Design of variable stiffness composite panels for maximum fundamental frequency using lamination parameters
By Mostafa Abdalla, Shahriar Setoodeh, Zafer Gürdal. 2007
291 citations recorded by the source corpus.
View Paper: https://www.semanticscholar.org/paper/0a3ab538b9b36bd988c5cdb42a6115274c103d49
How researchers see this paper
The researchers whose trusted networks rank it highest, strongest advocate first. Every researcher gets a different order.
- Kazem Fayazbakhsh
- Hossein Ghiasi
- Paul M. Weaver
- Damiano Pasini
- Samuel T. IJsselmuiden
- L. Lessard
- Mostafa Abdalla
- Zafer Gürdal
Citations in the corpus
- Optimum stacking sequence design of composite materials Part II: Variable stiffness design (2010, background): “Abdalla and Gürdal [2] also selected the lamination parameters to maximize the natural frequency of composite panels.”
- Optimization of Variable-Stiffness Panels for Maximum Buckling Load Using Lamination Parameters (2010, background): “In past research the generalized reciprocal approximation, in which the response is approximated based on the inverse of the stiffness tensors, has been successful for variable-stiffness design [9,26].”
- Design of variable-stiffness composite panels for maximum buckling load (2009, methodology): “In the present study, we extend the generalized reciprocal approximation approach of Abdalla et al. [ 1 ] to buckling design of variable-stiffness panels.”
- Framework for the Buckling Optimization of Variable-Angle Tow Composite Plates (2015, unknown): “All of these works [5,14,17] rely on a finite element design scheme, in which the local lamination parameters (designvariables) are piecewise constant and associated with each element/node.”
- Isogeometric design of elastic arches for maximum fundamental frequency (2011, background): “…continuous variation of the stress resultants along the arch’s span, the stiffness terms are interpolated in a reciprocal sense (Wesseling 2001; Abdalla et al. 2007), which furnishes the following mapping: C(ξ) = ⎡ ⎣ i+p∑ j=i C−1j R j,p(ξ) ⎤ ⎦ −1 (15) where C(ξ) and C j represent the…”
- Improved aeroelastic tailoring using tow-steered composites (2013, background): “The change in natural vibration frequency as a function of the ply angle variation has also been studied [26–29].”