Space debris association method and medium

A technology of space debris and direction deviation, applied in space navigation equipment, space navigation equipment, space navigation vehicles, etc., can solve problems such as large incompatibility, restrictions on the expansion of debris cataloging library, initial orbit correlation problems or low efficiency, etc. Achieve the effect of improving computing efficiency and good independent correlation judgment ability

Inactive Publication Date: 2019-07-12
WUHAN UNIV +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The combined effects of the two problems make the aforementioned method less suitable when applied to initial orbit correlation
After observing a huge amount of very short arc initial orbits, if the initial orbit correlation problem cannot be solved or the efficiency is low, the expansion of the debris cataloging library will be severely restricted

Method used

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  • Space debris association method and medium
  • Space debris association method and medium
  • Space debris association method and medium

Examples

Experimental program
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Effect test

Embodiment 1

[0042] A method for associating space debris, comprising the steps, such as figure 1 Shown: Step 101, according to the two sets of orbital parameters of space debris, the orbital parameters are the initial orbital parameters of very short arc only angle observations, including orbital major radius, orbital eccentricity, orbital inclination, ascending node right ascension, perigee angular distance , mean anomaly angle, reference time of orbital parameters. A common time is selected, and the common time is the reference time of the two groups of orbital parameters or any time between the reference times of the two groups of orbital parameters. Preferably, the common time is the mean value of the reference time of two groups of orbital parameters.

[0043] Step 102: Propagate the two groups of orbital parameters described in step 101 to the common time using the analytical propagation method; calculate the difference between the major radii and the orbital plane angle of the two...

Embodiment 2

[0052] A computer-readable storage medium, on which a computer program is stored, and when the program is executed by a processor, the steps of the method for associating space fragments are realized.

Embodiment 3

[0054] (1), set in the inertial space coordinate system, given two sets of independent Kepler orbital parameters, respectively σ 1 =(a 1 ,e 1 ,i 1 ,Ω 1 ,ω 1 , M 1 ;t 1 ) and σ 2 =(a 2 ,e 2 ,i 2 ,Ω 2 ,ω 2 , M 2 ;t 2 ), the variables in the brackets represent the major radius, eccentricity, inclination, ascending node right ascension, perigee angular distance, mean anomaly angle and the reference time of the orbital parameters of the space debris orbit in turn. The inertial space coordinate system is geocentric J2000.

[0055] (2), select t 1 and t 2 The middle moment of is public moment t m , ie t m =(t 1 +t 2 ) / 2.

[0056] (3), using the analytical propagation method to convert σ 1 and σ 2 Propagated to public moments, respectively:

[0057]

[0058]

[0059] The second, third and fourth order harmonic perturbations of the earth's non-spherical gravitational field are considered in the analysis of propagation. Orbital propagation can adopt the me...

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Abstract

The invention discloses a space debris association method. The space debris association method includes the following steps that step 1, a public moment is selected according to two sets of orbital parameters of space debris; step 2, the two sets of orbit parameters in the first step are separately propagated to the public moment; the difference between long radii and an included angle of orbitalplanes of the two sets of orbital parameters at the public moment are calculated; step 3, when the difference between the long radii and the included angle of the orbital planes in the second step areboth smaller than corresponding thresholds, a step 4 is performed, otherwise, it is determined that the two sets of orbital parameters are different space debris; and step 4, the long radii of the two sets of orbital parameters at the public moment are adjusted, when the radial deviation, the deviation in the orbit directions and the deviation in the normal directions of the orbital planes of thetwo sets of orbital parameters at the public moment are all smaller than corresponding thresholds, it is determined that the two sets of orbital parameters are the same space debris, otherwise, it isdetermined that the two sets of orbital parameters are different space debris. The accuracy and calculation efficiency of the space debris association method are both higher than that of a covariance-based track association (CBTA) method.

Description

technical field [0001] The invention relates to a space debris correlation method and a medium, in particular to a space debris very short arc initial orbit correlation method without error information, and belongs to the technical field of space target orbit determination. Background technique [0002] Very short arc initial orbit correlation means: Given two independent initial orbit parameters determined by very short arc angle observations, determine whether they belong to the same target. The so-called very short arc means that the time between the first and last moments of observation is the arc length of the orbit of the measured celestial body, and if the arc length of the measured orbit is less than 1% of the orbital period of the celestial body, it is called a very short arc. Angle-only observations of natural or man-made celestial bodies The initial orbit determination problem is defined as: Given the angular observations (right ascension / declination or azimuth / al...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/66
CPCB64G1/66
Inventor 雷祥旭桑吉章潘腾李怀峰贺东雷
Owner WUHAN UNIV
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