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  • NASA/TM2013-217869

    May 2013

    An Erratum was added to this report October 2014.

    J. Michael Pereira, Duane M. Revilock, Bradley A. Lerch and Charles R. RuggeriGlenn Research Center, Cleveland, Ohio

    Impact Testing of Aluminum 2024 and Titanium 6Al-4V for Material Model Development

    DOT/FAA/TC12/58

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  • NASA/TM2013-217869

    May 2013

    An Erratum was added to this report October 2014.

    J. Michael Pereira, Duane M. Revilock, Bradley A. Lerch and Charles R. RuggeriGlenn Research Center, Cleveland, Ohio

    Impact Testing of Aluminum 2024 and Titanium 6Al-4V for Material Model Development

    DOT/FAA/TC12/58

    National Aeronautics andSpace Administration

    Glenn Research CenterCleveland, Ohio 44135

  • Acknowledgments

    Available from

    NASA Center for Aerospace Information7115 Standard DriveHanover, MD 210761320

    National Technical Information Service5301 Shawnee Road

    Alexandria, VA 22312

    Available electronically at http://www.sti.nasa.gov

    Level of Review: This material has been technically reviewed by technical management.

    The authors recognize the work of Dr. Richard Rogers in performing the texture analyses.

    Erratum

    Issued October 2014 for

    NASA/TM2013-217869Impact Testing of Aluminum 2024 and Titanium 6Al-4V for Material Model Development

    J. Michael Pereira, Duane M. Revilock, Bradley A. Lerch and Charles R. Ruggeri

    May 2013

    Table 6(e), column 5: Header has been changed to read as follows:

    Trade names and trademarks are used in this report for identifi cation only. Their usage does not constitute an offi cial endorsement, either expressed or implied, by the National Aeronautics and

    Space Administration.

    (e) Impact Results for 0.5 in. Thick Ti-6Al-4VTest Projectile mass,

    gramProjectile impact

    velocity,ft/sec

    Projectile exitvelocity, ft/sec

    Plug exit velocity, ft/sec

    Plug depth,in.

    Comments

    DB177 126.3 896 475 620 Full PenetratedDB178 126.4 865 424 522 Full PenetratedDB179 126.2 713 241 360 Full PenetratedDB180 126.2 646 152 310 Full PenetratedDB182 126.4 527 0 0 .053 ContainedDB184 126.3 581 0 0 .237 ContainedDB185 126.2 597 0 0 .308 ContainedDB186 126.4 578 0 0 .187 ContainedDB192 126.3 630 0 153 Full Contained/plug releasedDB193 126.3 629 104 226 Full PenetratedDB195 126.3 616 0 132 Full Contained/plug released

  • NASA/TM2013-217869 iii

    Executive Summary One of the difficulties with developing and verifying accurate impact models is that parameters such

    as high strain rate material properties, failure modes, static properties, and impact test measurements are often obtained from a variety of different sources using different materials, with little control over consistency among the different sources. In addition there is often a lack of quantitative measurements in impact tests to which the models can be compared.

    To alleviate some of these problems, a project is underway to develop a consistent set of material property, impact test data and failure analysis for a variety of aircraft materials that can be used to develop improved impact failure and deformation models. This project is jointly funded by the NASA Glenn Research Center and the FAA William J. Hughes Technical Center. Unique features of this set of data are that all material property data and impact test data are obtained using identical material, the test methods and procedures are extensively documented and all of the raw data is available. Four parallel efforts are currently underway: Measurement of material deformation and failure response over a wide range of strain rates and temperatures and failure analysis of material property specimens and impact test articles conducted by The Ohio State University; development of improved numerical modeling techniques for deformation and failure conducted by The George Washington University; impact testing of flat panels and substructures conducted by NASA Glenn Research Center.

    This report describes impact testing which has been done on aluminum (Al) 2024 and titanium (Ti) 6Al-4vanadium (V) sheet and plate samples of different thicknesses and with different types of projectiles, one a regular cylinder and one with a more complex geometry incorporating features representative of a jet engine fan blade. Data from this testing will be used in validating material models developed under this program. The material tests and the material models developed in this program will be published in separate reports.

  • NASA/TM2013-217869 v

    Contents Executive Summary ..................................................................................................................................... iii 1.0 Introduction ......................................................................................................................................... 1 2.0 Methods ............................................................................................................................................... 1

    2.1 Materials .................................................................................................................................... 2 2.1.1 Material Chemistry ..................................................................................................... 2 2.1.2 Material Texture and Microstructure .......................................................................... 3

    2.2 Small Panel Test Setup .............................................................................................................. 3 2.2.1 Al-2024 Test Specimens ............................................................................................. 3 2.2.2 Ti-6Al-4V Test Specimens ......................................................................................... 5 2.2.3 Projectiles ................................................................................................................... 5 2.2.4 Gas Gun ...................................................................................................................... 6 2.2.5 Instrumentation ........................................................................................................... 6

    2.3 Large Panel Test Setup ............................................................................................................ 11 2.3.1 Test Specimens ......................................................................................................... 11 2.3.2 Projectile ................................................................................................................... 11 2.3.3 Instrumentation ......................................................................................................... 13

    3.0 Results and Discussion ...................................................................................................................... 13 3.1 Small Panel Impact Tests .....................................................................................................