Date of Award
Fall 2007
Document Type
Thesis
Degree Name
Master of Science (MS)
Department
Mechanical & Aerospace Engineering
Program/Concentration
Aerospace Engineering
Committee Director
Chuh Mei
Committee Member
Jen-Kuang Huang
Committee Member
Brett Newman
Call Number for Print
Special Collections; LD4331.E535 K56 2007
Abstract
Suppression of nonlinear panel flutter at supersonic speeds has been investigated traditionally with system equations of motion in terms of in vacuo modal coordinates. For isotropic and symmetrically laminated orthotropic composite plates, the limit-cycle oscillations converged with six in vacuo natural modes at zero yaw angle. However, as laminated composite plates undergo the effect of an arbitrary yawed flow angle, complicated characteristics emerge when increasing the required in vacuo natural modes for an analysis of limit-cycle oscillations. In order to design an effective controller, the large number of modes should be reduced. As a result, the small number of modes produces the capability to alleviate the costly computational effort in designing controllers for suppression of nonlinear panel flutter. In the present study, aeroelastic modes that provide the reduced order basis are utilized for panel limit-cycle motion. Two or six to seven aeroelastic modes are implemented for developing an active controller of panel flutter with isotropic and anisotropic laminated composite plates at zero or non-zero yaw angle, respectively. Along with the aeroelastic modal equations of lesser number, a linear quadratic regulator, which is one of the output feedback controllers, is constructed to suppress nonlinear panel flutter. An added extended Kalman filter compensates for the nonlinearity of structural motion resulting by updating the system information on-line. The norms of feedback control gain matrix and the norms of Kalman filter estimation gain matrix are employed for the optimal placement of PZT5A or Macro-Fiber Composite piezoelectric actuators and sensors. Numerical results show that the designed controller based on aeroelastic modal coordinates can suppress the large-amplitude panel nonlinear flutter response. The maximum flutter-free dynamic pressure for isotropic and composite plates is evaluated to measure how much the performance is improved.
Rights
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DOI
10.25777/snjv-wz89
Recommended Citation
Kim, Myounghee.
"Active Control of Nonlinear Panel Flutter at Supersonic Speed Using Aeroelastic Modes and Self-Sensing Piezoelectric Actuators Under Yawed Flow Angle"
(2007). Master of Science (MS), Thesis, Mechanical & Aerospace Engineering, Old Dominion University, DOI: 10.25777/snjv-wz89
https://digitalcommons.odu.edu/mae_etds/565