Transactions of the Korean Society of Mechanical Engineers A (대한기계학회논문집A)

The Korean Society of Mechanical Engineers (대한기계학회)
권호 표지
DOI QR코드

DOI QR Code

Effect of Aluminum Treatment by Plasma on the Bonding Strength Between Aluminum and CFRP Composites

플라즈마를 적용한 알루미늄의 표면처리가 알루미늄/CFRP 복합재의 접합강도에 미치는 영향

  • Published : 2001.12.01
Download PDF
⟨ Previous Next ⟩

Abstract

This paper documents the effect of surface treatment of aluminum on the bonding strength of aluminum/CFRP composites. The surface of aluminum panel was treated by DC plasma. The optimal treatment condition of the aluminum was determined by measuring the contact angle and T-peel strength as functions of mixture ratio of acetylene gas to nitrogen gas. The mixture ratios used were 1:9, 3:7, 5:5, 7:3, and 9:1 Lap shear tests and T-peel tests were performed using surface-treated alumiunm/CFRP composites and regular alumiunm/CFRP composites. The results showed that the contact angle was minimized and the T-peel strength was maximized iota the mixture ratio of 5:5. The results also showed that the shear strength of surface-treated alumiunm/CFRP composites was 34% greater than that of regular alumiunm/CFRP composites. The T-peel strength of surface-treated alumiunm/CFRP composites was also 5 times greater than that of regular alumiunm/CFRP composites.

Keywords

References

  1. Baker, A.A., 1987, 'Fiber Composite Repair of Cracked Metallic Aircraft Components,' Composite, Vol. 18, pp. 293-308 https://doi.org/10.1016/0010-4361(87)90293-X
  2. Ong, C.L., and Shen, S.B., 1990, 'Some Results on Metal and Composite Patch Reinforcement of Aluminum Honeycomb Panel,' Theoretical and Applide Fracture Mechanics, Vol. 14, pp. 145-153 https://doi.org/10.1016/0167-8442(91)90031-E
  3. Ong, C.L., and Shen, S.B., 1990, 'Repair of F-104 Aircraft Nosedome by Composite Patching,' Theoretical and Applied Fracture Mechanics, Vol. 15, pp. 75-83 https://doi.org/10.1016/0167-8442(91)90006-6
  4. Chester, R.J., Walker, K.F. and Chalkley, P.D., 1999, 'Adhesively Bonded Repairs to Primary Aircraft Structure,' International J.of Adhesion and Adhesives, Vol. 19, pp. 1-8 https://doi.org/10.1016/S0143-7496(98)00014-1
  5. Denny J.J. and Mall. S., 1997, 'Characterization of Disbond Effects on Fatigue Crack Growth Behavior in Aluminum Plate with Bonded Composite Patch,' Engineering Fracture Mechanics, Vol. 57, pp. 507-525 https://doi.org/10.1016/S0013-7944(97)00050-7
  6. Schubbe, J. J. and Mall. S., 1999, 'Investigation of a Cracked Thick Aluminum Panel Repaired with a Bonded Composite Patch,' Engineering Fracture Mechanics, Vol. 63, pp. 305-323 https://doi.org/10.1016/S0013-7944(99)00032-6
  7. Baker, A.A., 1999, 'Bonded Composite Repair of Fatigue-Cracked Primary Aircraft Strucure,' Composite Structures, Vol. 47, pp. 431-443 https://doi.org/10.1016/S0263-8223(00)00011-8
  8. 이경엽, 강용태, 양준호, 2001, '에너지 구조재적용을 위한 알루미늄/섬유강화 복합재의 표면처리,' 한국표면공학회지, 제34권 제1호 pp. 56-61
  9. Koh, S. K. Kim, K. H. Kang, B. H. Ha, S. C., 1999, 'New Surface Layer Formation by Ion Assisted Reaction (IAR) and Optimum Plasma Zone (OPZ),' Mitigation of Heat Exchanger Fouling and Its Economic and Environmental Problems, Banff, Canada. July pp. 11-16
  10. ASTM D1876-95, 'Standard test method for peel resistance of adhesive (T-Peel Test),' ASTM Standards, Vol. 15.06, pp. 107-109
  11. ASTM D906-94a, 'Standard Test Method for Strength Properties of Adhesives in Plywood Type Construction in Shear by Tension Loading,' ASTM Standards, Vol. 15.06, pp. 25-28