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

Continuing Chapter V, internal stress resultants are established for the open rings in (he fuselage due to the various statically equivalent and self‐equilibrating load systems. The determination of the frame redundancies leads immediately to the corresponding results for the closed rings. The procedure is developed for both single‐ and double‐cell cross‐sections with cither singly‐or doubly‐connected rings. A brief account is also given of the flexibility of a diaphragm or bulkhead, describing how cither the force or displacement method may be used. The analysis of the fuselage basic system concludes with an investigation of thermal stresses in the closed frames.