Proportional-derivative-acceleration controller design for spacecraft with flexible appendages

Abstract

A design methodology for certain third order systems is demonstrated using the root locus method, and extended and applied to a simple SISO model of a single axis of a flexible spacecraft with sensor and actuator dynamics included. The controller, including derivative and acceleration feedback, is tuned for the flexible spacecraft system to improve its steady state and transient performance. A numerical example then demonstrates the features of the controller.