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Virginia Polytechnic Institute and State University

Nonlinear optimal control and near-optimal guidance strategies in spacecraft general attitude maneuvers

Abstract

dc:description.abstract

Solving the optimal open-loop control problems for spacecraft large-angle attitude maneuvers generally requires the use of numerical techniques whose reliability is strongly case dependent. The primary goal of this dissertation is to increase the solution reliability of the associated nonlinear two-point boundary-value problems as derived from Pontryagin’s Principle. Major emphasis is placed upon the formulation of the best possible starting or nominal solution. Constraint relationships among the state and costate variables are utilized. A hybrid approach which begins with the direct gradient method and ends with the indirect method of particular solutions is proposed. Test case results which indicate improved reliability are presented. The nonlinear optimal control law derived from iterative procedures cannot adjust itself in accordance with state deviations measured during the control period. A real-time near-optimal guidance scheme which takes the perturbed states to the desired manifold by tracking a given optimal trajectory is also proposed. Numerical simulations are presented which show that highly accurate tracking results can be achieved.

Degree

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

Author and committee

dc:creator, dc:contributor.*
Author dc:creator
  • Lin, Yiing-Yuh
Chair dc:contributor.committeechair
  • Kraige, Luther
Committee members dc:contributor.committeemember
  • Smith, C.W.
  • Nayfeh, Ali
  • Hendricks, Scott L.
  • VanLandingham, Hugh F.

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/10919/53572
OAI identifier oai:identifier
oai:vtechworks.lib.vt.edu:10919/53572

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

Lin, Yiing-Yuh. Nonlinear optimal control and near-optimal guidance strategies in spacecraft general attitude maneuvers. doctoral thesis, Virginia Polytechnic Institute and State University, 1988. http://hdl.handle.net/10919/53572