Accession Number:

ADA193828

Title:

F-14 Wing Outer Panel Fatigue Test Spectrum.

Descriptive Note:

Final rept Jan-Oct 86,

Corporate Author:

NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA AIR VEHICLE AND CREW SYSTEMS TECHN OLOGY DIRECTORATE

Personal Author(s):

• Seidel, G. S., Jr.
• Koutsiouroubas, A.

Report Date:

1987-04-01

Pagination or Media Count:

215.0

Abstract:

A spectrum of loads for the F-14 Wing Outer Panel fatigue test has been derived, based on the spectrum used by Grumman for the Aircraft 98 test of the F-14A fuselage. Flight and ground load distributions on the wing have been developed corresponding to those in that test, and the Aircraft 98 spectrum was simplified where significant fuselage loading conditions would have negligible effect on the wing outer panel. In addition, requirements for sweeping the wing under load have been incorporated based on fleet operational data. Keywords Aircraft structure Fatigue test.

Descriptors:

• *SWEPTBACK WINGS
• *AIRCRAFT PANELS
• *FATIGUE(MECHANICS)
• AIRCRAFT
• EXTERNAL
• FATIGUE TESTS(MECHANICS)
• FUSELAGES
• GROUND LEVEL
• LOAD DISTRIBUTION
• PANELS
• WINGS
• JET FIGHTERS
• LOADS(FORCES)
• AERODYNAMIC LOADING
• SPECTRA

Subject Categories:

• Attack and Fighter Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE