The method is suitable for quick processing of large eccentricity ratio orbit dense ephemeris precision calculation

A processing method and eccentricity technology, applied in complex mathematical calculations, observation of aerospace vehicles, satellite radio beacon positioning system, etc., can solve problems that are difficult to balance accuracy and efficiency

Active Publication Date: 2020-05-29
ZIJINSHAN ASTRONOMICAL OBSERVATORY CHINESE ACAD OF SCI
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Problems solved by technology

Aiming at the problem that the calculation of dense ephemeris with large eccentricity orbits is difficult to take into account both accuracy and efficiency, the present invention proposes a method for constructing non-uniform interpolation base points, combined with a technical solution for fast in

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  • The method is suitable for quick processing of large eccentricity ratio orbit dense ephemeris precision calculation
  • The method is suitable for quick processing of large eccentricity ratio orbit dense ephemeris precision calculation
  • The method is suitable for quick processing of large eccentricity ratio orbit dense ephemeris precision calculation

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Embodiment

[0101] Example: known space target epoch t 0 =58362.0 (reduced Julian day MJD) moment orbital element is: semi-major radius a=5.25a e (a e To refer to the equatorial radius of the ellipsoid, its value is 6378136m), the eccentricity e=0.8 (the value of root number a and e in case 3 is different from this, see the description of case 3 for details), orbital inclination i=45°, The equator of the ascending node Ω=0°, the argument of perigee ω=0°, and the mean anomaly M=0°. Orbital elements can be converted to get t 0 time position vector and velocity vector The conversion method will not be described in detail. The time point to generate dense ephemeris is {t i}(i=1, 2, 3, ... m), where t 1 = t 0 +P 0 / 2,t m = t 0 +3P 0 / 2, after one orbital period, the interval between the intermediate points is 1 second.

[0102] Situation 1: Use equal time intervals (commonly used construction methods for navigation ephemeris) and non-uniform intervals proposed by the present inv...

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Abstract

The invention provides a quick processing method suitable for large eccentricity ratio orbit dense ephemeris precision calculation. Aiming at large eccentricity ratio orbit calculation, the inventionprovides a new method for constructing interpolation base points through time transformation, the constructed non-uniform interpolation base points are matched with interpolation polynomial interpolation to obtain dense ephemeris, and the technical scheme can remarkably improve the calculation efficiency and precision. Based on a large-scale numerical experiment, the optimal universal numerical value of time conversion parameters corresponding to different orbit eccentricity ratios and various interpolation polynomials is 0.3. Besides, under the condition that the optimal pervasive numerical value is taken as the time transformation parameter, the Hermite interpolation polynomial is determined by comparing the calculation efficiency of various interpolation polynomials, and the method is agood method.

Description

technical field [0001] The invention belongs to the field of astrometry and celestial mechanics, and specifically solves the problem of insufficient timeliness in calculating the precise orbit of a large eccentricity target involved in the detection and cataloging of space targets through the rational use of high-precision numerical methods, and provides a method suitable for large An effective technical means with both high precision and fast processing for the calculation of eccentricity moving target catalogue. Background technique [0002] The cataloging and management of space objects involves complex orbit calculation work. When dealing with a large number of space objects, in addition to requiring the accuracy of orbit calculation to meet the needs of controlling the movement situation of the objects, it is also necessary to focus on the calculation efficiency. The minimum requirement for the efficiency of orbit calculation in cataloging is to ensure that the overall ...

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Application Information

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IPC IPC(8): G06F17/11G06F17/13G06F17/15
CPCG06F17/11G06F17/13G06F17/15G01S19/27B64G1/242B64G3/00G06F17/17
Inventor 徐劲戴志军
Owner ZIJINSHAN ASTRONOMICAL OBSERVATORY CHINESE ACAD OF SCI
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