C.E. Harris

An advanced analytical methodology has been developed for predicting the residual strength of stiffened thin-sheet riveted shell structures such as those used for the fuselage of a commercial transport aircraft. The crack-tip opening angle elastic-plastic fracture criterion has been coupled to a geometric and material nonlinear finite element shell code for analyzing complex structural behavior. An automated adaptive mesh refinement capability together with global/local methods have been developed to predict the behavior of fuselage structure with long cracks. The methodology is in the process of being experimentally verified and transferred to industry.

5th International Conference on Structural Airworthiness of New and Aging Aircraft, Hamburg, 1993

Conference Paper

englisch

21,0 x 29,7 cm, 6 Seiten

DGLR-Bericht, 1993, 1993-02, 5th International Conference on Structural Airworthiness of New and Aging Aircraft - Proceedings; S.151-156; 1993; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

structural fatigue

Bestellbar

1993