CONTROL OF FLEXIBLE SPACECRAFT.

摘要

This dissertation presents two separate theories on the automatic control of flexible spacecraft.; In the first chapter a method is presented for maneuvering a flexible spacecraft from one position to another while leaving an arbitrary number of bending modes inactive at the end of the maneuver. The method combines standard fixed-time LQG regulator control theory with a modal decomposition of a flexible body. Further features of the method are that it uses minimum control effort and that it can be converted to a feedback form to deal with random disturbances and parameter uncertainties. Several examples are given to demonstrate the efficacy of the method, and results from a hardware experiment are presented.; The theories presented in the second chapter are more theoretical in nature. What is derived is a way of applying optimal control theory to a system described by partial differential equations. Specifically, an optimal steady state regulator is designed for a simple example of a flexible spacecraft. In addition to describing the behavior of the spacecraft under the influence of the optimal control system, a means is shown to obtain a simply described distributed gain function to implement this optimal control.