국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Simulating the Response of a Composite Honeycomb Energy Absorber Part 1;; Dynamic Crushing of Components and Multi-Terrain Impacts
저자	Jackson, Karen E.;; Fasanella, Edwin L.;; Polanco, Michael A.
Keyword	AIRCRAFT ACCIDENTS;; AIRCRAFT SAFETY;; COMPOSITE STRUCTURES;; CRUSHING;; 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
URL	http://hdl.handle.net/2060/20120008167
보고서번호	NF1676L-13139
발행년도	2012
출처	NTRS (NASA Technical Report Server)
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), 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.