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Satellite orbit determination method for eccentricity of frozen orbit

A technology for satellite orbit determination and method, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of simple calculation process, complex calculation, low precision, etc., to solve the problems of low precision, avoid complex operations, improve The effect of stability

Active Publication Date: 2014-06-11
BEIHANG UNIV
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Problems solved by technology

[0007] In order to solve the defects of complex calculation and long time when using high-precision calculation method in the process of determining the eccentricity of the original frozen orbit, or simple calculation process and low precision when using low-precision calculation method, the present invention proposes A satellite orbit determination method based on the eccentricity of the frozen orbit

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  • Satellite orbit determination method for eccentricity of frozen orbit
  • Satellite orbit determination method for eccentricity of frozen orbit
  • Satellite orbit determination method for eccentricity of frozen orbit

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Embodiment 1

[0103] Take the satellite that was put into orbit at 12:00 AM on July 1, 2006 as an example, the lifespan is 10 years (ie T=10), the flat root of the orbital eccentricity is 0.001 (ie Ae=0.001), and the flat root of the semi-major axis of the orbit is 6870.713 kilometers (that is, Aa=6870.713 kilometers), the flat root of the argument of perigee is 90° (that is, Aω=90°), the flat root of the argument of latitude is 0° (that is, Au=0°), and the flat root of the orbital inclination is 97.3736° (that is, Ai=97.3736°), and the flat root of the right ascension of the ascending node is 0° (that is, AΩ=0°).

[0104] Using the freezing eccentricity determination method of the present invention to design satellite orbits includes the following steps:

[0105] Set the flat root of the eccentricity to (i.e. Ae = 0.0011);

[0106] Substituting Aa=6870.713 kilometers into the conversion formula from flat root to instantaneous root, the instantaneous root number Ba=6861.219 kilometers of...

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Abstract

The invention discloses a satellite orbit determination method for the eccentricity of a frozen orbit. The method comprises the following steps: setting an initial orbit parameter; converting the mean element of an orbit element to an instant element; calculating the orbit element within the service life under the assistance of STK (Satellite Tool Kit) software; performing extreme value processing to extract the eccentricity, and updating the frozen orbit. By adopting the method provided by the invention, the defects of complex calculation and long time during calculation by adopting a high-accuracy calculation method or simple calculation process and low accuracy in a low-accuracy calculation method during determination of the eccentricity of the original frozen orbit are overcome.

Description

technical field [0001] The invention relates to a method for determining a satellite orbit, more particularly, a method for determining the eccentricity of a frozen orbit. Background technique [0002] During the satellite's in-orbit flight, the earth's aspherical perturbation will bring short-period and long-term changes in the orbital eccentricity and argument of perigee: the short-period changes are determined by the latitude of the satellite and cannot be eliminated by proper orbit design ; The long-term term of the argument of perigee will cause the orbital arch line to precess continuously in the equatorial plane (taking the sun-synchronous orbit at a height of 645km as an example, the precession period is about 100 days), which will have a negative impact on satellite applications. Track design is eliminated. [0003] The change of orbital eccentricity is extremely important, and it is one of the key factors restricting the orbital life of various (different heights)...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 徐明魏延汪作鹏徐世杰
Owner BEIHANG UNIV
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