TY - JOUR AB - 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. VL - 31 IS - 5 SN - 0002-2667 DO - 10.1108/eb033113 UR - https://doi.org/10.1108/eb033113 AU - Argyris J.H. AU - Kelsey S. PY - 1959 Y1 - 1959/01/01 TI - The Analysis of Fuselages of Arbitrary Cross‐section and Taper: A DSIR Sponsored Research Programme on the Development and Application of the Matrix Force Method and the Digital Computer T2 - Aircraft Engineering and Aerospace Technology PB - MCB UP Ltd SP - 133 EP - 143 Y2 - 2024/03/29 ER -