| タイトル | Simulating the Response of a Composite Honeycomb Energy Absorber |
| 本文（外部サイト） | http://hdl.handle.net/2060/20120008167 |
| 著者（英） | Fasanella, Edwin L.; Jackson, Karen E.; Polanco, Michael A. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2012-04-15 |
| 言語 | eng |
| 内容記述 | 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. |
| NASA分類 | Composite Materials |
| レポートNO | NF1676L-13139 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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