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Accession Number
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N20120008167
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Title
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Simulating the Response of a Composite Honeycomb Energy Absorber, Part 1.
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Publication Date
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Apr 2012
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Media Count
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24p
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Personal Author
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E. L. Fasanella K. E. Jackson M. A. Polanco
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Abstract
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This paper describes the experimental and analytical evaluation of an externally deployable composite honeycomb structure that is designed to attenuate impact energy during helicopter crashes. The concept, designated the Deployable Energy Absorber (DEA), utilizes an expandable Kevlar (Registered Trademark) honeycomb to dissipate kinetic energy through crushing. The DEA incorporates a unique flexible hinge design that allows the honeycomb to be packaged and stowed until needed for deployment. Experimental evaluation of the DEA included dynamic crush tests of multi-cell components and vertical drop tests of a composite fuselage section, retrofitted with DEA blocks, onto multi-terrain. Finite element models of the test articles were developed and simulations were performed using the transient dynamic code, LSDYNA (Registered Trademark). In each simulation, the DEA was represented using shell elements assigned two different material properties: Mat 24, an isotropic piecewise linear plasticity model, and Mat 58, a continuum damage mechanics model used to represent laminated composite fabrics. DEA model development and test-analysis comparisons are presented.
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Keywords
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Aircraft accidents
Aircraft safety
Composite structures
Drop tests
Energy absorption
Finite element method
Fuselages
Helicopters
Honeycomb structures
Impact tests
Kevlar(Trademark)
Kinetic energy
Rotary wing aircraft
Simulation
Stress-strain diagrams
Terrain
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Source Agency
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National Aeronautics and Space Administration
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NTIS Subject Category
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71F - Composite Materials
41K - Engineering Materials
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Corporate Author
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National Aeronautics and Space Administration, Hampton, VA. Langley Research Center.
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Document Type
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Conference proceedings
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Title Note
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N/A
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NTIS Issue Number
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1222
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Contract Number
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N/A
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