Precession control method for under-actuated satellite

Abstract

The invention discloses a precession control method for an under-actuated satellite. The method comprises the steps of: (1) determining an initial self-rotating shaft position of the under-actuated satellite by the adoption of an attitude sensor, and determining a direction and an amount of precession control according to a position of a target self-rotating shaft; (2) determining geometric relationship between an injection control moment and a precession control direction produced by each injection control engine, and selecting the injection control engine with the largest amount of the injection control moment in the precession control direction as a precession control engine; and (3) at the time of tz0+n*Ts+Ts / 2-Tp / 2, using the precession control engine to inject a pulse with a width of Tp so as to carry out precession control, and using the precession control engine to inject the pulse with the width of Tp so as to carry out precession control in every n self-rotation period Ts until the self-rotating shaft of a satellite reaches the position of a target rotating shaft. According to the method, the strategy of pulse modulation precession control is adopted, the operation is simple and convenient, and nutation produced by precession control can be reduced at the same time.

Description

technical field [0001] The invention relates to a satellite attitude control method. Background technique [0002] Precession control is generally used for spin-stabilized satellites. Many satellites use spin-stabilized methods to stabilize attitude, and their spin axis is perpendicular to the orbital plane. When a constant disturbing torque acts, its spin axis drifts at a constant velocity instead of accelerating. Spin stabilization is an attitude stabilization method that uses the fixed axis of the satellite when it rotates around the spin axis to keep the spin axis in the inertial space without external torque. When there is an external force, the angular momentum of the spin satellite The direction of the vector will precess at a certain angular velocity. When the instantaneous rotation axis does not coincide with the spin axis, the spinning satellite will nutate. In order to maintain the fixed axis of the spin axis, it is necessary to consume the energy of the satellit...

AI Technical Summary

Problems solved by technology

[0004] In the process of satellite precession control, if the satellite jet control is under-actuated control, if the method of full-drive precession control is still used, the control purpose will not be achieved, and even the safety of the satellite will be endangered.

Literature at home and abroad have mainly conducted a series of studies on all-actuated precession control. Although there are reports on the failure and rescue of in-orbit satellites at home and abroad, none of them involve underactuated jet precession control.

Images