Accession Number:

ADA061759

Title:

Stress Corrosion Testing of AU4SG Aluminum Alloy in Plate Form.

Descriptive Note:

Technical rept.,

Corporate Author:

ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)

Personal Author(s):

Report Date:

1978-05-01

Pagination or Media Count:

25.0

Abstract:

The resistance to stress corrosion cracking in the short transverse direction of the 2014 type plate aluminum alloy AU4SG was assessed when aged to peak strength at either 160 C or 175 C, and when overaged. Stress corrosion tests were done in accelerated and natural environments using constant strain and constant strain rate techniques. All of the tests demonstrated that AU4SG aged to peak strength was very susceptible, stress corrosion cracks occurring in the alloy stressed at less than 30 MPa. Overageing to the extent that a 10 loss in 0.2 proof stress resulted, slightly improved the alloys resistance. Stretching the alloy after solution treatment accelerated the subsequent ageing process. No advantage was detected in the use of 160 C rather than 175 C for the ageing treatment. 2014 type alloy produced to DTD 5020A appeared to be slightly more resistant to stress corrosion cracking than the overaged AU4SG tested. Author

Subject Categories:

  • Properties of Metals and Alloys
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE