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Nonsingular orbital elements-based 14 parameter broadcast ephemeris satellite position estimating method

A technology for broadcasting ephemeris and satellite positions, applied in the field of satellite navigation, can solve the problems of singularity of legalized matrix, inconvenient unified processing, inability to fit broadcast ephemeris parameters, etc., and achieve the effect of saving communication resources

Inactive Publication Date: 2018-02-02
TSINGHUA UNIV
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Problems solved by technology

However, according to the definition of orbital elements, both small eccentricity and small inclination will cause some ambiguities in the definition of orbital elements. The singularization matrix makes it impossible to fit the broadcast ephemeris parameters
At present, in order to solve the above problems, the method adopted by the Beidou GEO satellite broadcast ephemeris user algorithm model is to perform 5° coordinate rotation. However, this method will cause the GEO satellite broadcast ephemeris user The algorithm model is inconsistent with MEO and IGSO, and it is not convenient for unified processing

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  • Nonsingular orbital elements-based 14 parameter broadcast ephemeris satellite position estimating method
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  • Nonsingular orbital elements-based 14 parameter broadcast ephemeris satellite position estimating method

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Embodiment Construction

[0040] The present invention will be described in detail below in conjunction with the embodiments.

[0041] The invention provides a 14-parameter broadcast ephemeris satellite position estimation method based on the second type of non-singularity root.

[0042] The 14 parameter broadcast ephemeris model of the present invention based on the second type no-singularity orbital element is designed as:

[0043]

[0044] Among them, t oe It is the reference time of the broadcast ephemeris; is the rate of change of λ, Respectively h, k rate of change, C rc Amplitude of cosine harmonic correction term representing satellite orbit radius, C rs is the amplitude of the sinusoidal harmonic correction term of the satellite orbit radius, C uc is the amplitude of the cosine harmonic correction term of true longitude, C us is the amplitude of the sinusoidal harmonic correction term of true longitude; (a, ξ, η, λ, h, k) is the second type of non-singularity variable, a is the semi...

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Abstract

The invention discloses a nonsingular orbital elements-based 14 parameter broadcast ephemeris satellite position estimating method. The method can be applied to satellite tracks small in eccentricityratios and track inclination angles; via adoption of the method, MEO, IGSO and GEO satellite broadcast ephemeris user algorithms can be unified. The method comprises the following steps: a new secondtype nonsingular orbital elements-based 14 parameter broadcast ephemeris model is built; based on the model, a new broadcast ephemeris satellite position estimating method is put forward; compared with technologies of the prior art, the method disclosed in the invention is advantageous in that ephemeris parameter are reduced by 2, and navigation satellite communication resources can be saved. In the model put forward in the invention, eccentricity and track inclination angle parameters are directly adopted; a problem of matrix singularity which occurs during broadcast ephemeris parameter fitting processes when satellites run in orbits small in eccentricity ratios and track inclination angles, and the method can be applied to the satellite tracks small in eccentricity ratios and track inclination angles; MEO, IGSO and GEO satellite broadcast ephemeris user algorithm models can be unified.

Description

technical field [0001] The invention relates to the technical field of satellite navigation, in particular to a 14-parameter broadcast ephemeris satellite position estimation method based on the second type of non-singularity root. Background technique [0002] The broadcast ephemeris is an important part of the navigation message of the satellite navigation system, and it is the final expression form of the precise orbit of the satellite broadcast to the user, providing accurate satellite position information for the user's navigation and positioning. The broadcast ephemeris parameter model and accuracy directly determine the performance of user navigation and positioning. At present, the broadcast ephemeris of the Beidou, GPS and Galileo satellite navigation systems are all based on the classic six Kepler orbital elements, plus the reference time of the ephemeris, the harmonic coefficient of the orbital perturbation, and the perturbation amount changing with time, It cons...

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Application Information

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IPC IPC(8): G01S19/27
CPCG01S19/27
Inventor 谢小刚陆明泉
Owner TSINGHUA UNIV
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