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system radar, aerial mapping camera photographs, calculations using time
of shock arrival, and from optical ground tracking data.
position was essentially thet intended.
The actual
The measured overpressure of
0.15 psi agrees reasonably well with the calculated value of 0.165 psi.
5.3
RESPONSE MEASUREMENTS
The blast response measurements made om the B~36 aircraft during
Shot 9 are presented in the sub-paragraphs following. Measurements on
the tail were made according to two instrummtation procedures arbitrar-
ily defined as the point load method and the conventional or distributed
load method, The response data obtained by the two methods were in good
agreement. In the plotting of the data as tine-histories, the time axis
has been broken such that the *irst and setond shock appear one above
the other for ease of comparison. Zero time was taken as time of shock
arrival as in the Mike and King presentations.
5.3.1
Sending Moment
Curves of incremental bending moment above "one ge" flight loads
as measured by the conventional method are reported in Figs. 5.1 through
5.7.
The stabilizer bending moments measered by the point load method
are presented in Figs. 5.8, 5.9, and 5.10, The left wing bending mombnt
at Station 390 has ceen reported, Fig. 5.2, although it is believed this
value is in error. The reasons for suspetting this measurement are set
forth in the Discussion.
data considered valid.
Except for the above, all bending gages yielded
Point load tending data were in general agree-
ment with conventionally measured values.
5.3.2
Acceleration
Tail, nose, and center of gravity normal accelerstion data are
presented in Figs. 5,11, 5.12, and 5.13, mespectively,
ations measurements were not made,
rerorted as read from the records.
3.3.3
Wing tip acceler-
Sharp spikes were not averaged, but
Shear
Shear was measured on the horizontal stabilizer by the point
road method. From a cursory comparison, tie shezr data are in agreement
with what would be expected on the basis «ff tending measurements. The
shear data are presented in Figs. 5.14 through 5.16,
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