Flutter Analysis of Composite Wing Using Differential Quadrature Method

Yan Ping Xiao; Jun  Yang; Jun Li  Yang

doi:10.4028/www.scientific.net/AMR.765-767.3147

Paper Titles

Corrosion Behavior of Rebar HPB235 in NaCl Solution
p.3130

The Effect of Inclusions on the Formation of Intragranular Ferrite
p.3134

Property Research of Concrete Mixed with Flyash
p.3139

Microstructure and Properties of Alloys with Equal Atomic Principal Components
p.3143

Flutter Analysis of Composite Wing Using Differential Quadrature Method
p.3147

Research on Wellbore Stability in Formation with Anisotropic Strength
p.3151

Dynamic Test of Bird Strike on a Flat Plate Made from LY-12 Aluminium
p.3158

Properties of Freestanding Buckypapers with Monodispersion of Multi-Walled Carbon Nanotube Aqueous Solution
p.3162

Interfacial Properties for MEA and MEA-Water Mixtures
p.3166

HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 765-767Flutter Analysis of Composite Wing Using...

Flutter Analysis of Composite Wing Using Differential Quadrature Method

Abstract:

Considering the geometric and material coupling of a composite wing, the equations of motion are derived based on Hamilton theory. Frequencies computing and validation of a composite wing with bending-torsion coupling using differential quadrature method (DQM). And the DQM is applied to the flutter speed solution of a composite wing. The results thus obtained are then compared with some available results and a good agreement is observed. The computing time of DQM is highly improved compared with Galerkin method. Moreover, the effect of material coupling rigidity on flutter speed is analyzed and this is important to the design of composite wings.

You might also be interested in these eBooks

View Preview

Info:

Periodical:

Advanced Materials Research (Volumes 765-767)

Pages:

3147-3150

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.765-767.3147

Citation:

Cite this paper

Online since:

September 2013

Authors:

Yan Ping Xiao, Jun Yang, Jun Li Yang

Keywords:

Bending-Torsion Coupling, Composite, DQM, Flutter

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

Citation:

References

[1] Qin Z, Librescu L. Dynamic aeroelastic response of aircraft wings modeled as anisotropic thin-walled beams. J Aircraft 2003: 40: 532–43.

DOI: 10.2514/2.3127

Google Scholar

[2] Librescu L, Song O. Thin-walled composite beams: theory and application. The Netherlands: Springer; (2006).

Google Scholar

[3] Banerjee JR, Williams FW. Free vibration of composite beams – an exact method using symbolic computation. J Aircraft 1995; 32: 636–42.

DOI: 10.2514/3.46767

Google Scholar

[4] J.R. Banerjee, H. Su, C. Jayatung. A dynamic stiffness element for free vibration analysis of composite beams and its application to aircraft wings. Computers and Structures 86 (2008) 573–579.

DOI: 10.1016/j.compstruc.2007.04.027

Google Scholar

[5] Chen Guibin, Zou Congqing, Yang Chao. Aeroelastic design basis[M]. Beijing University of Aeronautics and Astronautics publication. 2004: 64-67.

Google Scholar

[6] Kaihong Wang, Daniel J. Inman, Charles R. Farrar. Modeling and analysis of a cracked composite cantilever beam vibrating in coupled bending and torsion. Journal of Sound and Vibration 284 (2005) 23–49.

DOI: 10.1016/j.jsv.2004.06.027

Google Scholar