Compensating Structure and Parameter Optimization for Attitude Control of a Flexible Spacecraft

摘要

A Feedback Double Path Compensating (FDPC) control structure is considered for the attitude control of a flexible spacecraft, where vibration modes and modelling errors are present. Parameter optimization is applied for finding the controller, so as to have optimized behavior for a high order model. The second-order FDPC controller was tested for the one axis attitude control of a space-craft with flexible appendages, whose dynamics was approximated by a fourteenth-order linear invariant model. The results are found to be satisfactory.