Structural Design and Finite Element Analysis of Unfolding Process for All Composite Folding Wing of UAV

Peng Lv; Sheng Li Lv; Guang Jun Yang; Qing Na Zeng; Xiao Yan Tong

doi:10.4028/www.scientific.net/AMR.163-167.2328

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 163-167Structural Design and Finite Element Analysis of...

Structural Design and Finite Element Analysis of Unfolding Process for All Composite Folding Wing of UAV

Abstract:

This paper discusses the unfolding form of the folding wing and its application to special UAV. The main investigations involve aspects such as unfolding process of the special UAV’s folding wing, contour structure of the complete unfolding, the choice of composite materials for the folding wing and its overall performance parameters. Modeling and dynamics analysis are made for all-composite wing through finite element analysis and calculating software. The unfolding process is also simulated. The result shows that the wing’s first-order frequency is low, second-order frequency and third-order frequency are close at different sweep angles. The wings are apt to happen flutter coupling in flutter analysis. With the continued folding of the wing, the wing’s natural frequency decreases significantly at different orders. The conclusions can provide effective basis for the study of wing rotational rate, unfolding time and impact action.

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Periodical:

Advanced Materials Research (Volumes 163-167)

Pages:

2328-2332

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.163-167.2328

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Online since:

December 2010

Authors:

Peng Lv, Sheng Li Lv, Guang Jun Yang, Qing Na Zeng, Xiao Yan Tong

Keywords:

Composite Material, Finite Element Analysis (FEA), Folding Wing, UAV

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