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)).
The Elementary Theory of. Stressed-Skin Construction
Two Further Instalments of a Series on the Stressing of Modern Aeroplane Structures
Aircraft Engineering and Aerospace Technology ; 21 , 8 ; 248-251
01.08.1949
4 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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