An autonomous control method for geo-orbit satellites using only angle information

Abstract

The invention provides an autonomous control method for a GEO (Geosynchronous) orbit satellite by using angle information only. The method comprises the steps of correcting the orbit deviation of a star sensor and an infrared earth sensor; calculating the projection of a geocentric unit vector in an inertial equatorial coordinate system; calculating longitude and latitude deviation between the current satellite and an ideal fixed point, and using a result as a filter observed quantity; using a C_W equation as a system equation and estimating the right ascension and the declination of the satellite by using a Kalman recursion method; determining the reference coordinate system of the current attitude control of the satellite by using the result; calculating the attitude deviation of the satellite by using the information of the star sensor again and using the attitude deviation as system control input; and repeating the steps to realize the autonomous continuous navigation and the autonomous attitude control of the satellite. By conducting the autonomous on-star resolution and the autonomous attitude control of the position of a spacecraft through on-star sensor observation only, the problems that a measurement and control network cannot be globally distributed and the measurement and control cost is high are solved, the autonomous running of the satellite is realized and the survivability of the satellite is improved.

Description

technical field [0001] The present invention relates to on-board autonomous navigation and autonomous control technology, which is an autonomous control technology for geosynchronous orbit (GEO orbit) satellites, and specifically relates to an autonomous control method for GEO orbit satellites using only angle information. Background technique [0002] High-orbit satellites are mainly geostationary orbit satellites. In the synchronous orbit stage, such satellites usually need to conduct multiple orbit measurements on the ground to determine the satellite orbit and add orbital parameters to realize on-board attitude control. This kind of navigation has always relied on ground orbit determination technology. The disadvantage of this method is that it is highly dependent on the ground. To achieve high-precision orbit forecasting, multiple ground stations are required for long-term observation. With the development of space technology in China, high-orbit satellites The number o...

AI Technical Summary

Problems solved by technology

This kind of navigation has always relied on ground orbit determination technology. The disadvantage of this method is that it is highly dependent on the ground. To achieve high-precision orbit forecasting, multiple ground stations are required for long-term observation. With the development of space technology in China, high-orbit satellites The number of GEO satellites is increasing rapidly, especially overseas GEO satellites, which have higher and higher requirements for ground stations and fast positioning, so there are more and more demands for autonomous positioning and autonomous attitude control of high-orbit satellites

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