Dynamic modeling and optimal control of spacecraft with flexible structures undergoing general attitude maneuvers

Yiing-Yuh Lin, Gern Liang Lin

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

In this research, the dynamics and control of a rigid spacecraft with flexible structures were studied for the case of optimal simultanuous multi-axis reorientation. A model spacecraft consisting of a rigid hub in the middle and two solid bodies symmetrically connected to either side of the hub through uniformly distributed flexible beams is considered for the dynamic analysis and control simulation. To optimally reorienting the spacecraft, an optimal nominal control trajectory is found first through an iterative procedure. Linear flexural deformations are assumed for the beam structures and the assumed modes method is applied to find the vibration control law of the beams. The system overall optimal attitude control is achieved by following the open loop optimal reference control trajectory with an stabilizing guidance law.

Original languageEnglish
Title of host publicationAdvances in the Astronautical Sciences
PublisherPubl by Univelt Inc
Pages395-410
Number of pages16
Editionpt 1
ISBN (Print)0877033471
Publication statusPublished - 1992 Jan 1
EventProceedings of the AAS/AIAA Astrodynamics Conference - Durango, CO, USA
Duration: 1991 Aug 191991 Aug 22

Publication series

NameAdvances in the Astronautical Sciences
Numberpt 1
Volume76
ISSN (Print)0065-3438

Other

OtherProceedings of the AAS/AIAA Astrodynamics Conference
CityDurango, CO, USA
Period91-08-1991-08-22

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

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  • Cite this

    Lin, Y-Y., & Lin, G. L. (1992). Dynamic modeling and optimal control of spacecraft with flexible structures undergoing general attitude maneuvers. In Advances in the Astronautical Sciences (pt 1 ed., pp. 395-410). (Advances in the Astronautical Sciences; Vol. 76, No. pt 1). Publ by Univelt Inc.