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Active control of an aircraft tail subject to harmonic excitation
Faculty
Science
Year:
2007
Type of Publication:
Article
Pages:
451-462
Authors:
Bauomy, H. S, Amer, Y. A, Eissa, M
DOI:
10.1007/s10409-007-0077-2
Journal:
ACTA MECHANICA SINICA SPRINGER HEIDELBERG
Volume:
23
Research Area:
Engineering; Mechanics
ISSN
ISI:000248818300012
Keywords :
active vibration control, stability, response curves, aircraft tail
Abstract:
Vibration of structures is often an undesirable phenomena and should be avoided or controlled. There are two techniques to control the vibration of a system, that is, active and passive control techniques. In this paper, a negative feedback velocity is applied to a dynamical system, which is represented by two coupled second order nonlinear differential equations having both quadratic and cubic nonlinearties. The system describes the vibration of an aircraft tail. The system is subjected to multi-external excitation forces. The method of multiple time scale perturbation is applied to solve the nonlinear differential equations and obtain approximate solutions up to third order of accuracy. The stability of the system is investigated applying frequency response equations. The effects of the different parameters are studied numerically. Various resonance cases are investigated. A comparison is made with the available published work.
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