Periodic disturbance torque identification and compensation method

Abstract

The invention provides a periodic interference torque identification and compensation method, which is used for phase identification and torque compensation of the periodic interference torque received by the satellite, applying a control torque with a fixed amplitude and a known period to the satellite, and compensating the moment on the satellite. The flywheel sends a feedforward compensation torque command to arbitrarily specify the initial phase of the compensation torque, including: measuring the satellite angular velocity in real time and extracting the angular velocity fluctuation range; when the angular velocity fluctuation range is greater than the first preset threshold, it is determined that phase shift control is required , carry out phase scanning with the initial phase as the starting point, during the phase scanning process, update the feedforward compensation torque according to the current phase; when the angular velocity fluctuation range is reduced to the second preset threshold, it is determined to end the phase movement control, and the current phase is For the disturbance torque phase, the feedforward compensation torque is updated according to the disturbance torque phase. The invention can realize the identification and compensation of the periodic interference moment of the satellite, and improve the control precision of the satellite.

Description

technical field

[0001] The invention relates to the technical field of spacecraft, in particular to a periodic disturbance torque identification and compensation method. Background technique

[0002] With the continuous development of space missions, satellites have more and more functions, and the control system design has higher and higher requirements for satellite control accuracy and attitude stability. For some large rotating parts on the satellite, when the satellite rotates at high speed, due to the existence of the offset of the center of mass, the satellite will be subjected to periodic disturbance torque, which will affect the attitude stability of the satellite to a certain extent. At the same time, if the frequency of the interference moment is close to some frequencies of the flexible attachment on the satellite, it may cause the vibration of the flexible attachment, which will bring greater interference to the satellite.

[0003] Therefore, it is necessary to...

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