Study on Strength Recovery of Impact Damaged Composite Laminate by External Patch Repair
Recently, composite materials have been extensively used to the aircraft structure due to advantages of high specific strength and low weight. However the composite structure has a disadvantage which is very weak against impact due to foreign object damages. A repair technique using external patch is recognized as an effective method to recover the service life of damaged structures. This work is focusing on the impact damage evaluation and the external patch repair techniques of the aircraft composite structure. The impact damages of composite laminates of the carbon/epoxy UD laminate and the carbon/epoxy fabric face sheets-honeycomb core sandwich laminate are simulated by the drop-weight type impact test equipment The damaged specimens are repaired using the external patch repair method after removing the damaged area. The compressive strength test and analysis results of the repaired impact damaged specimens are compared with the compressive strength test and analysis results of the undamaged specimens and the impact damaged specimens. Finally, the strength recovery capability after repairing is investigated.
External patch repair Impact damage Compressive strength Aircraft composite laminate structure
Kong Changduk Park Hyunbum Lim Sungjin
Department of Aerospace Engineering, Chosun University, 375 Seosuk-dong, Dong-gu,Gwangj, Rep.of Kore Department of Aerospace Engineering, Chosun University, 375 Seosuk-dong, Dong-gu, Gwangj, Rep.of Kor
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
852-855
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）