ORIENTATION OPTIMIZATION FOR THE FLUTTER ONSET IN FIBER REINFORCED LAMINATED PLATES USING MAC

ORIENTATION OPTIMIZATION FOR THE FLUTTER ONSET IN FIBER REINFORCED LAMINATED PLATES USING MAC

Varella, G.; Leon, D. M. De; Fonseca, J. S. O.; Souza, C. E de; Silva, R. G. A. da

Full Article:

This work presents an optimization formulation to increase the flutter onset velocity in a composite plate made of glass-epoxy subject to an airflow parallel to its surface. The problem is stated as the maximization of the eigenvalue related to the flutter effects, aiming the improvement in the flutter onset speed. The design variable is the fiber orientation of each ply of the composite plate. The sensitivities are calculated analytically and sequential linear programming is applied. The flutter mode and onset velocity are calculated by the ZAERO software. Mode tracking switching scheme based on the modal assurance criterion (MAC) is used to improve the optimization formulation when a repeated eigenvalue problem has to be handled by the algorithm. Results are presented for many test cases, showing a marked improvement of the simulated flutter behavior.

This work presents an optimization formulation to increase the flutter onset velocity in a composite plate made of glass-epoxy subject to an airflow parallel to its surface. The problem is stated as the maximization of the eigenvalue related to the flutter effects, aiming the improvement in the flutter onset speed. The design variable is the fiber orientation of each ply of the composite plate. The sensitivities are calculated analytically and sequential linear programming is applied. The flutter mode and onset velocity are calculated by the ZAERO software. Mode tracking switching scheme based on the modal assurance criterion (MAC) is used to improve the optimization formulation when a repeated eigenvalue problem has to be handled by the algorithm. Results are presented for many test cases, showing a marked improvement of the simulated flutter behavior.

Palavras-chave:

DOI: 10.5151/meceng-wccm2012-18946

Referências bibliográficas

• [1] Albano E., Rodden W. P., “A Doublet-Lattice Method for Calculating Lift Distributions on Oscillating Surfaces in Subsonic Flows”. AIAA Journal 7, 279-285, 1969.
• [2] Allemang R. J., “The modal assurance criterion - Twenty years of use and abuse”, Sound and Vibrations, 14-21, 2003.
• [3] Bunton R. W., Denegri Jr. C. M. “Limit Cycle Oscillation Characteristics of Fighter Aircraft”. Journal of Aircarft 37(5), 916-918, 2000.
• [4] Chen P. C. “Damping Perturbation Method for Flutter Solution: The g-method.”. AIAA Journal 38(9), 1519-1524, 2000.
• [5] EADS Deutschland GmbH, C. R. C. “The research requirements of the transport sectors to facilitate an increased usage of composite materials, Part 1 : The Composite Material Research Requirements of the Aerospace Industry”, 2004.
• [6] Giesing J., Kalman, T., Rodden, W., “Subsonic Unstweady Aerodynamics for General Configurations”. Technical report affdl-tr-71-5, Air Force Flight Dynamics Laboratory, 1971.
• [7] Harder R. L., Desmarais R. N. “Interpolation Using Surface Splines”, Journal of Aircraft 9, 189-191, 1972.
• [8] Hertz T. J., Shirk M. H., Ricketts R. H., Weisshaar, T. A., “Aeroelastic Tailoring with Composites Applied to Forward Swept Wings.” Technical report, Flight Dynamics Laboratory (FIBR) AF Wright Aeronautical Laboratories, 1981.
• [9] Irvine T., “http://www.vibrationdata.com/tutorials2/ModalMass.pdf”. Web page consulted on October 14th, 2010.
• [10] Jones R. M., “Mechanics of Composite Materials”. Scripta Book Company, Washington 2nd edition, 1999.
• [11] Kim T. S., Kim Y. Y., “Mac-based mode tracking in structural topology optimization”, Computers and Structures 74, 375-383, 2000.
• [12] KumarW. P. P., Palaninathan R., “Finite Element Analysis of Laminated Shells with Exact Through-Thickness Integration”, Computers and Structures, 63(1), 173-184, 1997.
• [13] Reddy J. N. “Mechanics of Composite Plates and Shells - Theory and Analysis”. 2nd edition, 2004.
• [14] von Gersdorff K., “Bölkow-Sportflugzeuge: Die Sport-, Schul- und Reiseflugzeuge mit Entwürfen und Projektender Firmen Klemm, Bökow, SIAT, MBB, LFU und Mylius von 1956 bis 1979 Buchzentrum Empfingen”, 1981.
• [15] Weisshaar T. A., “ Aircraft Aeroelastic Design and Analysis”. School of Astronautics and Aeronautics - Purdue University, Class Notes, 1995.
• [16] Zhang Y. X., Yang Z. H., “Recent Developments in Finite Element Analysis for Laminated Composite Plates”, Composite Structures 88, 147-157, 2009.
• [17] Zienkiewicz O., Taylor R. L., “The Finite Element Method - The Basis”. Elsevier Academic Press, 5th edition volume 1, 2000.
• [18] ZONA-Technology., “ZAERO Theoretical Manual”. ZONA Technology Inc., Scottsdale, Arizona, USA., 15a edition, 2006.

Como citar:

Varella, G.; Leon, D. M. De; Fonseca, J. S. O.; Souza, C. E de; Silva, R. G. A. da; "ORIENTATION OPTIMIZATION FOR THE FLUTTER ONSET IN FIBER REINFORCED LAMINATED PLATES USING MAC", p-2652-2667. In: In Proceedings of the 10th World Congress on Computational Mechanics [= Blucher Mechanical Engineering Proceedings, v. 1, n. 1]. São Paulo: Blucher, 2014.
ISSN 23580828, DOI 10.5151/meceng-wccm2012-18946