Differential interception tracking method based on space object orbit error

Abstract

The invention provides a differential interception tracking method based on a space object orbit error. The differential interception tracking method comprises the steps: S1, determining an interception tracking trajectory according to theoretical orbit parameters of a target space object; S2, determining the in-advance interception tracking time and direction according to the orbit forecast error of the target space object; and S3, iteratively determining the differential interception tracking rate so as to ensure that the differential interception tracking can cover the orbit forecast error range, and completing the differential interception tracking based on the space object orbit error. The method can effectively alleviate the technical problems of overlarge guide precision deviation, low tracking observation success rate, influence on meteorite falling forecast precision and the like when a specific target is tracked and observed in the prior art.

Description

technical field [0001] The present disclosure relates to the technical field of space object observation, and in particular to a differential interception and tracking method based on space object orbit error. Background technique [0002] In the past 60 years, the aerospace industry has developed vigorously, but it has also brought hundreds of millions of space objects, such as space debris and artificial satellites, to the outer space of the earth, among which the number of space debris is the largest. Space debris larger than 1 cm can cause serious damage to orbiting spacecraft, and space debris smaller than 1 cm can degrade the performance of spacecraft systems. Currently, there are more than 30,000 fragments larger than 10 cm, nearly one million fragments larger than 1 cm, and hundreds of millions of millimeter-sized fragments. In important common orbits, such as the 500-1000km low earth orbit (LEO) and the 36000km geosynchronous orbit (GEO), the space debris is the mo...

AI Technical Summary

Problems solved by technology

This is not a big problem for stable cataloged space debris, but for at least the following two cases, there is a problem of excessive deviation of guidance accuracy

First, due to the low initial orbit accuracy of newly cataloged space debris, the guidance error is too large, and the success rate of tracking observation is not high, which affects the cataloging efficiency of new debris

The second is that the space debris in the re-entry stage has a large error in the atmospheric resistance model, which leads to excessive guidance error, and the success rate of tracking observation is not high, which affects the accuracy of fall forecast

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