Characterization of BMS 8-212 for Use in Penetration Simulations

A program to simulate the performance of aircraft composite material as uncontained engine fragment barriers has been initiated and supported by the Federal Aviation Administration (FAA). Computational constitutive models of the shields are an important part of that program. An important initial step in the FAA program was the determination of the lamina properties of a representation carbon-fiber composite panel. BMS 8-212 lamina properties for use in the computational modeling of aircraft shielding systems were determined in this study. The carbon-reinforced BMS 8-212 composite lay-ups that were tested were unidirectional, 0.351 inches thick (45-ply) flat panels. The mechanical responses of the flat panel unidirectional specimens were assumed to be representative of the behavior of the matrix-dominated compressive BMS 8-212 lamina responses in the transverse and normal directions. The rate sensitivity of the flat-panel specimens was determined for loading rates between 0.001 s-1 and 1000 s-1. In that regime, the transverse and normal failure stresses were found to increase by approximately 1.5.

  • Record URL:
  • Corporate Authors:

    Lawrence Livermore National Laboratory

    7000 East Avenue
    Livermore, CA  United States  94550

    Federal Aviation Administration

    800 Independence Avenue, SW
    Washington, DC  United States  20591
  • Authors:
    • Kay, G
    • Urabe, D
    • Shields, A
    • DeTeresa, S
  • Publication Date: 2009-9


  • English

Media Info

  • Media Type: Print
  • Edition: Final Report
  • Pagination: 24p

Subject/Index Terms

Filing Info

  • Accession Number: 01150573
  • Record Type: Publication
  • Files: TRIS, USDOT
  • Created Date: Feb 9 2010 3:16PM