Design, Optimization, and Evaluation of A1-2139 Compression Panel with Integral T-Stiffeners

A T-stiffened panel was designed and optimized for minimum mass subjected to constraints on buckling load, yielding, and crippling or local stiffener failure using a new analysis and design tool named EBF3PanelOpt. The panel was designed for a compression loading configuration, a realistic load case...

Full description

Saved in:
Bibliographic Details
Published inNASA Center for AeroSpace Information (CASI). Reports
Main Authors Mulani, Sameer B, Havens, David, Norris, Ashley, Bird, R Keith, Kapania, Rakesh K, Olliffe, Robert
Format Report
LanguageEnglish
Published Hampton NASA/Langley Research Center 01.06.2012
Subjects
Aluminum base alloys
Buckling
Compression tests
Design
Design optimization
Displacement
Failure analysis
Finite element method
Metal plates
Nonlinear analysis
Photogrammetry
Stiffeners
Strain gauges
Online AccessGet full text

Cover

More Information
Summary:A T-stiffened panel was designed and optimized for minimum mass subjected to constraints on buckling load, yielding, and crippling or local stiffener failure using a new analysis and design tool named EBF3PanelOpt. The panel was designed for a compression loading configuration, a realistic load case for a typical aircraft skin-stiffened panel. The panel was integrally machined from 2139 aluminum alloy plate and was tested in compression. The panel was loaded beyond buckling and strains and out-of-plane displacements were extracted from 36 strain gages and one linear variable displacement transducer. A digital photogrammetric system was used to obtain full field displacements and strains on the smooth (unstiffened) side of the panel. The experimental data were compared with the strains and out-of-plane deflections from a high-fidelity nonlinear finite element analysis.