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.
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 ; 31 , 5 ; 133-143
1959-05-01
11 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
The Analysis of Fuselages of Arbitrary Cross-section and Taper
Emerald Group Publishing | 1959
|The Analysis of Fuselages of Arbitrary Cross-section and Taper
Emerald Group Publishing | 1961
|The Analysis of Fuselages of Arbitrary Cross-section and Taper
Emerald Group Publishing | 1961
|The Analysis of Fuselages of Arbitrary Cross-section and Taper
Emerald Group Publishing | 1959
|The Analysis of Fuselages of Arbitrary Cross-section and Taper
Emerald Group Publishing | 1959
|