Alloy Needs and Design: The Airframe

  • R. F. Simenz
  • M. A. Steinberg
Part of the Battelle Institute Materials Science Colloquia book series (volume 31)


Materials applications in aircraft are discussed, and design requirements for strength and fatigue resistance are examined to afford an insight as to the problems of selecting materials for structural applications. Examples of materials selection and application are discussed for a new generation/wide-body aircraft. The concepts of fail-safe and damagetolerant structures are reviewed.

Alloy needs for future aircraft are expected to continue to depend on aluminum, steel, and titanium for the principal components. However, in aluminum, new developments in alloy design are needed that achieve superior fatigue and strength properties combined with immunity to stress-corrosion cracking. Aluminum alloys with enhanced high-temperature strength and stability are also needed. In titanium, future alloys should have improved fabrication characteristics lo achieve lower cost structure and better metallurgical controls to provide more reliable fatigue and toughness properties. Future steel-alloy developments must provide more damage tolerant and more stress-corrosion resistant grades without compromising strength properties or fabrication characteristics.


Aluminum Alloy Fracture Toughness Titanium Alloy Fatigue Life Corrosion Fatigue 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.


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Copyright information

© Plenum Press, New York 1977

Authors and Affiliations

  • R. F. Simenz
    • 1
  • M. A. Steinberg
    • 2
  1. 1.Materials Engineering Science and Engineering DivisionLockheed California CompanyBurbankUSA
  2. 2.Lockheed Aircraft CorporationBurbankUSA

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