Effect of ply angle on nonlinear static aeroelasticity of high-aspect-ratio composite wing
| Autor: | Wensheng Zhang, Zhigui Ren, Shuai Lei, Hong Cui, Junli Wang, Li Tuolei |
|---|---|
| Rok vydání: | 2020 |
| Předmět: |
Materials science
fluid-structure coupling lcsh:Mechanical engineering and machinery composite materials Composite number 02 engineering and technology 01 natural sciences Stress (mechanics) 0203 mechanical engineering 0103 physical sciences lcsh:TJ1-1570 General Materials Science ply angle 010301 acoustics Wing business.industry Mechanical Engineering Aerodynamics Structural engineering Aeroelasticity high-aspect-ratio wing Lift (force) 020303 mechanical engineering & transports Deformation (engineering) business optimization Beam (structure) |
| Zdroj: | Journal of Vibroengineering, Vol 22, Iss 4, Pp 959-970 (2020) |
| ISSN: | 2538-8460 1392-8716 |
| DOI: | 10.21595/jve.2019.20968 |
| Popis: | In order to reduce the weight and improve aerodynamic characteristics, the new aircraft generally adopts lightweight composite materials and high-aspect-ratio layout. Such the structural layout aircraft will produce large nonlinear aeroelastic deformation under the action of aerodynamic loads. Due to the anisotropy of the composite, the composite ply angle of wing skin has a great influence on the elastic deformation of the high-aspect-ratio wing. In order to study the influence of the ply angle on the nonlinear static aeroelastic wing deformation, based on CFD/CSD unidirectional fluid-solid coupling, the structural deformation and stress of high-aspect-ratio composite wing were numerically solved. The wing deformation along the lift direction was taken as the optimization target. The structure strength was taken as the constraint. The ply angle for the composite skin of the high-aspect-ratio composite wing was optimized by the Screening method. The optimization results show the nonlinear static aeroelastic deformation of the wing in the lift direction is reduced by 39.1 %. The maximum stress of the wing beam and rib is reduced by 39.0 %. The maximum Tsai-Wu failure factor of the wing skin is reduced by 47.1 %. |
| Databáze: | OpenAIRE |
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