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

In the two short sections which close Chapter VII, an improved ring programme is developed which allows i.a. for the application of externally applied moments on the ring vertices and a preliminary and tentative extension of the analysis takes into account the bending stiffness of some of the flanges. The final chapter returns to the subject of the uniform, circular section fuselage and develops the theory for the polygonized cross‐section in analytical form. Standard expressions are given for the elements of the D,, matrix and application of the analysis to a simple example suggests that the effect of the polygonization on the accuracy of the stress distribution is insignificant.