Hostname: page-component-848d4c4894-m9kch Total loading time: 0 Render date: 2024-05-05T09:26:02.926Z Has data issue: false hasContentIssue false
  • English
  • Français

Vibration analyses of an equivalent plate wing with an external store

Published online by Cambridge University Press:  27 January 2016

Y.-H. Na ,
J.-H. Kim  and
S.-J. Shin
Y.-H. Na
Affiliation:
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul, Korea
J.-H. Kim
Affiliation:
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul, Korea
S.-J. Shin*
Affiliation:
Institute of Advanced Aerospace Technology, Seoul National University, Seoul, Korea
*
ssjoon@snu.ac.kr
Get access Rights & Permissions [Opens in a new window]

Extract

Generally, pylon-mounted external stores significantly affect the aerodynamic characteristics of the aircraft due to their flexibility. Therefore, many investigations upon the dynamic and aeroelastic characteristics of an aircraft wing with external stores have been done over the last few decades Recently, a study was carried out regarding the aeroelastic effects on wings by the engine placement For severe operation conditions, classical linear theory with a small amount of amplitude vibration may not be an appropriate analysis. Nonlinear vibration analysis will be required, especially when the amplitude of the vibration is larger than the wing thickness. Chia performed static, dynamic, and post-buckling analyses of various isotropic and composite plates for that purpose. Dumir and Bhaskar derived finite element formulations to analyse the nonlinear vibration of beams and plates. Moreover, the variational-asymptotic plate formulation and the accompanying equations for the global analysis for the plates have been studied. That approach accounted every possible geometrical non-linearity associated with large displacement and small strain.

Type
Research Article
Information
The Aeronautical Journal , Volume 118 , Issue 1207 , September 2014 , pp. 1090 - 1098
Copyright
Copyright © Royal Aeronautical Society 2014 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Li, B., Yang, Z.C. and Zhao, L.C. Effect of external stores on futter characteristics of a straight/swept aircraft wing, Key Engineering Materials, 2003, 243-244, pp 111–117.Google Scholar
2. Karpel, M. Effcient vibration mode analysis of aircraft with multiple external store confgurations, J Aircraft, 1988, 25, (8), pp 747–751.Google Scholar
3. Librescu, L. and Song, O.S. Dynamics of composite aircraft wings carrying external stores, AIAA J, 2008, 46, (3), pp 568–577.Google Scholar
4. Terashima, H. and Fujii, K. Infuence of stores on the transonic futter of a delta wing confguration, AIAA J, 2007, 45, (1), pp 237–246.Google Scholar
5. Mardanpour, , Pezhman, , Hodges, , Dewey, H., Neuhart, , Ryan, and Graybeal, , NATHAN Effect of engine placement on aeroelastic trim and stability of fying-wing aircraft, J Aircraft, 2013, 50, (6), pp 1716–1725.Google Scholar
6. Mei, C., Narayanaswami, R. and Rao, G.V. large amplitude free fexural vibrations of thin plates of arbitrary shape, Computers & Structures, 1979, 10, pp 675–681.Google Scholar
7. Chia, C. Y. Nonlinear Analysis of Plates, McGraw-Hill Inc, USA, 1980.Google Scholar
8. Dumir, P.C. and Bhaskar, A. Some erroneous fnite element formulation of nonlinear vibrations of beams and plates, J Sound and Vibration, 1988, 123, (3), pp 517–527.Google Scholar
9. Yu, W. Mathematical construction of a reissner-mindlin plate theory for composite laminates, Int J Solids and Structures, 2005, 42, (26), pp 6680–6699.Google Scholar
10. Hodges, , Dewey, H., Yu, , Wenbin, , Patil, and Mayuresh, J. Geometrically-exact, intrinsic theory for dynamics of moving composite plates, Int J Solids and Structures, 2009, 46, (10), pp 2036–2042.Google Scholar
11. Giles, G.L. Further generalization of an equivalent plate representation for aircraft structural analysis, J Aircraft, 1989, 26, (1), pp 67–74.Google Scholar
12. Livne, E. Equivalent plate structural modeling for wing shape optimization including transverse shear, AIAA J, 1994, 32, (6), pp 1278–1288.Google Scholar
13. Kapania, R.K. and Liu, Y. Static and vibration analyses of general wing structures using equivalent-plate models, AIAA J, 2000, 38, (7), pp 1269–1277.Google Scholar
14. Livne, E. and Israel, N. Nonlinear equivalent plate modeling of wing box structures, J Aircraft, 1999, 36, (5), pp 851–865.Google Scholar
15. Bhumbla, R., Kosmatka, J.B. and Reddy, J.N. Free vibration of spinning shear deformable plates composed of composite materials, AIAA J, 1990, 28, (11), pp 1962–1970.Google Scholar
16. Bhumbla, R. and Kosmatka, J.B. Stability of spinning shear deformable laminated composite plates, J Sound and Vibration, 1993, 163, (1), pp 83–99.Google Scholar
17. Weiliang, Y. and Dowell, E. Limit cycle oscillations of a futtering cantilever plate, AIAA J, 1991, 29, (11), pp 1929–1936.Google Scholar
18. Dixon, I.R. and Mei, C. Finite Element Analysis of Nonlinear Flutter of Composite Panels, Proc. of the 32nd AIAA/ASME/ASCE/AHS Structures, Structural Dynamics and Materials Conference, AIAA Paper No.91-1173-CP, 1991, pp 2002–2010.Google Scholar
19. Gray, C.E., Mei, C. and Shore, C.P. Finite element method for large-amplitude two-dimensional panel futter at hypersonic speeds, AIAA J, 1991, 29, (2), pp 290–298.Google Scholar
20. Chiang, C.K., Xue, D.Y. and Mei, C. Nonlinear Vibration of Thin Arbitrarily Laminated Composite Plates Subjected to Harmonic Excitations Using DKT Elements, Proc. of the 34th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 19-22 April, AIAA Paper No. 93-1324-CP.1993.Google Scholar