Abstract
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), uses an expandable Kevlar honeycomb to dissipate kinetic energy through crushing. The DEA incorporates a unique flexible-hinge design that enables the honeycomb to be packaged and stowed efficiently until needed for deployment. Experimental evaluation of the DEA included dynamic crush tests of multicell components and vertical drop tests of a composite fuselage section retrofitted with DEA blocks onto multiterrain. Finite-element models of the test articles were developed and simulations were performed using the transient dynamic code LS-DYNA. 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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Information
Published In
Journal of Aerospace Engineering
Volume 27 • Issue 3 • May 2014
Pages: 424 - 436
Copyright
© 2014 American Society of Civil Engineers.
History
Received: Feb 14, 2013
Accepted: May 29, 2013
Published online: Jun 15, 2013
Published in print: May 1, 2014
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