TARE &.2--NOGMALICED FISSION-PRUDLCT GAMMA-2Y
EXERCY VERSUS RANGE IN AIR
Range (gw a®)
ee
0
10
£0
40
éo
LA-1820
1.oo
0.046
0.657
0.361
0.160
Adjusted
1.00
0.845
0.656
0.354
0.200
ee
100
120
140
160
180
La-1620
0.0575
0.0225
0.0099
k.2@s10°3
1.b8xta74
Adjusted
0.073
0.0551
0.0251
"9.0126
6. 33x10
Range [gma/ ca)
a
Since a point-source geumetry is used, geometrical Viet divergence of
energy mist be inserted.
The distance between the source amd the instrument
carriers can be found as a fiction of time.
was used for Teak a
photographic datz.
A Cloud-rise rat
or Orange, as determined from prelininary
The rocket trajectory is accurately known for most instru-
ments flown by Sandia (see Chapter -9).:
Results preseoted below are based on calculations which proceeded as follows.
First, the spatial distribution of gacma-ray intensity at zero time was
found from Table 4.2,
The tine dependence of the spherical spreading term was then found by
computing the tise-dependent distance between the rocket and rhe fissionproduct debris as explained above.
This distance was then converted into aa
appropriate number or ga/oné of air by using the ARDC aodel atoosphere.*
‘Ibe
assuaption that the inbomogereous atmosphere can be treated in this way is inplicit bere and is legitimate according to Monte Carlo calculations done by
Marcu!
Finally, the cize decay of the intensity of the source was treated
according to Fig. 5.2 of LA-1&20.
(OC