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.
Simulating the Response of a Composite Honeycomb Energy Absorber. I: Dynamic Crushing of Components and Multiterrain Impacts
Journal of Aerospace Engineering ; 27 , 3 ; 424-436
2013-06-15
132014-01-01 pages
Article (Journal)
Electronic Resource
Unknown
Simulating the Response of a Composite Honeycomb Energy Absorber. II: Full-Scale Impact Testing
Online Contents | 2014
|Multiterrain Earth Landing Systems Applicable for Manned Space Capsules
British Library Conference Proceedings | 2009
|Design of Honeycomb Mesostructures for Crushing Energy Absorption
Online Contents | 2012
|