Simulating the Response of a Composite Honeycomb Energy Absorber: Part 2. Full-Scale Impact Testing

• Published in: Journal of aerospace engineering
• Main Authors: Fasanella, EL, Annett, MS, Jackson, KE, Polanco, MA
• Format: Journal Article
• Language: English
• Published: 17.06.2013
• Subjects: Aircraft accidents; Aircraft components; Computer simulation; Finite element method; Helicopters; Honeycomb; Honeycomb construction; Spacecraft
• ISSN: 0893-1321
• DOI: 10.1061/(ASCE)AS.1943-5525.0000358

NASA has sponsored research to evaluate an externally deployable composite honeycomb designed to attenuate loads in the event of a helicopter crash. The concept, designated the Deployable Energy Absorber (DEA), is an expandable Kevlar registered honeycomb. The DEA incorporates a flexible hinge that allows the honeycomb to be stowed collapsed until needed during an emergency. Evaluation of the DEA began with material characterization of the Kevlar registered -129 fabric/epoxy, and ended with a full-scale crash test of a retrofitted MD-500 helicopter. During each evaluation phase, finite element models of the test articles were developed and simulations were performed using the dynamic finite element code, LS-DYNA registered . The paper will focus on simulations of two full-scale impact tests involving the DEA, a mass-simulator and a DEA-retrofitted MD-500 helicopter. Isotropic (MAT24) and composite (MAT58) material models, which were assigned to DEA shell elements, were compared. Based on simulations results, the MAT58 model showed better agreement with test.