Titanium Development Program. Volume 5

Abstract

Typical airframe structures, fuselage frames, wing leading edge, bleed air ducts, tail cone, shear panels and compression panels of Ti-4Al-3Mo-1V and Ti-13V-11Cr-3Al were subjected to test loads in increasing increments of 100 degrees from room temperature to maximum temperatures of 800 F and 900 F, depending on the part. Riveted and resistance welded construction was evaluated in the fuselage frame and wing leading edge.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1961
Accession Number
ADA955944

Entities

People

  • D. H. Love
  • G. D. Lindeneau
  • G. F. Foelsch
  • H. A. Buehler
  • J. K. Neary

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Air Platforms
  • Counter WMD
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Aircrafts
  • Airframes
  • Assembly
  • Engineers
  • Fabrication
  • Insensitive Explosives
  • Manufacturing
  • Manufacturing Engineering
  • Materials
  • Materials Laboratories
  • Mechanics
  • Plastic Explosives
  • Production Engineering
  • Tensile Strength
  • Test And Evaluation

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Metallurgy
  • Structural Health Monitoring of Composite Structures.