Improved Design and Dynamic Simulation of High Aspect Ratio Folding Wings

Sheng Li Lv; Ping Liu; Guang Jun Yang; Xiao Yan Tong

doi:10.4028/www.scientific.net/AMM.249-250.410

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 249-250Improved Design and Dynamic Simulation of High...

Improved Design and Dynamic Simulation of High Aspect Ratio Folding Wings

Abstract:

Folding wings of UAV may lead to high bending and torsion deformation under flight load. In order to solve the problem, an improved folding wing mechanism is proposed, which makes support mechanism stiffness become enough big. By means of CATIA and ADAMS, a virtual prototype is set up, which can simulate dynamics of the deployment mechanism. Therefore the relationship among deployment time and friction coefficient and tension is arrived. Meanwhile finite element analysis is made on folding wing with support structure and without support structure by MSC.Nastran. And the results show that the stiffness and strength change obviously. Simulation results have a certain guiding significance for practical engineering application.

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Periodical:

Applied Mechanics and Materials (Volumes 249-250)

Pages:

410-414

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.249-250.410

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Online since:

December 2012

Authors:

Sheng Li Lv, Ping Liu, Guang Jun Yang, Xiao Yan Tong

Keywords:

Adam, Dynamic, Folding Wing, Strength

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References

[1] Wilson, J. R. Aerospace America. pp.28-29. February (2004).

Google Scholar

[2] David Neal, Matthew Good, Christopher Johnson. Design and Wind-Tunnel Analysis of a Fully Adaptive Aircraft Configuration[C]. AIAA 2004-1727, (2004).

Google Scholar

[3] Basic ADAMS Full Simulation Training Guide [M]. 256-258.

Google Scholar

[4] MSC. Software. MSC. Patran user's manual[M]. Los Angeles: The Macneal-Schwendler Corporation, (2005).

Google Scholar

[5] Lv. P, Lv. SL, Yang. GJ, Zeng. QN, and Tong. XY, Structural Design and Finite Element Analysis of Unfolding Process for All Composite Folding Wing of UAV, Adv. Mater. Res. 163-167, 2328 (2011).

DOI: 10.4028/www.scientific.net/amr.163-167.2328

Google Scholar

[6] Deman Tang and Earl H. Dowell: Journal of Aircraft Vol. 45NO. 4 (2008), p.1136.

Google Scholar

[7] Woldemar Voigt. Swept Wing With Unswept Span [P]. USA, Utility Patent. 3018985, 1962-01-30.

Google Scholar

[8] Max Bowen. Adjustable Wing Aircraft [P]. USA, Utilitty Patent. 2822995, 1958-02-11.

Google Scholar