On the Root Locus Method Applied to Flexural Vibration Control Systems

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概要

• 論文の詳細を見る

• Precise attitude and shape control of flexible spacecraft requires active control of flexural vibrations. This work 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 first 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 a determinantal form may be expanded in a mathematically tractable form. The expanded form can show clearly the significance of the colocation condition of sensors and actuators. The characteristic equation in a moving coordinate system is also derived, considering that the control is made using the outputs of onboard sensors. Finally the paper presents a numerical study to illustrate a practical procedure of applying the root locus method to flexural vibration control systems.

• 宇宙航空研究開発機構の論文

著者

• Goto N

  Kyushu Univ. Fukuoka

• Goto Norihiro

  Department Of Aeronautical Engineering Faculty Of Engineering Kyushu University

• Hokamoto S

  Saga Univ. Saga Jpn

• HOKAMOTO Shinji

  Graduate Student, Applied Mechanics, Division of Engineering, Graduate School, Kyushu University,

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