The Effect of Loading Parameters on Fatigue of Composite Laminates: Part V

Details

• Creators:
  Han, H. T. ; Choi, S. W.
• Corporate Creators:
  University of California, Los Angeles. Mechanical and Aerospace Engineering Department
• Corporate Contributors:
  United States. Department of Transportation. Federal Aviation Administration. Office of Aviation Research
• Subject/TRT Terms:
  • Airplanes
  • Composite materials
  • Laminates
  • Epoxides
  • Impact loads
  • Engineering tolerances
  • Composite materials
  • Compressive strength
  • Damage
  • Fatigue(Mechanics)
  More +
• Publication/ Report Number:
  DOT/FAA/AR-01/24
• Resource Type:
  Tech Report
• Geographical Coverage:
  United States
• Edition:
  Final Report
• Corporate Publisher:
  United States. Department of Transportation. Federal Aviation Administration. William J. Hughes Technical Center
• Description:
  This report is the fifth in a series of reports on the damage growth of notched and visible impact-damaged AS4/3501-6 graphite/epoxy quasi-isotropic laminates under long-term mechanical fatigue loading. The effects of load type, load level, load sequence, and spectrum modification are evaluated in this study. X-ray radiography is taken of the test specimens to monitor the fatigue damage, which are in the form of splitting and delamination around the center hole of a specimen.
• Format:
  PDF
• Funding:
  95-G-021
• Download URL:
  https://rosap.ntl.bts.gov/view/dot/93984/dot_93984_DS1.pdf
• File Type:
  [PDF - 4.60 MB]
• Collection(s):
  FAA William J. Hughes Technical Center for Advanced Aerospace
• Main Document Checksum:
  urn:sha-512:b7012cbea6f238e4899e370d1d8969f026547b07f2819d3f4f88d4820aab2d7fda7c82731a7259a7f58ecca786c3a4dcf425aa095babf506102353fd30679649