MIL-DTL-48568D(OS)
TABLE I. Ballistic performance requirements for a 459-pound ejected weight.
70 ± 2°F
-65 ± 2°F
165 ± 2°F
Max
Min
Min
Max
Min
Max
Parameter
Catapult
Initiation pressure, Pact (psi)
250
550
250
550
250
550
Rate of change of acceleration,
A (g/sec), see
300
300
300
6.3.5
Separation velocity 1/, CSv (ft/s), see 6.3.4
40
42
37
--
Ignition delay, Cld (ms), see 6.3.2
30
30
30
--
7000
Axial thrust, CFmax (lbf), see 6.3.11
7000
7300
210
200
200
Launch time, CLt (ms), see 6.3.3
--
18
18
Dynamic response index, DRI, see 6.3.10
22
--
Acceleration, A (g), (reference)3/
20
18
20
Rocket Motor
Resultant impulse, Rlr (lbf/see), see 6.3.9
1100
1100
1100
--
Ignition delay, Rld (ms), see 6.3.6
25
25
25
--
Action time, RAt (ms)2/, see 6.3.7
450
550
450
--
7350
7350
7600
Resultant thrust, RFmax (lbf), see 6.3.8
Thrust angle (reference)3/
40°
40°
40°
1/ Nominal separation velocities are: 39.0 ft/s at -65°F and 47.0 ft/s at 165°F.
2/ Nominal rocket motor action time is: 460 ms at -65°F and 330 ms at 165°F.
3/ Record for information only.
3.6 Residual magnetism. The rocket catapult assembly, when passed in front of an MS 17983 compass along
the entire length of the catapult (see figure 1) shall not cause the compass indicator to deflect more than 5
degrees in either direction. The test shall be performed in an area free from local magnetic effects.
5
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