Orbit estimation method of space vehicle in active period

Abstract

The invention provides an orbit estimation method of a space vehicle in an active period. The method utilizes a Beidou satellite to acquire information of an objective space vehicle at the initial position in the active period; simplified motion equations and decomposition equations of the objective space vehicle in the active period are built, so that a motion equation model of the orbit of the space vehicle and a represented estimation model, based on a third order polynomial, of the orbit of the space vehicle are built; the built estimation model of the orbit is solved, so that an estimation position and estimation speed of any point in time of the objective space vehicle in the active period are obtained. The method has the advantages that more accurate, more reliable and more independent orbit estimation for the space vehicle in the active period can be realized; better information foundation can be provided for judgment of the category and the flight intention of the objective space vehicle; the method is simple and practicable; and the practicability is strong.

Description

technical field [0001] The invention belongs to the technical field of spacecraft orbit estimation, in particular to a method for orbit estimation of an active segment of a spacecraft. Background technique [0002] The Beidou satellite navigation system is a global satellite navigation system independently developed and operated independently in my country. It can provide users with all-weather, all-time high-precision and high-reliability positioning services. The Beidou satellite navigation system consists of three parts: the space terminal, the ground terminal and the user terminal. The Beidou satellite navigation system has great strategic and economic significance for promoting the development of my country's satellite navigation and positioning business and meeting the needs of my country's military and national economy. However, the Beidou satellite navigation system can only locate the target object from time to time, but cannot perform positioning and orbit estimat...

AI Technical Summary

Problems solved by technology

[0005] For the traditional spacecraft orbit estimation method, in the process of obtaining the initial position information of the target spacecraft during the active flight period, the traditional detection method generally uses infrared optical detectors to detect and obtain, and it only receives the target The infrared radiation information can be oriented but not range-finding, and is easily affected by climate and cloud interference, and its reliability is not good enough, and the initial position information obtained by it is the position information on the observation coordinate system moving with the detection satellite, so it needs Carry out coordinate transformation from the observation coordinate system to the basic coordinate system, the transformation is complex and the amount of calculation is large

In addition, the traditional spacecraft orbit estimation method still has some disadvantages, such as inaccurate initial position information, too many variables to be determined in the orbit estimation process, complex calculation, and insufficient estimation accuracy.

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