Satellite fast high-precision extrapolation method of great-eccentricity track

An eccentricity and high-precision technology, applied in the field of satellite orbits, can solve the problem of large fitting errors of orbit extrapolation algorithms on satellites

Active Publication Date: 2013-01-16
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0003] The technical problem of the present invention is: to overcome the deficiencies of the prior art, to propose a fast and high-precision extrapolation method on a large eccentricity orbit, and to solve

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  • Satellite fast high-precision extrapolation method of great-eccentricity track
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  • Satellite fast high-precision extrapolation method of great-eccentricity track

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[0038] Such as figure 1 As shown, the specific implementation of the present invention includes the following steps:

[0039] (1) Solve the X, Y, Z three-axis position difference between the precision orbit of the large eccentricity elliptical orbit and the two-body orbit on the ground, and then use the Chebyshev polynomial fitting method to fit the Chebyshev polynomial coefficients;

[0040] Chebyshev polynomial fitting is to fit a function according to the given data to minimize the sum of variance between the function value at a given point and the given value, and the function is composed of Chebyshev polynomial as the basis function The function.

[0041] The precise orbit refers to the actual orbit of the satellite, which is provided by ground orbit measurement. The two-body orbit refers to the ideal orbit of the satellite under the gravitational force of the center of the target celestial body, which is calculated by theory; the initial value of the two-body orbit and the prec...

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Abstract

The invention relates to a satellite fast high-precision extrapolation method of a great-eccentricity track. A task track of a martian detector is an elliptic track with great eccentricity (e is greater than 0.6), a numerical integration method is adopted, and in order to realize the high-precision track calculation, the consideration of higher-order martian shape perturbation and the influence of other perturbation factors is needed, so the calculation quantity is greater, and the numerical integration method can be interrupted when a satellite computer resets or is switched; an analytical method is only applicable to the elliptic track with smaller eccentricity (e is smaller than 0.6); and the detector position provided by a precise track is utilized for fitting the Chebyshev multinomial coefficient, so greater fitting errors can be brought. The satellite fast high-precision extrapolation method has the advantages that the position difference of the precise track and the two-body track is introduced, the position difference is utilized for fitting the Chebyshev multinomial coefficient, the calculation problem of the satellite track of the elliptic track with great eccentricity can be perfectly solved, the calculation quantity is small, and in addition, the precision is high.

Description

technical field [0001] The invention relates to an on-board method for a large eccentricity orbit, and belongs to the technical field of satellite orbits. Background technique [0002] The motion trajectory of a spacecraft in space is called the orbit of the spacecraft. Through high-precision extrapolation calculations, the motion state of the spacecraft at any time in the past, current, and future periods can be obtained. The Mars probe is in interstellar flight, with a flight distance of up to 400 million kilometers. Compared with the earth satellite and the moon probe, the Mars probe faces problems such as long distance between the star and the ground, large time delay, and long-term sun transit. The Mars probe is independent of GNC Sexuality puts forward higher demands. Therefore, on-board high-precision orbit calculation and orbit extrapolation are very important. There are two main methods for solving satellite orbit dynamics equations: numerical method and analytica...

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Application Information

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IPC IPC(8): G01C21/20
Inventor 黄翔宇胡少春王大轶张斌
Owner BEIJING INST OF CONTROL ENG
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