Comparison of Stress Corrosion Cracking Properties of Several Aircraft Structural Alloys
Comparison of Stress Corrosion Cracking Properties of Several Aircraft Structural Alloys

Author: JT. Ryder

Publisher:

Published: 1978

Total Pages: 9

ISBN-13:

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Sustained load subcritical flaw growth characteristics of five alloys of interest to aircraft designers were investigated. The aluminum alloy (2024-T851) and steel alloy (18Ni-maraging) were studied in 3.5% sodium chloride solution and high humidity air environments while two of the titanium alloys, Ti-6Al-4V (recrystallized annealed) and Ti-6A1-6V-2Sn (solution-treated and overaged), were also investigated in these environments plus sump tank water. The Ti-6Al-4V (beta) alloy was tested in 3.5% sodium chloride solution. Wide differences between the alloys were noted not only in their cracking rates but also in their responses to similar loads and environments. Specimen thickness was found to have an important effect on stress corrosion susceptibility of the titanium alloys. Many coupons of specific titanium alloys had significant subsurface crack growth without visible surface growth. For these alloys, no precise threshold for stress corrosion cracking could be defined.

Aluminum-Lithium Alloys
Aluminum-Lithium Alloys

Author: R.J.H. Wanhill

Publisher: Elsevier Inc. Chapters

Published: 2013-09-20

Total Pages: 42

ISBN-13: 0128068531

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The material and manufacturing property requirements for selection and application of 3rd generation aluminium-lithium (Al–Li) alloys in aircraft and spacecraft are discussed. Modern structural concepts using Laser Beam Welding (LBW), Friction Stir Welding (FSW), SuperPlastic Forming (SPF) and selective reinforcement by Fibre Metal Laminates (FMLs) are also considered. Al–Li alloys have to compete with conventional aluminium alloys, Carbon Fibre Reinforced Plastics (CFRPs) and GLAss REinforced FMLs (GLARE), particularly for transport aircraft structures. Thus all these materials are compared before discussing their selection for aircraft. This is followed by a review of the aluminium alloy selection process for spacecraft. Actual and potential applications of 3rd generation Al–Li alloys are presented. For aircraft it is concluded that the competition between different material classes (aluminium alloys, CFRPs and FMLs) has reached a development stage where hybrid structures, using different types of materials, may become the rule rather than the exception. However, aluminium alloys are still the main contenders for spacecraft liquid propellant launchers.

STRESS CORROSION CRACKING IN AIRCRAFT STRUCTURAL MATERIALS.
STRESS CORROSION CRACKING IN AIRCRAFT STRUCTURAL MATERIALS.

Author:

Publisher:

Published: 1967

Total Pages: 248

ISBN-13:

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Contents: General theory of stress corrosion; Laboratory aspects of aluminium alloys; Some engineering aspects of stress corrosion cracking in high strength aluminium alloys; Engineering aspects of stress corrosion failure in martensitic steels; Stress corrosion cracking of high strength stainless steels; Stress corrosion of titanium alloys; Stress corrosion cracking of very strong low alloy and maraging steels: laboratory aspects; National surveys of work on stress corrosion cracking.