Aeroelastic tailoring using fiber orientation and topology optimization

• Published in: Structural and multidisciplinary optimization Vol. 46; no. 5; pp. 663 - 677
• Main Authors: De Leon, D. M., de Souza, C. E., Fonseca, J. S. O., da Silva, R. G. A.
• Format: Journal Article
• Language: English
• Published: Berlin/Heidelberg Springer-Verlag 01.11.2012; Springer Nature B.V
• Subjects: Aeroelastic stability; Aeroelasticity; Computational Mathematics and Numerical Analysis; Density distribution; Design optimization; Eigenvalues; Engineering; Engineering Design; Equilibrium equations; Fiber orientation; Finite difference method; Finite element method; Fluid-structure interaction; Flutter; Lift devices; Linear programming; Maximization; Nonlinear programming; Plates (structural members); Research Paper; Resonant frequencies; Sensitivity analysis; Stability analysis; Theoretical and Applied Mechanics; Topology optimization; Vibration analysis; Vibration mode; Finite element method; Structural optimization; Flat plates; Aeroelasticity; Laminated composite materials
• ISSN: 1615-147X; 1615-1488
• DOI: 10.1007/s00158-012-0790-8

This work presents a structural optimization aided design methodology for composite laminated plates subject to fluid-structure interaction. The goal of the optimization procedure is to increase the flutter speed onset through the maximization of natural frequencies related to the vibration modes involved in the phenomenon. The aeroelastic stability analysis is performed using ZAERO software system, which includes ZONA 6 unsteady lifting surface method. The finite element method is applied to solve the structural model equilibrium equations, the eigenvalues sensitivities with respect to design variables are calculated analytically, and sequential linear programming is applied. The maximization is accomplished using two methods; the first method uses an aeroelastic analysis to determine which eigenmode causes the flutter onset, and its eigenvalue is then maximized. In the second method, a forward finite difference method is applied and the flutter speed sensitivities with respect to the eigenvalues are calculated. This sensitivity is used to guide the optimization process. Finally, a topology optimization problem is formulated to reduce the plate mass under a minimum flutter velocity constraint, using density distribution as the design variable.