Structural Optimization Research of Composite Aircraft Based on Different Wing Stiffness Constraints

Li Liang; Sun Qin

doi:10.4028/www.scientific.net/AMR.466-467.282

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 466-467Structural Optimization Research of Composite...

Structural Optimization Research of Composite Aircraft Based on Different Wing Stiffness Constraints

Abstract:

Wing stiffness, mainly including bending stiffness and torsion stiffness, is very important in aircraft structure design. In order to research the relation between wing stiffness and optimization results, this paper makes optimization analysis to a composite T-tail configuration and a composite flying wing configuration based on different wing stiffness constraints, and some valuable conclusions are achieved.

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Periodical:

Advanced Materials Research (Volumes 466-467)

Pages:

282-286

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.466-467.282

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Online since:

February 2012

Authors:

Li Liang, Sun Qin

Keywords:

Composite Flying Wing, Composite T-Tail, Structural Optimization, Wing Stiffness Constraints

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References

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