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Next generation of composite civil aircrafts and unconventional configurations, such as High Altitude Long Endurance HALE-UAV, exhibit aeroelastic instabilities quite different from their rigid counterparts. ...The objective of this paper is to provide the authors' point of view on a consistent scaling procedure applicable when investigating the flutter stability of a full-size high aspect-ratio composite wing structure by means of an economical laboratory wind tunnel test model. Sizing and technological development aspects are discussed along with a detailed design procedure to gather the necessary data for the model manufacture. ...Finally a dynamically scaled composite model is defined for a wind tunnel aeroelastic test.

The robust evaluation is obtained via a Quasi Monte Carlo Method using Sobol sequence (QMCM), the uncertainties due to material and manufacturing process are modeled via Composite Micromechanics Theory. Example of applications presented include the optimization process for a composite flat plate for minimum weight and maximum uniaxial buckling load. ...Example of applications presented include the optimization process for a composite flat plate for minimum weight and maximum uniaxial buckling load. The proposed approach is compared with classical Robust Multi-Objective Optimization method in terms of computational time and a reduction up to one order of magnitude has been pointed out.

The wing of this type of UAVs, usually made of highly flexible composite materials, has high aspect ratio with significant bending-torsional deformation during flight.

The model presented in this paper is based on a consistent nonlinear beam-wise scheme, capable of simulating the unconventional aeroelastic behaviour of flexible composite wings. The partial differential equations describing the wing dynamics are expanded up to the third order and can be used to explore the effect of static deflection imposed by external trim, the effect of gust loads and the one of nonlinear aerodynamic stall.

The model presented in this paper is based on a consistent nonlinear beam model, capable of simulating the unconventional aeroelastic behaviour of flexible composite wings. The partial differential equations describing the wing dynamics are reduced to a dimensionless form in terms of three ordinary differential equations using a discretization technique, along with Galerkin's method.