Attitude control system for space vehicle and method thereof

Abstract

The invention discloses an attitude control system for space vehicle and a method thereof. The control system has only one biased momentum wheel, one set of tri-axial magnetic torquer and one attitude controller loaded with algorithm. The method comprises a step of rate damping controlling, a step of initially capturing controlling and a step of stationarity controlling. At the rate damping stage, geomagnetism change is used to control the magnetic control of three passages of a satellite by B-dot; at the initially capturing stage, the magnetic control is realized, PD control is performed by pitching and the passages are rolled and yawed to carry out nutation and precession composite control; at the stationarity controlling stage, the magnetic control is realized, PD control is performed by pitching and the passages are rolled and yawed to carry out nutation and precession composite control. The capturing stage and the stationarity controlling stage fully depend on magnetic torquer to perform positive magnetic control, thereby changing which a satellite only uses a magnetic torquer to carry out unload of the momentum wheel or auxiliary magnetic control, so as to refine system configuration to further improve reliability of the system. Momentum of a satellite is biased to rotate on the ground, so as to ensure stable separation of the satellite without performing air injection control. Therefore, the magnetic torquer can be used for realizing fast and stable initial rate damping.

Description

technical field [0001] The invention belongs to the technical field of spacecraft control, and relates to an attitude control system and method, in particular to a highly reliable and low-cost attitude control system and method suitable for micro-satellites. Background technique [0002] Modern micro-satellites have a short development cycle, low cost, and flexible maneuverability. They can carry multiple satellites with one arrow, and have broad application prospects. At present, they have become a hot spot in the development of space technology in the world. As one of the important technologies of micro-satellite technology, the main task of attitude control is to control the attitude of the satellite to ensure that the attitude of the satellite meets the requirements of the working state. It is possible to save cost, reduce volume and weight, reduce power consumption, and realize long life. [0003] In order to ensure the high performance of the satellite attitude contro...

AI Technical Summary

Problems solved by technology

Among them, the combination of gravity gradient rod and magnetic torque device and the combination of gravity gradient rod, bias momentum wheel and magnetic torque device have simple structure, reliable and stable system, and low cost, but the control accuracy is too low, generally above 3 degrees, only It is suitable for satellites that do not require high attitude control performance; the combination of flywheel and magnetic torquer, the flywheel implements three-axis control, and the magnetic torquer assists unloading. It is a typical high-precision control system configuration used in China at present. It depends on the characteristics of the flywheel, and on the other hand depends on the characteristics of the attitude determination system. The performance of the flywheel is good, the performance of the attitude determination system is good, and the control accuracy is high. However, such a system has complex configuration, poor reliability and stability, many redundant backups, and high cost.

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