Method for determining relative adjoint orbit of space target

Abstract

The invention relates to a method for determining a relative adjoint orbit of a space target and belongs to the technical field of aerospace deep space exploitation. The method for determining the orbit state at the current moment comprises the following steps: (1) carrying out the recursion for a predicted value of the orbit state at an arbitrary moment according to an orbit dynamics equation, btaining a predicted observed quantity and further obtaining a difference value between a real observation value and the predicted value; (2) working out solutions of a system of linear equations by utilizing an observation equation and the difference value obtained in the step (1), thus obtaining an orbit state estimated deviation solution set; (3) carrying out increasing arrangement on the solutions obtained in the step (2) according to numerical values, and eliminating the solutions with the difference of two adjacent items greater than a measurement error limit; (4) determining the orbit state estimation deviation to be a middle item in the set obtained in the step (3) if the solution number of the set is an odd number, and determining the orbit state estimation deviation to be an average value of two continuous middle items in the set if the solution number of the set is an even number; (5) determining the orbit parameter estimation value at the current moment to be the sum of the orbit state predicted value and the orbit state estimation deviation. By adopting the method, the interference of a complicated dynamics model and noise can be alleviated.

Description

technical field [0001] The invention relates to a method for determining the orbit of a space target relative to an accompanying flight, and belongs to the technical field of aerospace deep space exploration. Background technique [0002] With the increasing number of deep space exploration missions, orbiting and accompanying spacecraft to observe target celestial bodies has become an important task and subject for future deep space scientific exploration. If the spacecraft has captured the target celestial body, but has little knowledge of its various information, it is necessary to use accompanying flight detection to determine the position, velocity, attitude and other parameters of the spacecraft relative to the target celestial body. In order to successfully complete the scientific investigation mission, the orbit keeping and control of the spacecraft accompanying the detection requires high orbit determination accuracy. The spacecraft ensures high orbit determination ...

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to solve the problem that the existing method for determining the orbit of the space target relative to the accompanying flight cannot guarantee high-precision orbit determination when there is interference from other noise information errors and the dynamic characteristics around the target celestial body are complex, and to provide a space The method of determining the orbit of the target relative to the accompanying flight. This method determines the orbit by calculating the median point of the orbit parameters, which can reduce complex dynamic models and noise interference.

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