High-precision satellite-borne orbit prediction method based on numerical fitting

A technology of orbit forecasting and numerical fitting, applied in astronomical navigation, ground navigation, etc., can solve the problem of poor orbit forecast accuracy on the planet, and achieve the effect of improving forecast accuracy

Active Publication Date: 2019-08-16
CHINA XIAN SATELLITE CONTROL CENT
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  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to provide a high-precision on-board orbit prediction method based on

Method used

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  • High-precision satellite-borne orbit prediction method based on numerical fitting
  • High-precision satellite-borne orbit prediction method based on numerical fitting
  • High-precision satellite-borne orbit prediction method based on numerical fitting

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0086] Take the initial orbital data shown in Table 1:

[0087] Table 1: Initial Orbital Data

[0088]

[0089] Use the high-precision orbit forecasting software to predict the two-day trajectory, and convert it into a flat root number. After fitting with a quadratic polynomial function, you can get the coefficient of the change item of each orbital root number, and the prediction formula is:

[0090]

[0091] The first point of the ballistic trajectory is selected as the flat root number injection demand point, and the corresponding variable output results are shown in Table 2:

[0092] Table 2: Correspondence between injection demand points and variable rate output results

[0093]

[0094] Use the fitted coefficients to perform extrapolation for 48 hours, and compare the extrapolation results with the standard trajectory. The maximum position error is 355m, mainly along the track direction, and the error in the radial and normal directions is relatively small, abo...

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Abstract

The invention discloses a high-precision satellite-borne orbit prediction method based on numerical fitting. The method comprises the following steps: firstly, obtaining atmospheric environment parameters including the latest solar radiation flow and a geomagnetic index, satellite star parameters and the latest precise orbital elements of the satellite, combining the star and space environment parameters, carrying out orbit prediction by utilizing a ground high-precision numerical method so as to obtain a set of satellite instantaneous orbital elements in a prediction arc section, then, converting into an average element to perform numerical fitting so as to obtain a change item coefficient of each orbital element, arranging multiple sets of primary orbits to carry out segmented extrapolation according to an satellite-borne predication requirement, carrying out orbit prediction according to the arranged initial orbital element and the change item coefficient to obtain the average element of the satellite at the prediction moment, if the prediction precision requirement is high, arranging a plurality of sets of initial values for staged prediction, converting the average element ofthe satellite at the prediction moment into the instantaneous element, so that the instantaneous position of the satellite is obtained. According to the method in the invention, the problem that the precision of satellite-borne orbit prediction is poor in the prior art is solved.

Description

technical field [0001] The invention belongs to the technical field of aerospace measurement and control, and in particular relates to a high-precision on-board orbit prediction method based on numerical fitting. Background technique [0002] Due to the limitations of on-board computers and other conditions, on-board orbit forecasting usually adopts simplified analytical models, and the forecasting accuracy is poor. For low-orbit satellites, coupled with the influence of atmospheric density, the forecasting accuracy is even worse. Contents of the invention [0003] The purpose of the present invention is to provide a high-precision satellite orbit prediction method based on numerical fitting, which solves the problem of poor accuracy of satellite orbit prediction existing in the prior art. [0004] The technical solution adopted in the present invention is a high-precision satellite orbit prediction method based on numerical fitting, which is specifically implemented accor...

Claims

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Application Information

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IPC IPC(8): G01C21/02G01C21/08
CPCG01C21/02G01C21/08
Inventor 王彦荣张轲方海舰王丹刘蓉曹璐何雨帆李海玥刘军锋任勃叶修松薛嘉马瑞明吴铁柱郭海
Owner CHINA XIAN SATELLITE CONTROL CENT
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