Engine Debris Fuselage Penetration Testing, Phase I

Details

• Creators:
  Lundin, Steven J
• Corporate Creators:
  Commander Naval Air Warfare Center (CA)
• Corporate Contributors:
  United States. Department of Transportation. Federal Aviation Administration. Office of Aviation Research
• Subject/TRT Terms:
  • Turbine engines
  • Fuselages
  • Foreign object debris
  • Hazard mitigation
• Publication/ Report Number:
  DOT/FAA/AR-01/27
• 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:
  During February 1999, the Naval Air Warfare Center Weapons Division (NAWCWD), China Lake, conducted a series of simulated uncontained engine failure structural impact tests. A large gas gun was used to launch turbine engine fan blade segments into an aircraft fuselage. The impacts were documented and analyzed with high-speed photography. Impact velocities, presented areas, and residual velocities were calculated. The data were then compared to analytic results predicted by the Joint Technical Coordinating Group for Munitions Effectiveness (JTCG/ME) penetration equations. These equations were originally develop to predict the penetration and residual velocity of ballistic weapon projectiles upon impact with various vehicles. The ballistic prediction equations developed for warhead fragments are the closest in geometric shape to turbine engine blade fragments. The data comparison shows good agreement for the predicted and experimental residual velocities.
• Format:
  PDF
• Download URL:
  https://rosap.ntl.bts.gov/view/dot/94014/dot_94014_DS1.pdf
• File Type:
  [PDF - 2.59 MB]
• Collection(s):
  FAA William J. Hughes Technical Center for Advanced Aerospace
• Main Document Checksum:
  urn:sha-512:4a120ad7f35159b39ee9f76ac9cc440083e643ab5950eec0a749cb47a9763020c105541eca8dbf58646f29c0c44d46169b3a991d3c3d9c39c8f7d2e4d26314df