This paper aims to present a multi-axis actuating approach to attenuate the bending and torsional vibration of the solar array through the reaction wheel (RW) actuators.
The motion equation of the solar array with the RW actuators is derived in modal coordinates for controller design. The reaction torques, induced by the speed change of the RW actuators, are controlled for vibration attenuation through the constraints on the actuators’ rotating speed. The proposed control approach is firstly verified with numerical simulation on the finite element model of a full-scale solar array. Experimental study of a simplified elastic plate model is subsequently performed for feasibility and validity investigation.
Both the numerical and experimental studies demonstrated the success of adopting RW as the actuator. Results from numerical simulation reveal that the vibration response peak can be reduced by 80% with 2% of mass increase by using the RW actuators.
It is demonstrated that the multi-axis actuating method using RW actuators has a great potential in vibration attenuation of the multi-panel deployable solar array.
An approach to reduce bending and torsional vibration of solar array based on RW actuators is investigated. Theoretical analysis, numerical simulation and experimental study are conducted to demonstrate the validity of the proposed vibration attenuation approach and its potential application in the spacecraft design.
