Orbit-data-based breakup debris source identification method

Abstract

The invention discloses an orbit-data-based breakup debris source identification method, which comprises the following steps of calculating breakup debris orbit data; screening a breakup debris matrix orbit surface range to obtain a suspected broken-up matrix set by utilizing the breakup debris orbit data; obtaining the suspected breakup time of each suspected matrix by virtue of a orbit surface geometrical screening method according to breakup debris and the number of suspected matrix orbits; calculating the average intersection distance of each suspected broken-up matrix and each breakup debris at respective suspected breakup time, and employing the suspected matrix with the shortest interaction distance as the real broken-up matrix. According to the method, the matrix of the debris can be rapidly determined when a space object is broken up; the breakup debris source identification method is completely and comprehensively described for the first time in China, an example shows the correctness of the method, and the method is significant for correctly sensing the change of a space debris environment and taking corresponding measures.

Description

technical field [0001] The invention relates to the technical field of space debris monitoring and early warning, in particular to a method for identifying the source of disintegrated debris based on orbital data, which is suitable for identifying the source of debris after the disintegration of earth-orbiting satellites or rocket wreckage. Background technique [0002] Orbital Surface Spherical Geometry. The disintegration debris and the parent body of the disintegration debris have a specific geometric relationship at the moment of disintegration, so the parent body's perigee argument and parent body's true perigee angle at the time of disintegration (disintegration position) can be determined by the variation of the debris inclination and the right ascension of the birth node The inclination angle with the parent body is calculated. That is, the disintegration time of the parent body can be obtained by calculating the orbital surface prediction of the disintegrating pare...

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Problems solved by technology

However, there is no introduction of relevant content in the current literature. The main reasons for the analysis are: (1) The source identification of disintegrated debris is a key technology for the processing of space object monitoring data. (2) The method of identifying the source of disintegrated debris is different from the monitoring equipment of the country / organization, and the analysis and processing methods are also different; (3) After the monitoring equipment is built in other countries, the content of this research will be of great significance , but currently there are few countries with large-scale space object monitoring and cataloging management capabilities, and there are few corresponding research and published papers

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