Summary

Problems solved by technology

At present, the country has mastered the core technologies related to low-earth orbit rendezvous and docking; in the third phase of the lunar exploration project, it will break through the technology of unmanned orbital rendezvous and docking around the moon, but it is also the rendezvous and docking of the orbit around the moon during the process of rising and returning from the lunar surface. A public design method for rendezvous and docking of orbits around the moon during the process of flying to the moon

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