曲线纤维翼面气动弹性建模及分析方法OA

Traditional composite laminates with straight fibers are prone to buckling failure under in-plane compressive and shear loads,their limited design space hinders the full exploitation of the advantages of composite materials.A semi-analytical method for the aeroelasticity of a variable-angle-tow composite wing is proposed.First,a structural dynamic model of an arbitrary quadrangle plate wing is established using the Rayleigh-Ritz method.Then,a low-speed flutter model of a high-aspect-ratio wing is established by coupling quasi-steady aerodynamic theory and strip theory.Com-pared with the commercial finite element software Nastran,the analysis results of structural mode and p-k flutter are in good agreement,with the error of modal frequency less than 3%.Based on the analytical/semi-analytical model,the me-chanical characteristics of a variable-angle-tow composite wing are investigated in detail.The influence of Continuous Tow Shearing(CTS)variable thickness design,fiber path,and reference angle on the structural dynamic response is summarized.Results show that the flutter speed at the optimal reference angle is 50%higher than that at the worst angle.The research results are oriented to engineering applications and can provide references for the efficient design and manufacture of variable-angle-tow composite wing structures.