LIAPUNOV OPTIMAL-CONTROL LAWS FOR FLEXIBLE STRUCTURES MANEUVER AND VIBRATION CONTROL
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Optimization of control laws for maneuvering of a flexible spacecraft model based upon Liapunov function type control laws are presented. The basic idea is to design a control law using a Liapunov function and augment the control law by some optimality condition for a particular control objective. Our approach of designing the optimal control law consists of two stages. The first stage is to find a stabilizing control law as a function of design parameters which are usually feedback gains. In the second stage, the control law is reshaped with the design parameters to satisfy an optimal criteria. Two kinds of control schemes - constant gain feedback and tracking type control laws are discussed with different perspectives on the optimization. The Optimization scheme used in this work is a sequential nonlinear programming algorithm which uses a homotopy method to sweep through a sequence of minimum norm design parameter changes. The outcomes of our results show how our control objective is improved by optimizing the parameters appearing in the control laws.
SPACEFLIGHT MECHANICS 1991, PTS 1 AND B
author list (cited authors)
BANG, H., & JUNKINS, J. L.
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