Investigating the Effect of Event-triggered Control and Nonlinear Actuator Dynamics on Spacecraft Attitude Stabilization

This paper proposes a suitable controller for the stability and regulation of a rigid spacecraft in the presence of nonlinear actuator dynamics. The controller design for the system is a static feedback controller that generates the appropriate control signal with feedback from the angular velocity vector and the spacecraft position vector. The effect of nonlinear factors on the system and controller is evaluated and simulated in full detail. Moreover, in addition to considering nonlinear factors, a suitable controller is designed by considering environmental disturbances, and the system is stabilized under the influence of nonlinear factors, and environmental disturbances and convergence to the desired set point are validated. Finally, numerical simulation of the closed-loop system is evaluated to validate the theoretical results.