Modelling of Actuator Dynamics for Spacecraft Attitude Control

摘要

In this paper, we have investigated the dynamical behavior of various actuators for spacecraft attitude control using functional descriptions and theoretical frameworks. Based on this investigation, we have provided an alternative way of describing the actuator dynamics on a general form, both in terms of a general theoretical model and a first- and second-order linear approximation. The presented models are suitable for direct inclusion within a controller design study to enable increased robustness and precision of control.