Control system of spacecraft solar array drive assembly actuator

Abstract

This paper deals with the issues of developing a control system of a spacecraft solar array drive assembly actuator that meets strict requirements for operation at the set angular accelerations and rotation velocities, under the influence of payload and disturbance forces. The work consists of developing a control system, its mathematical description, simulation and fabrication of an assembly prototype that meets the defined technical specifications. In the work, methods of mathematical and experimental investigation are applied. System mathematical simulation was carried out using the Matlab/Simulink applied software. As a result of the work, a structural diagram is proposed of the control system of a spacecraft SADA actuator of an operating follow-up system based on the set angular position that is calculated as required for operation at the defined angular accelerations and rotation velocities. The article presents the results of mathematical simulation of actuator operation, the results obtained during operation at the defined angular rotation velocity by a prototype SADA, the analysis and comparison of theoretical and practical results. Experimental investigation shows the achievement of the goal when developing the actuator control system, as well as rather exact matching of simulation and experiment results. The proposed control system can be used when designing and developing devices with similar technical specifications.