Calculation method of orbit control thrust fitting coefficient based on summer least square

Abstract

The invention provides a calculation method of orbit control thrust fitting coefficients based on summer least squares. The calculation method includes the steps of comprehensively analyzing the correlation among speed increment, actual speed increment and orbit control thrust coefficients of previous orbital control theories, characterizing thrust fitting coefficients by using summer least squares estimation and creating a model that mimics behavior of real systems, and predicting future evolution of system output with current measurable system inputs and outputs. With historical orbit control data utilized as an input, and the actual thrust fitting coefficients calculated by using Xia's method of generalized least squares,the calculation method of the orbit control thrust fitting coefficients based on the summer least squares has various advantages such as high calculation efficiency and no need for repeated data filtering Furthermore, with iteration to eliminate deviation in least squares trajectory, the calculation method is relatively simple and has high prediction accuracy.

Description

technical field [0001] The invention relates to the field of measurement, control and management of in-orbit spacecraft, and is suitable for fitting calculation of thrust coefficient during orbit control of near-earth satellites. Background technique [0002] Due to the orbit attenuation caused by atmospheric resistance, the near-Earth satellite's ground trajectory will gradually deviate from the set trajectory. It is necessary to periodically maintain the orbit through the orbit control thruster so that the satellite's ground trajectory always meets the design requirements of the trajectory network. The thrust of the satellite orbit control thruster is a polynomial function with the pressure of the propellant tank as the independent variable, and its coefficient is a binding constant, which remains constant throughout the life of the satellite. With the increase of satellite orbit control times, the pressure of the propellant tank keeps decreasing, and there is a large erro...

AI Technical Summary

Problems solved by technology

[0003] The traditional orbit control speed increment calculation only uses the calibration coefficient of the previous thruster as the calculation basis, and the thrust coefficient remains unchanged. It does not effectively use the previous orbit control data for optimal calculation, resulting in an unmeasurable error between the theoretical speed increment and the actual speed increment. , which brings certain difficulties to the formulation of orbital control strategies

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