Award Date

1-1-1999

Degree Type

Thesis

Degree Name

Master of Science (MS)

Department

Electrical Engineering

First Committee Member

Sahjendra N. Singh

Number of Pages

62

Abstract

In this thesis, it is exhibited that although, the aeroelastic system is not input-state feedback linearizable, a partial linearized representation of the system in dimension three can be obtained. Based on this partially linearized representation, a new inverse controller was derived and simulation results show that control of pitch angle and plunge displacement can be accomplished; Then, adaptive output feedback control law is examined. For the synthesis of the controller, it is assumed that only pitch angle and plunge displacement are measured. A canonical state variable representation of the system is derived for the reconstruction of the state variable. According to the new state variable form of the aeroelastic system, filters are designed and an estimate of states are constructed using a linear combination of the states of the filters. Based on a backstepping design technique, adaptive control laws for the control of pitch angle and plunge displacement are derived. Simulation results are presented to show the adaptive state regulation capability of the control system. Finally, reduced order filters are designed to obtain the unmeasured state variables and new adaptive control laws are obtained. In the close-loop system, the state vector is shown to converge asymptotically to zero.

Keywords

Adaptive; Aeroelastic Control; Feedback; Linearization; Nonlinear; Systems

Controlled Subject

Electrical engineering

File Format

pdf

File Size

1617.92 KB

Degree Grantor

University of Nevada, Las Vegas

Language

English

Permissions

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Identifier

https://doi.org/10.25669/f817-qxsr


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