Document Details


Title:
OPERATION REDWING - PROJECT 5.4: IN-FLIGHT PARTICIPATION OF A B-57B (DELETED)
Author(s):
WELLS, H M [MARTIN COMPANY, THE]; ROHA, D M [MARTIN COMPANY, THE]; SALLIS, D V [MARTIN COMPANY, THE]; WARD, J V [MARTIN COMPANY, THE]
Subject Terms:
BLAST EFFECTS; REDWING PROJECT; AIRCRAFT; THERMAL RADIATION; DAMAGE; SHOCK WAVES
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:
1960 Jul 28
Declassification Status:
Sanitized
Document Pages:
0062
Accession Number:
NV0051064
Document Number(s):
WT1330
Originating Research Org.:
MARTIN COMPANY, THE
OpenNet Entry Date:
1994 Aug 26
Description/Abstract:
PROJECT 5.4 WAS ESTABLISHED TO DETERMINE THE RESPONSE OF THE STRUCTURE OF THE B-57 AIRCRAFT IN FLIGHT TO THERMAL, GUST, AND OVERPRESSURE EFF ECTS OF LARGE-YIELD NUCLEAR EXPLOSIONS PRIMARILY FOR THE PURPOSE OF DE FINING THE DELIVERY CAPABILITIES OF THE AIRCRAFT AND SECONDARILY TO OB TAIN BASIC INFORMATION RELATIVE TO THE THERMOELASTIC RESPONSE OF THE A IRCRAFT STRUCTURE. IN ORDER TO OBTAIN THE DATA NECESSARY TO ACCOMPLIS H THIS OBJECTIVE, THE AIRCRAFT WAS INSTRUMENTED TO MEASURE THE OVERPRE SSURE, GUST, AND THERMAL INPUTS, AND THE RESPONSE OF VARIOUS COMPONENT S OF THE STRUCTURE TO THESE INPUTS. THE INSTRUMENTED AIRCRAFT WAS POS ITIONED AT PREDETERMINED POINTS IN SPACE IN THE VICINITY OF SEVERAL NU CLEAR DETONATIONS. THE POSITIONS WERE SELECTED SUCH THAT DESIGN LIMIT S WOULD BE APPROACHED. A MAXIMUM SKIN TEMPERATURE OF 400 F WAS THE CR ITERION FOR DETERMINATION OF THE AMOUNT OF THERMAL RADIATION WHICH THE B-57B COULD ABSORB WITHOUT SUSTAINING PERMANENT BUCKLING OF THE SKIN, AND 600F WAS THE CRITERION FOR THE MAXIMUM SAFE LIMIT. IN THERMALLY CRITICAL PARTICIPATIONS, THE AIRCRAFT WAS NORMALLY POSITIONED FOR THE 400-DEGREES LIMIT FOR THE DESIGN YIELD AND FOR LESS THAN 600 DEGREES F OR THE POSITIONING YIELD. WITH RESPECT TO GUST, THE AIRCRAFT WAS LIMI TED BY 100 PERCENT OF THE DESIGN LIMIT SHEAR AT WING STATION 123. THE AIRCRAFT EXPERIENCED LOADS OF FROM 14 TO APPROXIMATELY 61 PERCENT OF THE DESIGN LIMIT LOAD. DURING SHOT APACHE, THE AIRCRAFT WAS POSITIONE D FOR BOTH OVERPRESSURE AND A HIGH HORIZONTAL GUST COMPONENT. THE RES ULTS SUBSTANTIATED THE THEORETICAL ALLEVIATING EFFECT OF THE HORIZONTA L GUST COMPONENT. BLAST OVERPRESSURES OF 53 PERCENT OF THE OVERPRESSU RE LIMIT WERE RECEIVED. SUFFICIENT DATA WERE OBTAINED FOR THE DETERMI NATION OF THE DELIVERY CAPABILITY OF THE B-57B AIRCRAFT: IT WAS FOUND TO BE BETTER THAN THE CAPABILITY DESCRIBED IN THE B-57B PHASE I-A SPEC IAL WEAPONS STUDIES.


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