Output feedback rotational maneuvers and vibration damping of Nasa Scole system by inversion theory

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.).

Name thesis:degree_name

Master of Science (MS)

Level thesis:degree_level

Thesis

Discipline thesis:degree_discipline

Electrical and Computer Engineering

Grantor dc:publisher

University of Nevada, Las Vegas

Year

1991

Author dc:creator

• Azam, Misbahul

Contributors dc:contributor

• S. N. Singh

Statement dc:rights

• IN COPYRIGHT. For more information about this rights statement, please visit http://rightsstatements.org/vocab/InC/1.0/

Language dc:language

English

Identifier

https://oasis.library.unlv.edu/rtds/140

OAI identifier oai:identifier

oai:oasis.library.unlv.edu:rtds-1139