Satellite borne rapid multi-step integration method for track in real-time precise orbit determination

Abstract

The invention relates to the technical field of navigation satellite application, in particular to a satellite borne rapid multi-step integration method for a track in real-time precise orbit determination. The method comprises the following steps: selecting an integration window, and then smoothening the motion state of all epoch satellites in the whole window by virtue of the observed value at an epoch position at the tail end of the window; transferring matrix integration according to the updated motion state and the given state of all the epoch satellites in the window to calculate the new motion state of the epoch satellites; and finally updating a window epoch, i.e. moving backwards one epoch from the initial epoch of the window, and then smoothening the motion state of all the epoch satellites in the smoothening window by means of updating the observed information on the epoch at the tail end of the window. In the method, a multi-step method is adopted while updating the epoch and a single-step method while intersecting the epoch, thus achieving high numerical precision, better stability and smaller integral right-function calculation, transferring matrix information by the given state, avoiding updating state for matrix transfer while updating the state, reducing times for calculating integral right function, effectively improving calculating speed, transforming window length according to different calculation accuracy, and ensuring integral precision.

Description

technical field [0001] The invention relates to the technical field of navigation satellite applications, in particular to a space-borne fast multi-step integration method for real-time precise orbit determination of mid-orbit. Background technique [0002] In order to obtain high-precision satellite orbit and state transition matrix in precise orbit determination, it is necessary to use numerical integration algorithm to solve the satellite motion equation. The main integration algorithms currently used in orbit determination are Runge-Kutta single-step method and Adams multi-step method. The Runge-Kutta method indirectly refers to the Taylor expansion, using the interval [t i t i+1 ] on the linear combination of several right functions f to replace the derivative of f, and the corresponding combination coefficients are determined by the Taylor expansion. Since the Runge-Kutta method needs to solve the right function value at different times between the current epoch an...

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Problems solved by technology

[0004] In view of the above-mentioned technical problems, the purpose of the present invention is to provide a real-time precise orbit determination orbit onboard fast multi-step integration method to solve the technical problem that the orbit integration speed is too slow in real-time satellite orbit determination, so as to realize fast orbit integral

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