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Characterization of BMS 8-212 for Use in Penetration Simulations.
| 题名： | Characterization of BMS 8-212 for Use in Penetration Simulations. |
| 作者： | G. Kay; D. Urabe; A. Shields; S. DeTeresa; |
| 关键词： | engine failure,aircraft engines,composite materials,fiber composites,uncontained engine fragment barriers,penetration simulations,aircraft composite materials;lamina, performance simulation, characterization, computerized simulation, rate sensitivity, str |
| 摘要： | 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. / NOTE: Final rept. / Supplementary Notes: Sponsored by Federal Aviation Administration, Washington, DC. / Availability Note: Order this product from NTIS by: phone at 1-800-553-NTIS (U.S. customers); (703)605-6000 (other countries); fax at (703)605-6900; and email at orders@ntis.gov. NTIS is located at 5301 Shawnee Road, Alexandria, VA, 22312, USA. |
| 报告类型： | 科技报告 |
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