Structural Optimization Design of an Aircraft Metal-Composite Wing

Ya Hui Zhang; Ji Hong Zhu; Jun Shuo Li; Wei Hong Zhang

doi:10.4028/www.scientific.net/AMM.341-342.519

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 341-342Structural Optimization Design of an Aircraft...

Structural Optimization Design of an Aircraft Metal-Composite Wing

Abstract:

The problem of metal-composite wing structural optimization is discussed and a strategy is presented. Topology optimization method is applied to provide load transferring path of structure for concept design. Size, shape and other optimization method are used to provide detailed design for individual components. A three-phase optimization method is discussed for fiber reinforced composite laminate skin. Optimal parameters include ply angle, percentage, thickness, layer shape and sequence. The design of laminate for ease of manufacture is based on a set of manufacturing constraints. This paper deals with a total optimal design solution for aileron structure of an aircraft. The result satisfies all the requirements of strength and stability, and has obvious effect of weight loss.

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Periodical:

Applied Mechanics and Materials (Volumes 341-342)

Pages:

519-523

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.341-342.519

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Online since:

July 2013

Authors:

Ya Hui Zhang, Ji Hong Zhu, Jun Shuo Li, Wei Hong Zhang

Keywords:

Aileron, Laminates, Metal-Composite Structure, Structural Optimization, Wing

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References

[1] Andrew S. Fine, George S. Springer. Design of Composite Laminates for Strength, Weight, and Manufacturability. Journal of Composite Materials[J], 31: 2330.

DOI: 10.1177/002199839703102301

Google Scholar

[2] Jacob L. Pelletier, Senthil S. Vel. Multi-objective Optimization of Fiber Reinforced Composite Laminates for Strength, Stiffness and Minimal Mass. Computers & Structures [J], Volume 84, Issues 29–30, November 2006, Pages 2065–(2080).

DOI: 10.1016/j.compstruc.2006.06.001

Google Scholar

[3] Dr. Robert N. Yancey, Warren Dias. Optimization Driven Design of a Composite Underbelly Fairing with HyperWorks. Altair HyperWorks White Paper, 2009. 9.

Google Scholar

[4] Dianzi Liu, Vassili V. Toropov, Osvaldo M. Querin, David C. Barton. Bilevel Optimization of Blended Composite Wing Panels, Journal of aircraft [J], 2011, 48(1).

DOI: 10.2514/1.c000261

Google Scholar

[5] Shijun Guo ；Wenyuan Cheng ；Degang Cui, Aeroelastic Tailoring of Composite Wing Structures by Laminate Layup Optimization, AIAA Journal, 2006, 44(12).

DOI: 10.2514/1.20166

Google Scholar