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Title:
OPERATION UPSHOT-KNOTHOLE, BLAST EFFECTS ON B-36 TYPE AIRCRAFT IN FLIGHT, PROJECT 5.3 ( MARCH - JUNE 1953 )
Author(s):
Subject Terms:
BLAST EFFECTS; AIRCRAFT; IVY OPERATION; MIKE EVENT; KING EVENT; UPSHOT OPERATION; HARRY EVENT; DIAGRAMS; PHOTOGRAPHS; GRAPHS; DATA; COMPARATIVE EVALUATIONS; UPSHOT-KNOTHOLE OPERATION
Document Location:
Location - NNSA/NSO Nuclear Testing Archive Address - P.O. Box 98521 City - Las Vegas State - NV Zip - 89193-8521 Phone - (702)794-5106 Fax - (702)862-4240 Email - CIC@NV.DOE.GOV
Document Type:
REPORT
Publication Date:
1953 Jun 30
Declassification Status:
Declassified
Document Pages:
0104
Accession Number:
NV0051104
Document Number(s):
WT750
Originating Research Org.:
ARMED FORCES SPECIAL WEAPONS PROJECT
OpenNet Entry Date:
1994 Aug 26
Description/Abstract:
THIS REPORT IS A PRESENTATION OF THE DATA OBTAINED BY PROJECT 5.3 ON T HE BLAST RESPONSE OF A B-36D AIRCRAFT FLOWN IN THE PROXIMITY OF THE SH OT 9 EXPLOSION OF OPERATION UPSHOT-KNOTHOLE. THE TEST AIRCRAFT WAS THE SAME B-36D AIRCRAFT UTILIZED FOR SIMILAR TESTING BY PROJECT 6.10 DURI NG OPERATION IVY. THE INSTRUMENTATION WAS MODIFIED TO INCLUDE ADDITION AL MEASUREMENTS ON THE HORIZONTAL TAIL. RESPONSE MEASUREMENTS INCLUDED : NOSE, TAIL, WING TIP, AND CENTER OF GRAVITY ACCELERATIONS; WING FUSE LAGE, AND HORIZONTAL STABILIZER BENDING MOMENTS; AND HORIZONTAL STABIL IZER SHEAR. PEAK OVERPRESSURE AT THE AIRCRAFT WAS ALSO MEASURED. THE P URPOSE OF THE PROGRAM WAS TO SUPPLEMENT THE BLAST RESPONSE DATA OBTAIN ED DURING THE IVY TESTS PARTICULARLY TO INVESTIGATE MORE FULLY THE AFT FUSELAGE AND HORIZONTAL STABILIZER RESPONSE CHARACTERISTICS. THE PURP OSE WAS ACCOMPLISHED EVEN THOUGH THE PEAK LOADS OBTAINED WERE NOT AS H IGH AS DESIRED. THE PEAK STABILIZER BENDING MOMENT MEASURED WAS 34 PER CENT OF LIMIT LOAD. PEAK WING BENDING MOMENTS WERE SOMEWHAT HIGHER TH AN THOSE MEASURED DURING IVY BUT WERE STILL ONLY A FRACTION OF THE LIM IT ALLOWABLE. THE DATA OBTAINED BY PROJECT 5.3, COMBINED WITH PREVIOUS DATA, WILL ALLOW A COMPLETE CHECK OF THE PRESENT BLAST/LOAD THEORY IN THE LOW AND MEDIUM LOAD RANGES. THEORETICAL EXTRAPOLATION TO LOADS AP PROACHING DESIGN LIMIT SHOULD BE CONFIRMED BY ADDITIONAL EXPERIMENTAL DATA. THE POSITION OF THE AIRCRAFT AT BLAST ARRIVAL WAS SUCH THAT THE REFLECTED SHOCK WAVE ARRIVED 4.44 SECONDS AFTER THE DIRECT SHOCK WAVE; AND, BECAUSE OF FORTUITOUS PHASING WITH LOW AMPLITUDE VIBRATIONS INIT IATED BY THE DIRECT SHOCK, THE PEAK LOADS PRODUCED BY THE REFLECTED SH OCK WERE SLIGHTLY HIGHER. HOWEVER, WITH PROPER PHASING AND SHORTER TIM E INTERVAL BETWEEN SHOCKS, THE REFLECTED SHOCK COULD INDUCE PEAK LOADS CONSIDERABLY HIGHER THAN THOSE OBTAINED FROM THE DIRECT SHOCK. THE DA TA OBTAINED BY PROJECT 6.10 IN IVY ARE INCLUDED IN THIS REPORT.


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