NDLI: System-integrated finite element analysis of a full-scale helicopter crash test with deployable energy absorbers

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System-integrated finite element analysis of a full-scale helicopter crash test with deployable energy absorbers

Content Provider	NASA Technical Reports Server (NTRS)
Author	Annett, Martin S. Polanco, Michael A.
Copyright Year	2010
Description	A full-scale crash test of an MD-500 helicopter was conducted in December 2009 at NASA Langley's Landing and Impact Research facility (LandIR). The MD-500 helicopter was fitted with a composite honeycomb Deployable Energy Absorber (DEA) and tested under vertical and horizontal impact velocities of 26-ft/sec and 40-ft/sec, respectively. The objectives of the test were to evaluate the performance of the DEA concept under realistic crash conditions and to generate test data for validation of a system integrated finite element model. In preparation for the full-scale crash test, a series of sub-scale and MD-500 mass simulator tests was conducted to evaluate the impact performances of various components, including a new crush tube and the DEA blocks. Parameters defined within the system integrated finite element model were determined from these tests. The objective of this paper is to summarize the finite element models developed and analyses performed, beginning with pre-test predictions and continuing through post-test validation.
File Size	5289763
Page Count	16
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20100019315
Archival Resource Key	ark:/13960/t6353n35v
Language	English
Publisher Date	2010-05-11
Access Restriction	Open
Subject Keyword	Aircraft Design, Testing And Performance Finite Element Method Crashes Landing Loads Helicopters Impact Velocity Research Facilities Data Systems Impact Loads Energy Absorption Crashworthiness Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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