タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-934
一般注記Carbon fiber reinforced thermoplastic (CFRTP) composites have a great potential for use in aircraft structures especially where toughness is concerned. In this study, experiments are conducted on a fabric-CFRTP and fabric-CFRP composites subjected to the effect of elevated temperature on short beam shear strength and flexural fatigue strength. Composite were fabricated from carbon fiber 8-harness satin fabric reinforced with two thermoplastic matrices, polyethersulphon (PES) and polyetheretherketon (PEEK) and compared with those of an epoxy matrix system. The CFRTP laminates were prepared by the film stacking method, namely thermoplastic resin films and carbon fiber fabric were stacked altermately then consolidated into a laminate by heat and pressure. Short beam shear tests were performed under environmental conditions at temperatures of 25C to 180C. Flexural fatigue tests were performed at a room temperature of 25C and elevated temperatures of 80～90C and 130～140C. Short beam shear strength under elevated temperature conditions for fabric-CFRTP is comparable to that obtained with most fabric-CFRP. The fatigue failure specimens indicated that the tough thermoplastic matrix system shows an improved fatigue behavior compared to the brittle epoxy matrix system, mainly due to resistance to the initiation and growth of fatigue damage related to the matrix.
資料番号: NALTR0934000
レポート番号: NAL TR-934
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ