Abstract
In this paper, in order to understand the influence of the unbalanced coefficient of composite laminates on the static aeroelasticity of high aspect wings, a series of numerical simulation calculations were carried out, and this work wants to provide some reference for the structural design of aircraft. Considering the influence of geometric nonlinearity, the unidirectional fluid-solid coupling calculation method based on loose coupling is used to control the change of unbalanced coefficient of laminates on the basis of layering angle, layering thickness, and layering region, so as to observe the changes caused to the wings. The relationship between the unbalanced coefficient and the constant thickness layup and the variable thickness layup with 0° and ±45° layup angles was studied, respectively. Then, the layup angle of 90° was added to study the influence of the unbalanced coefficient on the static aeroelasticity of the wing structure with the change of the layup angle and the different choice of layup region. The results show that the deformation is the smallest when the unbalanced coefficient is 0.5, and the deformation trend is evenly distributed along both sides when the unbalanced coefficient is 0.5. When the unbalanced coefficient is changed, adding the 90° layup angle can significantly reduce the overall deformation of the wing and show different sensitivity characteristics to different layup areas. The increase of the unbalanced coefficient makes the chordal displacement gradually change from linear distribution to nonlinear distribution along the spread direction, and the displacement will gradually decrease.
Highlights
Advanced composite material (ACM) was born in the late 1960s
Based on the calculation method of fluid-structure interaction, this paper focuses on the analysis of the static aeroelasticity of high aspect ratio wing under different unbalanced coefficients, the layer thickness, angle, and the influence of each layer segment on the static aeroelasticity
The unidirectional fluid-structure coupling calculation method based on loose coupling is used to study the influence of the change of unbalanced coefficient on the static aeroelastic characteristics of the wing with high aspect ratio under the condition of geometric nonlinearity, and the following conclusions are drawn: (1) There is a single corresponding relationship between the maximum wing deformation and the change of unbalanced coefficient
Summary
Advanced composite material (ACM) was born in the late 1960s. In the early 1970s, the U.S Air Force Materials Research Institute applied composite materials to the structure of fighter aircraft in order to improve the performance of military fighter aircraft. Koohi et al and Xie et al [14, 15] carried out aeroelastic analysis on the composite wing beam model with high aspect ratio on the basis of considering geometric large deformation and achieved a good calculation accuracy. The performance design of structural parameters such as laying angle, laying order, and asymmetry/unbalanced of high aspect ratio composite wing was carried out, or the sensitivity algorithm and genetic algorithm were used to optimize the aeroelasticity of composite wing. The finite element method and Newton-Raphson iterative method are used to solve the structural equation under aerodynamic force, and the deformation and stress-strain values of the wing structure with high aspect ratio are obtained. The effects of various variables on the aerostatic elasticity of the wings with high aspect ratio are analyzed under different unbalanced coefficients
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