CRASHWORTHINESS OF AIRCRAFT FUSELAGE STRUCTURES

A combined analytical and experimental program was undertaken to study the dynamic structural response of aluminum model aircraft fuselage structures (nominally 36 inches diameter by 91 inches long). A drop-test gantry was used to provide a simulation of the wheels-up landing condition for both level and oblique angle impacts on a concrete pad for a range of wing loads and vertical descent velocities. Dynamic measurements of strain and g loads at discrete locations were obtained together with high speed photographs of the failure modes for comparison with a lumped mass-stiffness model of the structure using a finite element approximation.

Media Info

  • Features: References;
  • Pagination: p. 101-109

Subject/Index Terms

Filing Info

  • Accession Number: 00196064
  • Record Type: Publication
  • Source Agency: Engineering Index
  • Files: TRIS
  • Created Date: Aug 15 1979 12:00AM