Lamination Optimization Design Of CG231 Composite Wing Based On Response Surface Method

As the main bearing structure of the aircraft,the wing ensures that the aircraft meets the requirements of flight performance and maneuverability under the flight state specified by the design requirements.For modern aircraft,the proportion of composite materials in wing structural materials is increasing.Designing a high-rigidity,high-strength and lightweight wing plays an important role in improving aircraft flight performance and endurance.In this paper,the research on the optimization of a light aircraft composite wing structure is carried out in the following aspects:(1)The mechanical property parameter test experiment was carried out for CG231 glass fiber composite material.Tensile,compressive and shear tests were carried out on the composite laminate,and finally the performance parameters such as tensile strength,compressive strength,shear strength,Poisson’s ratio and elastic modulus of the material were obtained,and the damage of the material was obtained.Morphology and failure modes were analyzed.(2)Firstly,through the analysis of the design characteristics of the wing structure,the 3D model of the composite wing structure is constructed by using CATIA software,and the parameterized 3D model is associated with the ANSYS Workbench module to obtain the finite element model,and the mesh division and finite element model of the wing structure are completed.meta-analysis;Secondly,the sensitivity method is used to analyze the structural components of the wing,and the influence of each structural design variable on the optimization objective and the performance of the wing is obtained.The research shows that the initial wing model meets the design requirements;the skin thickness has the greatest influence on the mechanical properties of the wing relative to other structural design variables.(3)A combination of response surface optimization and direct optimization is used to further optimize the ply design of the wing structure.Firstly,Response Surface Optimization is used to optimize the layer thickness of the wing structure.The maximum displacement deformation,stress limit and strain limit are used as the response variables,and the minimum structure quality of the wing is used as the optimization goal.Finally,the wing structure is determined.The layer thickness of important components;then,combined with direct optimization,the layer sequence optimization design of the skin laminate structure was carried out,and the optimal layer sequence of the skin was finally obtained.Through the above optimization design,the optimal layering scheme of the wing structure is obtained.After the finite element analysis,the research shows that the optimized wing structure meets the performance requirements.Compared with before optimization,the weight of the wing is reduced by 16.12%.Compared with the traditional aluminum alloy wing,the weight reduction is more obvious,reaching 124.53%.(4)Through the sensitivity analysis of the main components of the wing structure and the optimal design of the layer of the wing structure,the mechanical properties of the wing structure meet the requirements for use,and the weight reduction of the wing structure is obvious,and the optimization method is combined with the finite element analysis.The accuracy and reliability of the composite material are high,which provides a reference for the optimal design of composite materials in aeronautical structures.