Effect of Aging Aircraft Structure on Magnesium Parts

reportActive / Technical Report | Accession Number: ADB814135 | Open PDF

Abstract:

Procedure for artificially aging assemblies and subassemblies to improve strength properties of wrought aluminum alloys in aircraft structures was developed. Aging treatment of ten hours at 375 deg F is applied to magnesium alloys. Magnesium alloys may be encountered in casting, extrusion, forging, and sheet forms. Alloys commonly used in aircraft structures in various forms and effect of aging treatment are discussed.

Author(s):
Winston, A. W.
Author Organization(s):
DOW CHEMICAL CO MIDLAND MI
Descriptive Note:
Technical note
Pagination:
0010

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
NACA-TN-979
Monitor Series:
TN-979, NACA
 Subject Terms
Communities of Interest:
Air Platforms
Descriptor(s):
*MAGNESIUM ALLOYS, AGING(MATERIALS), PARTS, AIRCRAFT, STRENGTH(MECHANICS)
Field(s)/Group(s):
Metallurgy and Metallography
Keyword(s):
ATI 7302, ATI COLLECTION
Report Date:
1945 Apr 01
Creation Date:
1999 May 19