Sidereal hour angle based attitude control method and system

Abstract

The invention discloses a sidereal hour angle based attitude control method. The method comprises S1) a Julian century corresponding to present onboard time of a satellite is obtained; S2) a sidereal hour angle is calculated; S3) an attitude conversion quaternion between a track coordinate system and an inertia coordinate system is obtained by calculation; S4) an attitude quaternion, relative to a track system, of a satellite body system is obtained by calculation; S5) an Euler angle of the satellite body system in a pitching-rolling-yawing turn order is calculated, and an attitude determining angle based on star sensor information is obtained; S6) a PD control algorithm is executed, and a control moment is obtained by calculation; and the steps S1) to S6) are repeated to realize autonomous continuous navigation and attitude control of the satellite. According to the invention, autonomous navigation and attitude control for the aircraft position are carried out only by calculating the sidereal hour angle, the problem that ground or GNSS measuring track information cannot be obtained in an abnormal state is solved, autonomous management of the satellite is realized, and the reliability and survival capability of the satellite are improved.

Description

technical field [0001] The invention relates to autonomous control technology of satellites, in particular to an attitude control method and system based on sidereal time angle. Background technique [0002] In the geosynchronous orbit stage, in order to determine the satellite orbit and realize on-board attitude control for geostationary orbit satellites, there are usually two methods. One requires the ground to conduct multiple orbit measurements to determine the satellite orbit and note the orbit parameters. This type of navigation needs to rely on ground orbit determination. The disadvantage of this technology is that it is highly dependent on the ground. To achieve high-precision orbit prediction, multiple ground stations are required for long-term observation; the other needs to receive real-time orbit determination information from space-based navigation systems such as GPS. The receiver that leaks GPS signal for navigation is verified. With the development of my cou...

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Problems solved by technology

[0002] In the geosynchronous orbit stage, in order to determine the satellite orbit and realize on-board attitude control for geostationary orbit satellites, there are usually two methods. One requires the ground to conduct multiple orbit measurements to determine the satellite orbit and note the orbit parameters. This type of navigation needs to rely on ground orbit determination. The disadvantage of this technology is that it is highly dependent on the ground. To achieve high-precision orbit prediction, multiple ground stations are required for long-term observation; the other needs to receive real-time orbit determination information from space-based navigation systems such as GPS. The receiver that leaks GPS signal for navigation is verified

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