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


Full Text : http://www.dtic.mil/get-tr-doc/pdf?AD=ADA193828


Report Date : Apr 1987


Pagination or Media Count : 215


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