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A Dynamic Correction Method of Atmospheric Perturbation Parameters Based on Space Environment Changes

A space environment and dynamic correction technology, applied in aerodynamic tests, motor vehicles, climate sustainability, etc., can solve the problem of increased orbit forecast error, large error of orbital dynamics model of low-orbit space targets, and failure to meet engineering needs and other issues to achieve the effect of improving the forecast accuracy

Active Publication Date: 2022-06-07
中国人民解放军32035部队
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Problems solved by technology

During the disturbance of the space environment, the error of the orbit dynamics model of the low-orbit space target is large, which causes the error of the orbit forecast to increase, which cannot meet the engineering requirements

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  • A Dynamic Correction Method of Atmospheric Perturbation Parameters Based on Space Environment Changes
  • A Dynamic Correction Method of Atmospheric Perturbation Parameters Based on Space Environment Changes
  • A Dynamic Correction Method of Atmospheric Perturbation Parameters Based on Space Environment Changes

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Embodiment Construction

[0029] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0030] Space targets will be affected by various forces when they are in orbit. Among them, the influence of atmospheric drag on orbit prediction is proportional to the square of time. At present, almost all atmospheric density models have a model error of about 10%~20% during the solar calm period, and the error reaches 100% or even higher when the solar activity is intense, which has a huge impact on the orbit prediction of low-orbit...

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Abstract

The invention discloses a method for dynamically correcting atmospheric perturbation parameters based on changes in the space environment. coefficient and ballistic coefficient correction factor, and the corrected ballistic coefficient is obtained according to the pre-built ballistic coefficient correction model; The analysis results of the influence of the parameter forecast on the error of the orbit forecast, and the analysis results of the systematic error of solving the ballistic coefficient absorption atmospheric density model are obtained by performing dynamic correction modeling of the atmospheric perturbation parameters; the ballistic coefficient correction factor is a function of sum. The present invention dynamically corrects the ballistic coefficient based on the change of the space environment, can solve the problem of large error in the track prediction of the space target under the condition of abnormal atmosphere, and can improve the prediction accuracy.

Description

technical field [0001] The invention belongs to the field of aerospace measurement and control, in particular to a dynamic correction method for atmospheric perturbation parameters based on changes in the space environment. Background technique [0002] At present, the main factor restricting the accuracy of low-orbit target orbit prediction in space target orbit dynamics model is atmospheric perturbation. One of the key parameters in atmospheric perturbation models is atmospheric density. Atmospheric density values ​​play an important role in orbit determination, forecasting, and control of low-orbit satellites, as well as satellite flight planning. At the same time, with the continuous progress and development of aerospace technology, human activities to explore space and develop and utilize space resources have become more frequent, resulting in an increasing number of space debris left in space orbits. Space debris is mainly distributed in the GEO orbital area and below...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24G01M9/08G06N20/00
CPCB64G1/242G01M9/08G06N20/00B64G1/247Y02A90/10
Inventor 王秀红张荣之张炜马鑫
Owner 中国人民解放军32035部队
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