MIL-DTL-82945B (OS)
TABLE I. Ballistic performance requirements for a 347-pound ejected weight.
-65F
70F
165F
AQL
Parameter
Min
Max
Min
Max
Min
Max
Catapult
--
Initiation pressure, (psi)
350
550
350
550
350
550
Dynamic response index, (DRI)1/
--
--
--
18.0
18.0
22.0
0.65
Separation velocity, (ft/s)2/
--
--
--
33
33
33
0.65
--
--
--
Ignition delay, (ms)
10
10
10
0.65
--
--
--
Axial thrust (lbf)
7000
7000
7000
1.0
--
--
--
Launch time (ms)
260
260
260
1.0
Rocket Motor
--
--
--
Resultant impulse, (lbf/sec)
960
960
960
1.0
--
--
--
Ignition delay, (ms)
30
30
30
1.0
Action time, (ms)3/
--
--
--
535
535
535
1.0
--
--
--
Resultant thrust, (lbf)
5000
5000
5000
0.65
Thrust angle (reference)*
47.5
47.5
47.5
--
CKU-10/A
--
54.5
54.5
54.5
CKU-11/A
1/ DRI is defined in section 3.4.1.1.7.
2/ Nominal separation velocities are: 37.0 ft/s at -65F and 46.0 ft/s at 165F.
3/ Nominal rocket motor action time is: 470 ms at -65F and 340 ms at 165F.
* Record for information only.
3.4.1.2 Other requirements. In addition to meeting the ballistic requirements, none of the following
shall occur during test firing of rocket catapults:
a.
No unit component, including but not limited to catapult components, O-rings, springs, or
pieces of propellant shall be ejected.
b.
No component subject to loading shall fail.
c.
No excessive nozzle erosion, hot spots, or burnthrough shall occur.
d.
No leakage of ballistic gas past a sealing surface shall occur.
e.
The thrust-time curve shall exhibit a shape that compares well with the established (or
representative) curve for the unit.
3.4.2 Initiation. Maximum allowed initiation pressure input is 10,000 psi. The rate of pressurization
input shall be 30,000 to 50,000 psi/sec.
8
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