High-precision ground trajectory repetitive orbit optimization method and system

Abstract

The invention provides a high-precision ground trajectory repetitive orbit optimization method and system. The method comprises steps of building a corresponding satellite orbit dynamics recursion model according to the analysis of a non-spherical perturbation order demand of an earth gravity field; giving a heavy rail interference orbit parameter under a J2 low-order gravity field according to ananalytic formula, and performing iterative calculation to obtain a correction parameter under J4 perturbation as an initial value of a high-precision ground trajectory repetitive orbit parameter adaptive setting algorithm; and according to the repeated track precision requirement, self-adaptive optimization setting of high-precision ground track repeated track parameters being carried out. The method solves problems that a traditional low-order gravity field orbit model is low in ground trajectory repetition precision, a high-order gravity field orbit model is high in nonlinearity, many in iterative correction parameters, incapable of being analyzed and solved and the like, and has more general engineering practicability.

Description

technical field [0001] The invention relates to orbit dynamics of an aerospace vehicle, in particular to a method and system for optimizing a repeating orbit of a high-precision ground trajectory. Background technique [0002] The track revisit characteristics of sub-satellite points are important indicators for the orbit design of earth observation satellites. Traditional satellite ground track maintenance does not require too high orbit return accuracy, and track deviations can range from a few kilometers to tens of kilometers without affecting Satellite mission. In recent years, with the sharp increase in imaging accuracy requirements, the limitations of existing regression orbit design methods have become increasingly apparent, especially for surveying and mapping tasks. In order to achieve accurate surveying and mapping and efficient mission planning, it is necessary to ensure the high precision of the ground track of the satellite reference orbit return. [0003] The...

AI Technical Summary

Problems solved by technology

In this method, the relationship between the sub-satellite point, the semi-major axis of the orbit, and the inclination function used for iterative correction only considers the earth's second-order gravitational field perturbation, which affects the regression accuracy; each iterative correction of eccentricity and perigee needs to be collected for 4 months Periodic data is averaged, which requires a large amount of calculation, which affects the iteration convergence speed; the obtained orbit regression accuracy can only reach the meter level, which affects engineering applications

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