A full mission cycle orbit design method for upper stage multi-satellite deployment

Abstract

The invention discloses an upper sage multi-satellite deployment full task periodic orbit designing method. The method includes the following steps: 1. based on an upper stage multi-satellite deployment task, presenting general procedures of multi-satellite deployment, analyzing the composition of phase error of multi-satellite deployment; 2. Conducting error compensation on the phase error of which the composition has been analyzed and the phase error which is caused by orbit perturbation, satellite separation and orbit maneuver, then designing a drift orbit; and 3. Considering phase error which is caused by other interference factors in the phase drift process, conducting intermediate correction in the phase maneuver. The method herein, by fully considering all kinds of error compositions and factors in the process of multi-satellite deployment, designs the parameters of an upper stage drift orbit on the basis of compensating respective phase errors, and by conducting intermediate correction in the phase maneuver based on the limited threshold values, further effectively suppresses phase error, and increases the effects of realizing multi-satellite deployment and initial performances of the constellation that is deployed.

Description

technical field [0001] The invention belongs to the field of spacecraft orbit design, and in particular relates to an upper-level multi-satellite deployment full-task cycle orbit design method. Background technique [0002] In order to meet the mission requirements of low-orbit micro-satellite networking and constellation applications, multi-satellite deployment using the advanced upper stage (hereinafter referred to as the upper stage) is the best constellation deployment method. The main task of the upper stage is to realize multi-satellite deployment. Using its powerful maneuverability, the upper stage can maneuver to another drift orbit through multiple ignitions, starts, accelerations or decelerations, and perform phase modulation drift. Return to the target orbit and complete satellite deployment to realize rapid inter-satellite phase adjustment to meet the phase or altitude requirements of different satellites entering orbit. Although the satellite itself can achieve...

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Problems solved by technology

[0004] At present, there are few researches on the design of upper-level multi-satellite deployment orbits, mainly including the optimization design for the design and selection of phase modulation orbits, and the preliminary exploration of error correction methods in the deployment process. After the error composition and influencing factors, a detailed study of the orbit design method within the full mission period of multi-satellite deployment is reported.

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