항공기 복합재료 적용 시편의 압축 강도 연구

The laminated sequence and thickness of a composite structure is an important design parameter which affect the strength and impact damage. In this study, it was investigated the residual strength of carbon fiber laminate after impact damage by the experimental investigation. The tensile strength te...

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Bibliographic Details
Published in항공우주시스템공학회지 Vol. 3; no. 1; pp. 12 - 16
Main Authors 공창덕(Changduk Kong), 박현범(Hyunbum Park), 김상훈(Sanghoon Kim), 이하승(Haseung Lee)
Format Journal Article
LanguageKorean
Published 항공우주시스템공학회 2009
Subjects
Open hole test
Compression test
Impact damage
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Summary:The laminated sequence and thickness of a composite structure is an important design parameter which affect the strength and impact damage. In this study, it was investigated the residual strength of carbon fiber laminate after impact damage by the experimental investigation. The tensile strength test and compressive strength test were used to find the mechanical properties, previously. Impact test was performed using low-velocity drop-weight test equipment. The impact damages were finally assessed by the compressive strength test. The investigation results revealed the residual strength of the damaged specimens due to the impact damage.
Bibliography:KISTI1.1003/JNL.JAKO200920855544449
ISSN:1976-6300
2508-7150