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The Symmetric Vibrations of Aircraft

Published online by Cambridge University Press:  07 June 2016

R. W. Traill-Nash
R. W. Traill-Nash*
Affiliation:
Department of Supply and Development, Aeronautical Research Laboratories, Melbourne
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Summary

The eigenvalue equations for symmetric vibration of a complete aircraft are derived in a very general form. The “lumped mass” approximation to the continuous mass distribution is used and sub-matrices are associated with properties of relatively simple branches of the system. The final eigenvalue equations are expressed in terms of these sub-matrices, so that in a numerical application the physical system, as such, is considered only in relation to the properties of the simple branches. It is assumed initially that the aircraft wing and tail have flexural axes of the conventional type, but it is shown in the Appendix that under certain conditions the treatment can be generalised to cover swept and cranked wing aircraft.

Type
Research Article
Information
Aeronautical Quarterly , Volume 3 , Issue 1 , May 1951 , pp. 1 - 22
Copyright
Copyright © Royal Aeronautical Society. 1951

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References

1. Frazer, R. A., Duncan, W. J. and Collar, A. R. (1946). Elementary Matrices, Cambridge University Press, 1946.Google Scholar
2. Morris, J. and Green, G. S. (1945). The Pitching Vibrations of an Aircraft. R. & M. 2291, August 1945.Google Scholar
3. Duncan, W. J. and Collar, A. R. (1934). A Method for the Solution of Oscillation Problems by Matrices. Phil. Mag. S 7, Vol. 17, No. 115, May 1934, p. 865. Google Scholar
4. Collar, A. R. (Chairman, Oscillations: Sub-Committee) (1949). Notes on (a) The Effects of Shear Stiffness on the Bending Vibrations of Beams, (b) The Distortion Characteristics of Swept and Cranked Wings. A.R.C. No. 12,028, Struct. 1263, Os. 785.Google Scholar
5. Williams, D. (1949). Note on the Distortion Characteristics of Swept and Cranked Wings in Relation to Flutter and other Aero-elastic Phenomena. R.A.E. Tech. Note No. Structures 44, July 1949.Google Scholar
6. Anderson, R. A. and Houbolt, J. C. (1948). The Effect of Shear Lag on Bending Vibration of Box-beams. N.A.C.A. Tech. Note No. 1583, May 1948.Google Scholar
7. Morris, J. and Head, J. W. (1944). The “ Escalator “ Process for the Solution of Lagran- gian Frequency Equations. Phil. Mag. S 7, Vol. 35, No. 350, November 1944, p. 735.CrossRefGoogle Scholar