A series of examples illustrates the application and results of the method previously given for improving the conditioning of the primary redundancies. The transformation matrix giving locally orthogonal redundancies for the parent station is used also to generate the primary self-equilibrating stress systems for sections with different (but related) geometry and varying ring stiffness. A double-cell cross-section is also treated and a brief investigation shows that the general methods developed for establishing primary redundancies in the fuselage can be usefully and economically applied to certain kinds of wing structure. Preparatory to a detailed discussion of cut-outs and modifications in the fuselage structure, the necessary general theory is collected and summarized.
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 ; 33 , 3 ; 71-83
01.03.1961
13 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 | 1959
|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 | 1959
|