The distributions of the interacting loads between orthogonal stiffeners and the shell wall are computed for a long circular cylindrical shell subjected to internal pressure. Identical stringers are equally spaced around the circumference, and identical frames, or rings, are equally spaced along the length. Both the stringers and frames are on the inside of the shell wall. Closed-end pressure vessel effects are included. A comparison is made between linear elastic response and geometrically nonlinear elastic response. The example problem has dimensions of the fuselage of a typical transport aircraft and has a composite material shell wall and symmetric stiffeners. The inclusion of geometric nonlinearity is found to increase the loads carried by the stiffeners and to decrease the pillowing, or bending, of the shell. However, the nonlinear response exhibits the most severe bending in a narrow boundary layer adjacent to the stringer midway between the frames, resulting in a larger transverse shear resultant in the shell compared with the linear response. The interacting normal load intensity exhibits singular behaviour at the stiffener intersection for both linear and nonlinear analyses.
Interacting loads in an orthogonally stiffened composite cylindrical shell
Sich gegenseitig beeinflussende Belastungen in einer orthogonal versteiften Verbundstoff-Zylinderschale
AIAA Journal ; 33 , 7 ; 1319-1326
1995
8 Seiten, 20 Bilder, 7 Quellen
Article (Journal)
English
Zylinderschale , Versteifung , Reifen (Ring) , Biegebeanspruchung , Innendruck , Carbonfaser , Epoxidharz , Flugzeugzelle , Flugzeugrumpf , Außenhaut , Elastizität , Nichtlinearität , Grenzfläche , Scherspannung , Querrichtung , mathematisches Modell , Differenzialgleichung , Integralgleichung , Verlagerung , Näherungsverfahren , Vektor , Dehnung , Biegemoment
Interacting Loads in an Orthogonally Stiffened Composite Cylindrical Shell
Online Contents | 1995
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