Author： M.A. W.S. Hemp
Publisher： Emerald Group Publishing Ltd
ISSN： 0002-2667
Source： Aircraft Engineering, Vol.21, Iss.8, 1993-12, pp. : 248-251
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Abstract
AIRCRAFT wings, tail planes, fuselages and control surfaces have to satisfy certain mandatory requirements of stiffness. These requirements arc designed to ensure the absence of aero-elastic troubles. They all take the form of a minimum specified limit to a stiffness, calculated or measured under the application of a definite force and constraint system. A 'stiffness' may be defined as the ratio of a force to its 'corresponding' displacement (see 5.2) and so the calculation of stiffnesses reduces itself to a 'deflection problem'(1.1 (2)).
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