Spacecraft orbit determination method based on multi-source data driving
A multi-source data and determination method technology, applied in the direction of instruments, integrated navigators, satellite radio beacon positioning systems, etc., can solve problems such as patents or papers that have not yet been published, and achieve high-precision results
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At present, there are no published patents or research results for spacecraft orbit determination methods driven by multi-source data for attitude and orbit control systems.
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[0046]In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is only some embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
[0047] like Figure 1-Figure 4 Shown, the present invention provides a kind of spacecraft track determination method based on multi-source data drive, and this method comprises the following steps:
[0048] Step S1. Carry out orbit data preprocessing for GNSS measurement data, and eliminate erroneous data in combination with threshold judgmen...
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The invention discloses a spacecraft orbit determination method based on multi-source data driving. The spacecraft orbit determination method comprises the following steps: performing orbit data preprocessing on GNSS measurement data; coordinate system conversion is carried out on GNSS measurement data; carrying out system time maintenance on the filtering moment and the satellite-borne computer operation moment, and carrying out time compensation on orbit data obtained by filtering; constructing a navigation filtering algorithm, and using a calculation result of an EKF filter as a main schemefor spacecraft orbit determination; determining a spacecraft orbit to obtain inertial system position and speed information, and converting the inertial system position and speed information to obtain instantaneous orbit parameters and an orbital mean number; judging the stability of navigation filtering according to the number of horizontal orbits; using an orbit recursive algorithm as a backupscheme for spacecraft orbit determination; and designing switching logic between main and backup schemes according to the working state of a GNSS measurement system. The influence generated by noise errors generated by the GNSS measurement system and time deviation between satellite platform subsystems is overcome, and a high-precision space-time reference is provided for an attitude and orbit control system.
Description
technical field [0001] The present invention relates to the application field of spacecraft engineering technology, in particular to a multi-source data-driven spacecraft orbit determination method, and more particularly, a method for obtaining the orbit of a GNSS measurement system (Global Navigation Satellite System, global satellite navigation system). The real-time orbit information and the reference time orbit parameters acquired by the ground measurement orbit use a filtering algorithm or an orbit recursion algorithm to determine the spacecraft orbit; compared with the method of directly using the GNSS system measurement value, the spacecraft orbit determination method designed by the present invention A higher-precision spatio-temporal reference can be obtained. Background technique [0002] The orbit determination of the spacecraft in orbit can be obtained based on the real-time measurement data of the GNSS system or the prediction of the orbit recursion algorithm. ...
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IPC IPC(8): G01C21/24G01S19/37G01S19/42
CPCG01C21/24G01S19/37G01S19/42
Inventor 杨盛庆贾艳胜杜耀珂王文妍王禹刘美师王嘉轶吴敬玉