ROOT LOCUS METHOD FOR ACTIVE CONTROL OF FLEXIBLE SYSTEMS.

Norihiro Goto, Shinji Hokamoto

Research output: Contribution to journalArticle

1 Citation (Scopus)

Abstract

Precise attitude and shape control of flexible spacecraft requires active control of flexural vibrations. This paper is concerned with the root locus method applied to active vibration control systems for a certain class of flexible bodies. A general characteristic equation is derived for a feedback system to control flexural vibrations with arbitrary numbers of sensors and actuators. Then it is shown, for the first time, that the characteristic equation in determinantal form may be reduced to a mathematically tractable form. It is also shown that under the condition of colocation of sensors and actuators the characteristic equation assumes a form in which the significance of this condition can be readily appreciated. Finally, the paper presents a numerical study to illustrate a practical procedure applying the root locus method to flexural vibration control systems.

Original languageEnglish
Pages (from-to)150-161
Number of pages12
JournalTransactions of the Japan Society for Aeronautical and Space Sciences
Volume30
Issue number89
Publication statusPublished - Nov 1 1987

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

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