The Attitude Control of Flexible Spacecraft

Abstract : This thesis details the design of the Naval Postgraduate School's Flexible Spacecraft Simulator and the first attempts at simulation and control of the model. The effect of flexible structures on the attitude control spacecraft has been a topic of research for many years. Only recently has the technology to actually test models and theory on the ground been available. At the Naval Postgraduate School, an experimental testbed for research into this area has been contracted. This facility has a model of a satellite with a flexible arm floating on air pads to eliminate the effects of friction. A mathematical model of the system has been constructed and simulations of various maneuvers have been run, utilizing proportional-derivative (PD) control as well as a Linear-Quadratic-Gaussian (LQG) compensator. Results show that both PD and LQG work well for station keeping, but that the LQG compensator is better for slewing the arm.