A method for rapid planning of low earth orbit spacecraft rendezvous window

By calculating the ascent reach and illumination constraints during rocket maneuvers at the atmospheric edge, and combining this with the Lambert algorithm, rendezvous windows for low-Earth orbit spacecraft can be planned quickly. This solves the problems of slow planning speed and insufficient constraint applicability in existing technologies, and achieves fast and highly applicable rendezvous window planning.

CN117485604BActive Publication Date: 2026-05-12BEIJING INST OF TECH
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Patent Information

Application Number
CN202311440730.9
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2023-11-01
Publication Date
2026-05-12
Estimated Expiration
2043-11-01

AI Technical Summary

Technical Problem

Existing technologies cannot quickly and effectively plan rendezvous windows for low-Earth orbit non-cooperative spacecraft under various constraints, especially under fuel consumption and illumination constraints, and cannot effectively determine rendezvous windows.

Method used

By maneuvering the rocket after it exits the atmosphere, the achievable ascent range is calculated. Combined with the target position and lighting constraints, the velocity increment is calculated using the Lambert algorithm, enabling rapid planning of rendezvous windows.

Benefits of technology

It enables rapid planning of rendezvous windows that meet multiple constraints in a short period of time, is applicable to multiple atmospheric edge states, has strong applicability, and is suitable for rendezvous between ground-launched rockets and low-Earth orbit spacecraft.

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Abstract

The application discloses a kind of low-orbit spacecraft's meeting window fast planning method, belong to aerospace field.The application implementation method is: after being applied to the rocket of ground launch reaches the edge of atmosphere, rocket carries out a maneuver, and meets target spacecraft in ascending process.Meeting window for spacecraft meeting target task is obtained.Meeting window fast planning is mainly divided into three steps, first, according to the envelope of rocket shutdown point and pulse size, the ascending reachable range is obtained.Second, the height of this ascending device, the range of the target in the fixed system is used to judge the coarse window.Third, after obtaining the coarse window, the rocket is shot to the target direction, and the shutdown point position in the inertial system is obtained.Based on the point, the Lambert method is used to calculate the velocity increment.If the constraint is satisfied, it is determined that the rocket can meet the target, i.e.the low-orbit spacecraft's meeting window fast planning is realized.The application has the advantages of fast planning speed and strong applicability.
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