A Method of Precise Orbit Acquisition Based on Strictly Regressive Orbit Space Trajectory Network

Abstract

The invention discloses a precise track capture method for entering orbit based on a strictly regressive orbit space trajectory network, which includes: processing data corresponding to reference orbit sampling points; Preliminary matching of orbital sampling points; correction of the reference time of reference orbital sampling points; determination of orbital parameter deviation, determination of precise orbital capture in the form of successive target control. The method can overcome the problem that there is a large deviation between the spacecraft and the reference orbit caused by the launch date, launch time or orbit accuracy during actual launch into orbit. The new method of the present invention is aimed at data processing of reference orbit sampling points; according to launch Determination of the actual state of orbit entry and the preliminary matching of reference orbit sampling points; precise correction of reference time of reference orbit sampling points; determination of orbit parameter deviation, determination of precise orbit capture in the form of successive target control, and other process steps to achieve strict return to orbit In-orbit precision orbit capture of space trajectory network.

Description

technical field [0001] The invention relates to the application field of spacecraft engineering technology, in particular to a precise orbit capturing method based on a strict regressive orbit space trajectory network. Background technique [0002] Accurate target orbit acquisition for entry into orbit belongs to the field of orbit control. The traditional orbit capture only has targets such as the target orbital element, the sub-satellite point trajectory, or a combination of the two. Near-Earth polar orbits can involve orbits with good sun-synchronous and freezing characteristics. Furthermore, a strict regression orbit and corresponding reference orbit sampling points can be optimally designed around the regression cycle of space trajectory revisiting. Reference orbit sample points are time-stamped and can be reused periodically. When actually launching into orbit, there is a deviation between the spacecraft and the reference orbit caused by factors such as launch time,...

AI Technical Summary

Problems solved by technology

[0003] The object of the present invention is to provide a method for capturing precise orbital orbits based on a strict regression orbital space trajectory network, which can overcome the gap between the spacecraft and the reference orbit caused by launch time, launch time, or orbital accuracy when actually launching into orbit. The present invention aims at the data processing of the reference orbit sampling point, and determines the preliminary matching with the reference orbit sampling point according to the actual state of launching into orbit, accurately corrects the reference time of the reference orbit sampling point, and determines the orbit parameter deviation, Determining the process steps such as the entry-to-orbit fine-track capture in the form of successive target control can realize the entry-to-orbit fine-track capture that strictly returns to the orbital space trajectory network

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