Prediction method for satellite orbit

Abstract

The invention provides a prediction method for a satellite orbit. The prediction method comprises the following steps: obtaining a precise satellite post orbit in N hours in the past, obtaining an initial state of the satellite; calculating a satellite stress parameter; calculating the first prediction orbit quantity of the satellite in M hours in the future according to the satellite stress parameter; calculating an orbit quantity correction coefficient according to the precise satellite post orbit in N hours in the past; correcting the first prediction orbit quantity according to the orbit quantity correction coefficient, and obtaining the correction orbit quantity; calculating the orbit state by using the correction orbit quantity to obtain a first prediction orbit state; calculating an initial state correction coefficient of the satellite according to the precise satellite post orbit in N hours in the past; correcting the first prediction orbit state according to the initial state correction coefficient, and obtaining the predicted satellite orbit state. The technique disclosed by the invention can be applied to prediction of the satellite orbit; the requirement of real-time orbit determination of navigating and positioning satellites based on the prediction method can be met.

Description

technical field [0001] The invention relates to a satellite orbit prediction method, in particular to a precise orbit prediction method suitable for low-orbit satellites, and belongs to the technical field of aerospace orbit dynamics. Background technique [0002] In recent years, LEO satellite navigation is attracting more and more attention. Compared with the existing global navigation satellites, low-orbit satellite navigation has three major advantages: under the same transmission power, the lower path loss brings a receiving power gain of more than 20dB to ground users; the satellite viewing angle changes quickly, which is conducive to Quickly and accurately solve the carrier phase integer ambiguity; adapt to the development trend of ubiquitous navigation capabilities. [0003] A basic problem of LEO satellite navigation is real-time orbit determination. In the field of real-time orbit determination of low-orbit satellites, the most common means is to install Global N...

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Problems solved by technology

[0004] However, the disadvantage of this method is that there are errors in the real-time orbit determination of the global navigation satellite system itself, and there are also errors in the clock, which leads to the real-time positioning accuracy of the low-orbit satellite onboard receiver to be greater than 6 meters, and low-orbit navigation enhancement usually requires The real-time orbit determination accuracy of low-orbit satellites is even better than 1 meter, which leads to inaccurate prediction of satellite orbits

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