Low-orbit-satellite orbit prediction method based on atmospheric resistance model compensation

Abstract

The invention discloses a low-orbit-satellite orbit prediction method based on atmospheric resistance model compensation, and relates to the field of aerospace. The method includes the steps that S1, orbit determination is carried out on a satellite through the pseudo-range observed quantity of a satellite-borne GNSS receiver and ultra-rapid ephemeris issued by an IGS, and kinetic parameters of the satellite are obtained, wherein the kinetic parameters include the position, the speed, the CD, the CR and the piecewise constant experience acceleration parameters of the satellite; S2, the experience acceleration is modeled, then the model and a determinacy kinetic model compose a reinforcing type kinetic model, and finally the position and the speed of the satellite at the orbit determination final epoch are used as initial values to carry out orbit predicting. According to the method, it is only required that the pseudo-range observed quantity of the satellite-borne receiver exists; in addition, achievement is easy, and the experience acceleration obtained after orbit determination is fitted and then can be applied to orbit predicting; meanwhile, the method has certain universality and operability, the errors of an atmosphere resistance model are compensated, predicating accuracy is improved, and the method is applied to in-orbit high-accuracy navigation.

Description

technical field [0001] The invention relates to the aerospace field, in particular to a low-orbit satellite orbit prediction method based on atmospheric resistance model compensation. Background technique [0002] At present, the orbit prediction accuracy of low-orbit satellites is not high, especially the orbital (tangential) prediction error deteriorates rapidly with time, the main reason is that it is difficult to establish a high-precision atmospheric drag model. The existing technologies all focus on the improvement of the atmospheric resistance model itself, and it is expected to improve the prediction accuracy by adjusting one or two coefficients in the atmospheric resistance model or by improving the atmospheric density model. However, the existing methods distort the physical meaning of the dynamic parameters in the atmospheric model and do not significantly improve the prediction accuracy, so they are not universal. Contents of the invention [0003] The purpose...

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Problems solved by technology

[0003] The purpose of the present invention is to provide a low-orbit satellite orbit prediction method based on atmospheric drag model compensation, which estimates the unmodeled force during the period of existing GNSS observations, and uses it for orbit prediction after modeling, thereby solving the problem There are the aforementioned problems in the technology

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