TY - JOUR
T1 - Uncertainty quantification of aeroelastic stability of composite plate wings using lamination parameters
AU - Scarth, Carl
AU - Cooper, Jonathan E.
AU - Weaver, Paul M.
AU - Silva, Gustavo H.C.
PY - 2014/9
Y1 - 2014/9
N2 - An approach is presented for modelling the aeroelastic stability of composite laminate wings with ply orientations subject to uncertainty. An aeroelastic model is constructed using the Rayleigh-Ritz technique coupled with modified strip theory aerodynamics. Lamination parameters are used as inputs to a Polynomial Chaos Expansion (PCE), enabling efficient propagation of the uncertainty through the aeroelastic model for a composite laminate with any number of plies. The Rosenblatt transformation is used to adapt the lamination parameter distributions for use with the PCE. A modified approach for modelling the uncertain aeroelastic response near the boundaries of different regimes of behaviour is also presented. Two case studies demonstrate application of the techniques; the first applies a simple PCE to a number of example balanced and symmetric laminates, the second applies the modified approach in a parametric investigation of the effects of bend-twist coupling on response mechanism. The proposed techniques offer at least an order of magnitude reduction in computation time compared to baseline Monte Carlo Simulation for all of the cases investigated.
AB - An approach is presented for modelling the aeroelastic stability of composite laminate wings with ply orientations subject to uncertainty. An aeroelastic model is constructed using the Rayleigh-Ritz technique coupled with modified strip theory aerodynamics. Lamination parameters are used as inputs to a Polynomial Chaos Expansion (PCE), enabling efficient propagation of the uncertainty through the aeroelastic model for a composite laminate with any number of plies. The Rosenblatt transformation is used to adapt the lamination parameter distributions for use with the PCE. A modified approach for modelling the uncertain aeroelastic response near the boundaries of different regimes of behaviour is also presented. Two case studies demonstrate application of the techniques; the first applies a simple PCE to a number of example balanced and symmetric laminates, the second applies the modified approach in a parametric investigation of the effects of bend-twist coupling on response mechanism. The proposed techniques offer at least an order of magnitude reduction in computation time compared to baseline Monte Carlo Simulation for all of the cases investigated.
KW - Aeroelastic tailoring
KW - Composite wing
KW - Lamination parameters
KW - Polynomial Chaos Expansion
KW - Uncertainty quantification
UR - http://www.scopus.com/inward/record.url?scp=84904582092&partnerID=8YFLogxK
U2 - 10.1016/j.compstruct.2014.05.007
DO - 10.1016/j.compstruct.2014.05.007
M3 - Article
AN - SCOPUS:84904582092
SN - 0263-8223
VL - 116
SP - 84
EP - 93
JO - Composite Structures
JF - Composite Structures
IS - 1
ER -