MIL-DTL-85097/1B(OS)
TABLE I. Propellant N-43 (AS 3550).
7-Year Equivalent
Temp
Property
Zero time
0% Rel. humidity
22% Rel. humidity
( F)
Min
Max
Min
Max
Min
Max
Sm (maximum stress) psi
77
157
256
157
269
157
276
Em (elongation at Sm) %
77
18
28
9
28
16
28
Ym (Young's modulus) psi
77
1014
1946
1014
3094
1014
3114
Br (strand burn rate at 1000 psi) in/sec
77
0.60
0.67
0.60
0.71
0.60
0.71
TABLE II. Propellant N-44 (AS 3554).
7-Year Equivalent
Temp
Property
Zero time
0% Rel. humidity
22% Rel. humidity
( F)
Min
Max
Min
Max
Min
Max
Sm (maximum stress) psi
77
116
193
116
202
116
208
Em (elongation at Sm) %
77
30
50
14
50
26
50
Ym (Young's modulus) psi
77
589
1093
589
1737
589
1745
Br (strand burn rate at 1000 psi) in/sec
77
0.55
0.67
0.60
0.71
0.60
0.71
3.3 First article/production.
3.3.1 Propellant. The propellant shall conform to the requirements of AS 3550 and AS 3554 for the
following parameters at -65, 70, and 160 F: heat of explosion, burning rate, and physical properties (see 6.2
and 6.3).
3.3.2 Ballistic performance. The rocket catapult shall meet the requirements of table III when test-fired
using an ejected weight of 315 pounds at 160 F and 410 pounds at -40 and 70 F.
3.3.2.1 Output cartridge pressure. The head end output cartridge shall produce pressure values as
specified in table III, when fired in a test chamber conforming to Drawing 736AS190, using test setup
assembly and adapter in accordance with Drawings 736AS191 and 736AS192, respectively. The head end
output cartridge shall reach maximum pressure within 10 milliseconds of rocket motor ignition as defined in
MIL-DTL-85097.
3.3.2.2 Acceleration. During the first 0.015 second after initiation, any initial pulse shall not exceed 19 g's
or exceed 5 g's for more than 0.010 second.
3.3.3 Rocket motor marking. The rocket motor serial number shall be stamped in black ink on the outer
diameter of the rocket motor housing.
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