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

Abstract

Following the self‐equilibrating stress systems developed for the single‐cell fuselage, further stress systems are given for the fuselage with a double‐cell cross‐section. These allow for the direct stress carrying ability of the floor. Wing‐fuselage interaction redundancies are discussed in detail and suitable self‐equilibrating load systems presented. The formation of the associated stress systems in the cover is described with reference to their generation inside the computer. Chapter IV concludes with a brief account of fin attachment loads which serves to introduce two further interaction redundancies to take account of skin attachment. The opening section of Chapter V relates the detailed frame loads to the overall fuselage loading preparatory to the analysis of the closed frames. Matrix equations for the calculation of the statically equivalent wing reactions and of the fuselage moment diagrams are given.

Citation

Argyris, J.H. and Kelsey, S. (1959), "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", Aircraft Engineering and Aerospace Technology, Vol. 31 No. 6, pp. 169-179. https://doi.org/10.1108/eb033125