Award Date

1-1-1991

Degree Type

Thesis

Degree Name

Master of Science (MS)

Department

Electrical and Computer Engineering

First Committee Member

S. N. Singh

Number of Pages

123

Abstract

We treat the question of large rotational maneuver and vibration stabilization of NASA Spacecraft Control Laboratory Experiment System (SCOLE). The mathematical model of SCOLE System includes the dynamical equations for rigid body slew maneuver and three dimensional vibration of the rigid space shuttle, the flexible beam and the reflector with an offset mass. The contribution of this thesis lies in the development of two control systems based on (i) Euler angles or (ii) angular velocity components as output variables for large rotational maneuvers and vibration suppression of the SCOLE System. Nonlinear inversion theory is used for the design. The design approach taken here is to decompose the rigid mode control from vibration stabilization. (Abstract shortened with permission of author.).

Keywords

Damping; Feedback; Inversion; Maneuvers; NASA; Output; Rotational; Scole; System; Systeminversion; Theory; Vibration

Controlled Subject

Electrical engineering; Aerospace engineering

File Format

pdf

File Size

2334.72 KB

Degree Grantor

University of Nevada, Las Vegas

Language

English

Permissions

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Identifier

https://doi.org/10.25669/hhxm-9wxh


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