Synthetic Design of High Aspect Ratio Folding Wings Based on Aeroelastic Analysis

Sheng Li Lv; Cheng Wang; Yang Biao Ou; Guang Jun Yang; Xiao Yan Tong

doi:10.4028/www.scientific.net/AMM.607.409

Paper Titles

Inherent Characteristic Similarity Analysis on Short Thin-Walled Cylindrical Shell
p.386

CFD Analysis of Energy Loss of Direction Control Valve in Electro-Hydraulic Systems with Inverter
p.393

Optimal Locomotive Control Parameters of Biologically Inspired Four-Legged Walking Machine
p.397

Modal Analysis and Experimental Research of Marine Gearbox
p.405

Synthetic Design of High Aspect Ratio Folding Wings Based on Aeroelastic Analysis
p.409

Real-Time Semi-Physical Simulation of Industry Design System Based on Virtual Reality Technology
p.413

Mixing Analysis of Laminar Flow in Static Mixers with Circle Grid Fractal Perforated Plate Elements
p.417

Research on the Static and Dynamic Characteristics of the Sliding Rail Joint Surfaces of the Fe-Based Porous Oily Material
p.422

The Thermal Structure Coupling Analysis of Hydrostatic Motorized Spindle in Ultra-Precision Grinding Machine
p.427

HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 607Synthetic Design of High Aspect Ratio Folding...

Synthetic Design of High Aspect Ratio Folding Wings Based on Aeroelastic Analysis

Abstract:

Finite element model of folding wings was designed in the light of structural scheme, and each part of the model used composites. Different aeroelastic analysis models were built from emission to cruise, and then the models were made the study focus on flutter analysis. The result showed the change relationship of the critical flutter speed of wings and flutter frequency with sweep angle in state of expansion process, and the change relationship of the critical flutter speed of wings and flutter frequency of folding wings with cruising altitude and cruise Mach number in state of cruise. The whole flight state was analyzed if the folding wings might flutter, and if it took place the structure optimization of wings was needed. Simulation results have a certain guiding significance for practical engineering application.

You might also be interested in these eBooks

Machine Design and Manufacturing Engineering III

View Preview

Info:

Periodical:

Applied Mechanics and Materials (Volume 607)

Pages:

409-412

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.607.409

Citation:

Cite this paper

Online since:

July 2014

Authors:

Sheng Li Lv*, Cheng Wang, Yang Biao Ou, Guang Jun Yang, Xiao Yan Tong

Keywords:

Aeroelastic, Design, Folding Wing, Strength

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

Citation:

* - Corresponding Author

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] Lv. SL, Ping Liu, Yang. GJ, and Tong. XY, Improved Design and Dynamic Simulation of High Aspect Ratio Folding Wings, Applied Mechanics and Materials Vols. 249-250 (2013) pp.410-414.

DOI: 10.4028/www.scientific.net/amm.249-250.410

Google Scholar

[8] Xie. C, Yang.C. Geometric nonlinear aeroelastic problems of high aspect ratio aircraft, The national air elastic papers of academic exchange . 2004, 12(2)：97-101.

Google Scholar