Kombinovaný parametr pro grafické vyhodnocení únosnosti konstrukce trupu

A combined parameter for graphic evaluation of the load capacity of fuselage

lecture

en

Proper determination of the total load capacity of semi-monocoque structures without significant structural elements is a complex problem, which results in weight reduction of the designed structure. One critical failure can start the avalanche propagation of following failures and cause the total collapse of the structure. A typical example is a fuselage structure, which is stiffened by longitudinal stringers with similar shape and cross-section area. Therefore, in this study, we present a design and research of new specific combined parameters for faster determination of the load capacity of metal thin-walled semi-monocoque structures. The graphic visualization and evaluation of the avalanche propagation start is a post-processing method for determining a load capacity based on the results of analytical methods. New parameters were tested to evaluate the typical fuselage sections of a small transport aircraft in the CS-23 regulation category and to effectively determine the total load capacity of the fuselage structure.

Proper determination of the total load capacity of semi-monocoque structures without significant structural elements is a complex problem, which results in weight reduction of the designed structure. One critical failure can start the avalanche propagation of following failures and cause the total collapse of the structure. A typical example is a fuselage structure, which is stiffened by longitudinal stringers with similar shape and cross-section area. Therefore, in this study, we present a design and research of new specific combined parameters for faster determination of the load capacity of metal thin-walled semi-monocoque structures. The graphic visualization and evaluation of the avalanche propagation start is a post-processing method for determining a load capacity based on the results of analytical methods. New parameters were tested to evaluate the typical fuselage sections of a small transport aircraft in the CS-23 regulation category and to effectively determine the total load capacity of the fuselage structure.

únosnost, trup, poloskořepina, pevnostní kontrola, porucha

load capacity, fuselage, semi-monocoque, stress analysis, failure

07.12.2017

CRC Press

London, UK

171–175

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