A real-time trajectory improvement method for spacecraft based on pseudo-relative motion

Abstract

The invention provides a spacecraft real-time orbit improving method based on pseudo relative movement, comprising the following steps: getting relative movement analytical expressions under the condition of perturbation / no perturbation by solving relative movement dynamics models of a spacecraft under the condition of perturbation / no perturbation respectively; making the relative movement analytical expressions correspond to orbit drift data, processing the orbit drift data by use of a Fourier transform method, and calculating the initial position error and velocity error of the spacecraft; and finally, getting the real-time position vector and velocity vector of the spacecraft through inversion. By using the method, the orbit determination accuracy can be improved by nearly one order of magnitude on the basis of the initial orbit determination technology. The method is of universal adaptability. The orbit of a circular / nearly circular spacecraft can be improved by using a CW equation and an improved equation taking perturbation into consideration, and the orbit of an elliptical spacecraft can be improved by using a Lawden equation and a transform thereof taking perturbation into consideration.

Description

technical field [0001] The invention belongs to the field of orbit determination of spacecraft, in particular to a method for improving real-time orbit of spacecraft based on pseudo relative motion. Background technique [0002] Spacecraft orbit determination is the process of estimating the spacecraft orbit using statistical principles for the spacecraft motion state data that contains measurement errors. Through orbit determination, the motion state of the spacecraft at any time in the past, current and future period can be obtained. [0003] According to whether to use the mechanical model of the perturbed force of the spacecraft and the relationship with the mechanical model, the orbit determination method can be divided into kinematic orbit determination, dynamic orbit determination and simplified dynamic orbit determination; according to the data processing strategy, it can be divided into batch Processing method and sequential recursion method; according to the lengt...

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide a real-time orbit improvement method for spacecraft based on pseudo-relative motion in order to solve the technical problem of low measurement accuracy of existing spacecraft orbit determination methods

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