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The Static Aeroelasticity of Slender Configurations

Part III: Static Stability

Published online by Cambridge University Press:  07 June 2016

G. J. Hancock
G. J. Hancock*
Affiliation:
Department of Aeronautical Engineering, Queen Mary College, University of London
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Summary

The validity and applicability of the static margin (stick fixed) Kn ,

where

as defined by Gates and Lyon is shown to be restricted to the conventional flexible aircraft. Alternative suggestions for the definition of static margin are put forward which can be equally applied to the conventional flexible aircraft of the past and the integrated flexible aircraft of the future. Calculations have been carried out on simple slender plate models with both linear and non-linear aerodynamic forces to assess their static stability characteristics.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 14 , Issue 1 , February 1963, pp. 75 - 104
Copyright
Copyright © Royal Aeronautical Society. 1963

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References

1. Hancock, G. J. The Static Aeroelastic Deformation of Slender Configurations. Part I— Some Elementary Concepts of Static Deformation. Aeronautical Quarterly, Vol. XII, p. 293, August 1961.CrossRefGoogle Scholar
2. Hancock, G. J. The Static Aeroelastic Deformation of Slender Configurations. Part II— Some Calculations on Slender Plate Aircraft, Including Non-Linear Aerodynamics. Aeronautical Quarterly, Vol. XII, p. 372, November 1961.CrossRefGoogle Scholar
3. Duncan, W. J. The Principles of the Control and Stability of Aircraft. Cambridge University Press, 1952.Google Scholar
4. Gates, S. B. and Lyon, H. M. A Continuation of Longitudinal Stability and Control Analysis. Part I—General Theory. R. & M. 2027, 1944.Google Scholar