Aeroelastic tailoring of composite sandwich panel with lamination parameters

Abstract

For sandwich panel with a thick core, stiffness matrix of composite sandwich panel can be formulated as function of membrane lamination parameters of the composite facesheet. In this paper, the flutter speed of a cantilevered sandwich panel is studied using lamination parameters of composite facesheet, with influence of transverse shear on sandwich panel considered. The results show that the flutter mode switch is not only related to the bending stiffness change, and also the transverse shear effect can result in switch of flutter mode. A minimum weight design of composite sandwich panel is conducted by using master-slave parallel real-coded genetic algorithm, with lamination parameters of facesheet and transverse shear modulus of foam core as design variables. The constraints considered include the flutter and divergence velocity constraints, the bound constraints of thicknesses of the facesheet and foam core. The feasible region constraints of membrane lamination parameters are also considered.

Flutter Characteristic Study of Composite Sandwich Panel with Functionally Graded Foam Core

“…Gradient Foam. When 3 is positive, the bending-torsional flutter mode still remains the same as the orthotropic sandwich panel [9]. When 3 is negative, there may be another flutter mode within part of the lamination parameter region (shown as Figure 6 Figure 7 shows the histories of the damping and frequency of the first four modes for the two cases.…”

“…Results. According to (9-11) of [9], with the optimum facesheet thickness (0.125 mm) and optimum lamination parameters ([ 1 , 2 , 3 ] = [0, −1, −0.076]), the corresponding layer thickness of facesheet can be obtained ([ 0 , 90 , 45 , −45 ] = [0, 0, 0.05775 mm, 0.06725 mm]). And the density distribution of the foam core is [ min core , max core ] = [20, 37.64] kg/m 3 .…”

“…Dunning et al fill a gap in the literature pertaining to FGM-based aeroelastic tailoring by considering a metallic wing in low-speed (subsonic) conditions. Based on author's previous research [9], this paper considers the low-speed flutter behavior of a clamped plate-wing, whose structure is composed of laminated facesheets and a functionally graded foam core. The present study aims to consider the flutter characteristic of sandwich panel with the macroscopic properties of the foam core changing continuously along this direction parallel to the facesheet lamina.…”

The effects of a full-aircraft aerodynamic model on the design of a tailored composite wing

“…The approach was first proved for a flat composite panel, where the set of lamination parameters and thickness was calculated for maximum flutter speed. The work of Jin et al [14], and Dillinger et al [15] has scaled this approach to solve a similar problem for the whole wing, modeled as a multitude of chordwise and spanwise panels for a more detailed description of a composite wingbox and its structural elements.…”

Lamination Parameters for Sandwich and Hybrid Material Composites

“…Sandwich composite optimization for a wide range of applications has been presented [13][14][15][16][17][18][19][20]. Among these, very few approaches using lamination parameters are available, which is the focus of this work.…”