The Bending of Fuselage Shells: A New Approach, Based on Laboratory Compression Tests, that is Analogous to the Calculation of the Form Factor of a Solid Beam Available to Purchase

THE paper suggests a new approach to the calculation of the bending strength of semi‐monocoque (and possibly fully mono‐coque) aircraft fuselage shells. The method described uses directly load‐deflexion graphs obtained from laboratory compression tests on panels representative of the shell at the section under consideration, and is analogous to the calculation of the form factor for a solid beam section, which factor is dependent on the shape of the section and on the stress‐strain relationship of the material of which the beam is made.