Optimal Attitude Control of an Orbiting Satellite Containing Flexible Appendages.

摘要

This thesis investigated three methods for obtaining optimal control requirements for satellites having flexible appendages. A discrete method, modal method, and a new integral coordinate method for obtaining control requirements were examined. Mathematical formulation was performed on a satellite configuration consisting of a symmetrical rigid body with two flexible antennas extending in opposite directions along the spin axis. System equations of motion were derived using Hamilton's equations. Modern optimal control theory, involving the minimization of a quadratic cost functional and the numerical solution to the steady state matrix Riccati equation, was applied to the system. The results of this thesis indicate that the integral coordinate technique provides a valid and useful means of obtaining realistic estimates of control requirements for the class of satellites under consideration.