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Project 5,2 - In-Flight Participation of a B-52 ~ Ist Lt, F. L, Williams
OBJECTIVE
The objective of this test was to determine the delivery capability
of the B-52 aircraft.
INSTRUMENTATION
Instrumentation of the B-52 for this shet consisted of 312 oscillograph channels which recorded measurements from strain-gage bridges,
accelerometers, roll and pitch gyros, radiometers, pressure transducers,
calorimeters, thermocouples, and control position transducers,
In addition,
13 cameras recorded photorecorder instruments (14 channels), wing and tail
deflection, cloud coverage, and fireball rise and growth,
AIRCRAFT POSITION IN SPACE
The following chart shows the airplane's position at zero time and
time of shock arrival:
Altitude
Offset
Heading
£1000
1900
106
£8800
762
757
Shock Arrival 41000
2750
105
©1000
752
7L7
Condition at
Time Zero
Condition at
(abs, ft)
(ft)
(true-dez)
Slant
Distance (ft)
Velocity (fps)
TAS
Ground
RESULTS
Thermal Energy:
57.7 BTU/ft? (14.9 cal/om2) measured at BS 655 by a
160° field calorimeter pointed straight down,
Maximum Temperature:
panel:
144°F measured at ES 230, lower surface.
absorptivity = 0,54)
Gust:
54% wing bending at LHWS 444
28% tail bending at LHSS 300
CUriED/GOE
Peper
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