The Effect of Loading Parameters on Fatigue of Composite Laminates: Part IV Information Systems

Details

• Creators:
  Hahn, H. T. ; Turkgenc, O.
• 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
  • Engineering tolerances
  • Mechanical fatigue
• Publication/ Report Number:
  DOT/FAA/AR-00/48
• Resource Type:
  Tech Report
• Geographical Coverage:
  United States
• Edition:
  Final Report
• Contracting Officer:
  Shyprykevich, Peter
• Corporate Publisher:
  United States. Department of Transportation. Federal Aviation Administration. William J. Hughes Technical Center
• Description:
  Damage tolerance, damage resistance and durability assessments of aircraft composite structures are essential components of certification. The certification procedure requires lengthy experimental validation of those assessments, although much research has been conducted to understand the behavior of polymer matrix composites under service conditions. A fair amount of data is available together with a number of analytical models in these areas of research. However, because of the vast number of parameters involved, a generic model is rather difficult to develop. The ultimate goal of this study is the identification of design parameters to be used in the development of information system tools that can help engineers synthesize different sets of data efficiently.
• Format:
  PDF
• Funding:
  DTFA03-92-A-00003
• Download URL:
  https://rosap.ntl.bts.gov/view/dot/93978/dot_93978_DS1.pdf
• File Type:
  [PDF - 5.20 MB]
• Collection(s):
  FAA William J. Hughes Technical Center for Advanced Aerospace
• Main Document Checksum:
  urn:sha-512:10afc78859d068a1f8f74f54f2b171a29e941b26bed8c9ad5ca0031148c627fe90932392ac15cc9a792b8c73cef47ed036c7c975ca749da312a5115715f7b927