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原文传递 Impact and Delamination Failure Characterization of BMS 8-212 Composite Aircraft Material. Final rept.

题名：	Impact and Delamination Failure Characterization of BMS 8-212 Composite Aircraft Material. Final rept.
作者：	Powell-D.; Zohdi-T.; Johnson-G.
关键词：	Engine-faliure; Aircraft-engines; Impact-tests; Delamination-; Fragments-; Turbine-engines; Rotor-blades-Turbomachinery; Composite-materials.;High-strain-rate; Ballistics-; Projectiles-; Panels-; Containment-; Carbon-fiber-composites; Tests-.
摘要：	This study was part of a program, sponsored by the Federal Aviation Administration that focused on understanding the behavior of different aircraft materials under impact in the speed range generated from engine uncontained failures. This test program investigated the material response of 8-, 16-, and 32-ply BMS8-212 composite panels provided by The Boeing Company. All tests were performed at the University of California, Berkeley ballistics laboratory using a pneumatic gas gun and half-inch-diameter spherical and flat-ended cylindrical projectiles. The ballistic impact tests indicated that the amount of energy absorbed by a similar composite target panel during impacts above the ballistic limit was nearly constant, showing only a slight increase with increasing initial energy. The amount of energy absorbed per ply increased only slightly for thicker panels. The tests also showed that the cylindrical projectiles required more energy to penetrate the composite panels than the spherical projectiles.
报告类型：	科技报告