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

The derived data matrices established for the basic system in the previous issues are assembled to give the compatibility equations from whose solution the redundancies are obtained. The assembly is presented in detail to show the necessary submatrix operations required in the computer. The general solution of the compatibility equations leads to the complete stress distribution and deformation of the regularized fuselage due to external loads, wing or tail interaction redundancies and to thermal strains. From these wc obtain, by use of the cut‐out and modification technique, the corresponding results for the actual fuselage as an independent structure. The interaction redundancies at the wing and tail unit attachments are determined on the assumption that these components are also analysed by the Force Method. Hence the final stress distribution is obtained for the fuselage as an integral part of the complete aircraft structure.