The flexibility matrices for the unassembled structural elements are discussed and a more concise form developed appropriate to the fuselage structure. A general method is given for obtaining self‐equilibrating flange load and shear flow systems in a single‐cell fuselage, the primary redundancies being defined by a simple transformation matrix. The particular matrix based on the orthogonal stress systems for a circular section is especially convenient. A slight extension of the equations leads also to alternative statically equivalent stress systems in the cover.
Argyris, J. and Kelsey, S. (1959), "The Analysis of Fuselages of Arbitrary Cross‐section and Taper", Aircraft Engineering and Aerospace Technology, Vol. 31 No. 5, pp. 133-143. https://doi.org/10.1108/eb033113Download as .RIS
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