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Virginia Polytechnic Institute and State University

Control of flexible spacecraft during a minimum-time maneuver

Abstract

dc:description.abstract

The problem of simultaneous maneuver and vibration control of a flexible spacecraft can be solved by means of a perturbation approach whereby the slewing of the spacecraft regarded as rigid represents the zero-order problem and the control of elastic vibration, as well as of elastic perturbations from the rigid-body maneuver, represents the first-order problem. The zero-order control is to be carried out in minimum time, which implies on-off control. On the other hand, the perturbed model is described by a high-order set of linear time-varying ordinary differential equations subjected to persistent, piecewise-constant disturbances caused by inertial forces resulting from the maneuver. This dissertation is concerned primarily with the control of the perturbed model during maneuver. On-line computer limitations dictate a reduced-order compensator, thus only a reduced-order model (ROM) is controlled while the remaining states are regarded as residual. Hence, the problem reduces to 1) control in a short time period of a linear time-varying ROM subject to constant disturbances and 2) mitigation of control and observation spillover effects, as well as modeling errors, in a way that the full modeled system remains finite-time stable. The control policy is based on a compensator, which consists of a Luenberger observer and a controller. The main features of the control design are: (1) the time-varying ROM is stabilized within the finite-time interval by an optimal linear quadratic regulator, (2) a weighted norm spanning the full modeled state is minimized toward the end of the time interval, and (3) the supremum"time constant" of the full modeled system is minimized, while (1) serves as a constraint, thus resulting in a finite-time stable modeled system. The above developments are illustrated by means of a numerical example.

Degree

thesis:*
Name thesis:degree_name
Ph. D.
Level thesis:degree_level
doctoral
Discipline thesis:degree_discipline
Electrical Engineering
Department dc:contributor.department
Electrical Engineering
Grantor dc:publisher
Virginia Polytechnic Institute and State University
Year dc:date.issued
1988

Author and committee

dc:creator, dc:contributor.*
Author dc:creator
  • Sharony, Yaakov
Chairs dc:contributor.committeechair
  • Meirovitch, Leonard
  • VanLandingham, Hugh F.
Committee members dc:contributor.committeemember
  • Burns, John A.
  • Beex, Aloysius A.
  • Lindner, Douglas

Rights

dc:rights
Statement dc:rights
  • In Copyright
Language dc:language.iso
en_US

Identifiers

dc:identifier.*
Handle dc:identifier.uri
http://hdl.handle.net/10919/77834
OAI identifier oai:identifier
oai:vtechworks.lib.vt.edu:10919/77834

Chain of custody

source
Harvested from
Virginia Tech
Base URL
vtechworks.lib.vt.edu/oai/request
Last updated
2026-07-22
Source record
OAI-PMH GetRecord
related terms
citation

Sharony, Yaakov. Control of flexible spacecraft during a minimum-time maneuver. doctoral thesis, Virginia Polytechnic Institute and State University, 1988. http://hdl.handle.net/10919/77834