Compressive-Strength Comparisons of Panels Having Aluminum-Alloy Sheet and Stiffeners with Panels Having Magnesium-Alloy Sheet and Aluminum-Alloy Stiffeners

reportActive / Technical Report | Accession Number: ADA801132 | Open PDF

Abstract:

Comparisons are made of 24S-T aluminum-alloy flat compression panels having longitudinal Z-section stiffeners, and panels having flat FS-1H magnesium-alloy sheet and longitudinal 24S-T aluminum-alloy Z-section stiffeners. It is shown that composite magnesium-alloy panels have higher structural efficiencies and buckling loads if stiffeners are widely spaced. If stiffeners are closely spaced, or if panels have ideal proportions, structural efficiencies are nearly the same, except in a small range of loading conditions in which 24S-T aluminum-alloy panels have slightly higher structural efficiencies.

Author(s):
Dow, Norris F. ; Hickman, William A. ; Mccracken, Howard L.
Author Organization(s):
NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA
Descriptive Note:
Technical note
Pagination:
0039

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-1274
Monitor Series:
NACA
 Subject Terms
Modernization Areas:
Directed Energy
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*AIRCRAFT PANELS, *COMPRESSIVE STRENGTH, LOADS(FORCES), STIFFENING, MAGNESIUM ALLOYS, SHEETS, BUCKLING, STRUCTURAL PROPERTIES, ALUMINUM ALLOYS, EFFICIENCY
Keyword(s):
ATI 7510, ATI 16216, ATI COLLECTION
Report Date:
1947 Apr 01
Creation Date:
2010 Sep 22