TY - GEN
T1 - Optimal postbuckling design of variable angle tow composites using lamination parameters
AU - Raju, Gangadharan
AU - White, Simon
AU - Wu, Zhangming
AU - Weaver, Paul M.
N1 - Publisher Copyright:
© American Institute of Aeronautics and Astronautics Inc. All rights reserved.
PY - 2015
Y1 - 2015
N2 - An optimization study is presented for the postbuckling design of orthotropic variable angle tow (VAT) composite plates under axial compression. The postbuckling analysis of a VAT plate is done using a perturbation approach namely, an asymptotic numerical method (ANM) which transforms the nonlinear problem into a set of well-posed recursive linear problems. These linear problems are solved using a generalized differential-integral quadrature method and the postbuckling results are found to be reasonably accurate over a finite load step size around the critical buckling point. The generalized differential-integral quadrature method implementation of the ANM is found to be robust and computationally efficient for evaluating the initial postbuckling solution of VAT plates. Furthermore, the relatively high efficiency of the ANM approach can be used for optimal design of composite plates in the postbuckling region. The postbuckling design criteria of VAT composite plates are based on the minimization of the end shortening strain for a given compressive load. In this work, an efficient two-level optimization framework is used for design of VAT plates that maximizes the postbuckling performance. At the first level, a gradient based optimization algorithm namely, globally convergent method of moving asymptotes is adopted to determine the optimal lamination parameter distributions of the VAT plate. At the second level, a genetic algorithm is used to convert the lamination parameter distributions into realistic VAT layups. The optimization studies are carried out for VAT plates under different in-plane boundary conditions.
AB - An optimization study is presented for the postbuckling design of orthotropic variable angle tow (VAT) composite plates under axial compression. The postbuckling analysis of a VAT plate is done using a perturbation approach namely, an asymptotic numerical method (ANM) which transforms the nonlinear problem into a set of well-posed recursive linear problems. These linear problems are solved using a generalized differential-integral quadrature method and the postbuckling results are found to be reasonably accurate over a finite load step size around the critical buckling point. The generalized differential-integral quadrature method implementation of the ANM is found to be robust and computationally efficient for evaluating the initial postbuckling solution of VAT plates. Furthermore, the relatively high efficiency of the ANM approach can be used for optimal design of composite plates in the postbuckling region. The postbuckling design criteria of VAT composite plates are based on the minimization of the end shortening strain for a given compressive load. In this work, an efficient two-level optimization framework is used for design of VAT plates that maximizes the postbuckling performance. At the first level, a gradient based optimization algorithm namely, globally convergent method of moving asymptotes is adopted to determine the optimal lamination parameter distributions of the VAT plate. At the second level, a genetic algorithm is used to convert the lamination parameter distributions into realistic VAT layups. The optimization studies are carried out for VAT plates under different in-plane boundary conditions.
UR - http://www.scopus.com/inward/record.url?scp=85088740406&partnerID=8YFLogxK
U2 - 10.2514/6.2015-0451
DO - 10.2514/6.2015-0451
M3 - Conference contribution
AN - SCOPUS:85088740406
T3 - 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
BT - 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2015
Y2 - 5 January 2015 through 9 January 2015
ER -