Hostname: page-component-7479d7b7d-c9gpj Total loading time: 0 Render date: 2024-07-13T15:38:35.406Z Has data issue: false hasContentIssue false
  • English
  • Français

Recent Developments in the Structural Approach to Aeroelastic Problems

Published online by Cambridge University Press:  28 July 2016

D. Williams
D. Williams*
Affiliation:
Royal Aircraft Establishment
Get access Rights & Permissions [Opens in a new window]

Abstract

The 899th Lecture to be given before the Royal Aeronautical Society was held on 11th February 1954 at the Institution of Mechanical Engineers, Storey's Gate, London, S.W.I. Mr. G. R. Edwards, C.B.E., F.R.Ae.S., Vice-President of the Society, presided. Introducing the Lecturer, Dr. D. Williams, M.I.Mech.E., F.R.Ae.S., Mr. Edwards said that Dr. Williams was really too well known to need any introduction; his activities had been devoted in recent years to structural problems as applied to aeroplanes. Without reciting his attainments in detail, the job he had tackled in recent years at the Royal Aircraft Establishment and about which he had written papers, covered such subjects as vibration, wing flutter, sandwich construction, the effect of blast on aeroplanes, energy theorems, fatigue, dynamic loading by gusts and landing impacts, water-borne runways and nose-wheel shimmy, a variety of subjects one or all of which had caused most of them a great deal of anguish at one time or another.

Type
Research Article
Information
The Aeronautical Journal , Volume 58 , Issue 522 , June 1954 , pp. 403 - 421
Copyright
Copyright © Royal Aeronautical Society 1954

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. Von kármán, T.and Biot, M. A. (1940). Mathematical Methods in Engineering. McGraw Hill, 1940.Google Scholar
2. Frazer, R. A., Duncan, W. J.and Collar, A. R. (1946). Elementary Matrices. Cambridge University Press, 1946.Google Scholar
3. Levy, S. (1953). Structural Analysis and Influence Coefficients for Delta Wings. Journal of the Aeronautical Sciences, July 1953.Google Scholar
4. Woodger, M. Data on the use of A.C.E. Pilot Model for Linear Algebra. Maths. Division, N.P.L., unpublished note.Google Scholar
5. Levy, S. (1953). Influence Coefficients of Tapered Cantilever Beams Computed on S.E.A.C. Journal of Applied Mechanics, March 1953.Google Scholar
6. Timoshenko|S. (1940). Theory of Plates and Shells. McGraw-Hill Book Co., 1940.Google Scholar
7. Southwell, R. V. (1946). Relaxation Methods in Theoretical Physics. Oxford, The Clarendon Press, 1946.Google Scholar
8. Hall, A. H. (1953). A Simplified Theory of Swept Wing Deformation. N.A.E.C. Report No. 19, 1953.Google Scholar
9. Reissner, E. and Stein, M. (1951). Torsion and Transverse Bending of Cantilever Plates. N.A.C.A. T.N. 2369, 1951 Google Scholar
10. Stein, M. and Anderson, J. E. (1952). Deflection and Stress Analysis of Thin Solid Wings of Arbitrary Plan Form with particular reference to Welta Wings. N.A.C.A. T.N. 2621, February 1952.Google Scholar
11. Fung, Y. C. (1953). Bending of Thin Elastic Plates of Variable Thickness. Journal of the Aeronautical Sciences, July 1953.CrossRefGoogle Scholar