Date of Award

Spring 1995

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Engineering Mechanics

Committee Director

Norman F. Knight, Jr.

Committee Member

Chuh Mei

Committee Member

Damodar R. Ambur

Call Number for Print

Special Collections; LD4331.E57B453

Abstract

This paper discusses the mechanism and behavior of load introduction to internally pressurized fuselage crown panels. Emphasis is placed on the finite element modeling of a simulated pressure-box test machine and representative fuselage crown panel. The geometry and mesh requirements for the finite element model are examined through numerical studies which gradually increase in complexity. These numerical studies culminate in the detailed specification of boundary conditions, mesh densities, load introduction mechanisms, element choice and solution process for the simulation of a pressure-box test machine and test panel.

The results obtained using the finite element model are then compared with experimental results. This finite element model correctly replicates full fuselage boundary conditions when loaded by internal cabin pressure. This model will provide analysts with a relatively simple tool for the analysis and development of damage tolerant composite fuselage panels.

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In Copyright. URI: http://rightsstatements.org/vocab/InC/1.0/ This Item is protected by copyright and/or related rights. You are free to use this Item in any way that is permitted by the copyright and related rights legislation that applies to your use. For other uses you need to obtain permission from the rights-holder(s).

DOI

10.25777/ntxw-4g40

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