MIL-DTL-85097/1B(OS)
TABLE III. Ballistic performance requirements.
Parameter
-40 ± 5 F
70 ± 5 F
160 ± 5 F
Min
Max
Min
Max
Min
Max
Catapult ignition delay (ms)
0
5
0
5
0
5
2501
2501
3501
Onset (g/s)
-
-
-
191
191
201
Acceleration (g)
-
-
-
Separation velocity 2 (ft/s)
41
-
-
-
-
-
Rocket ignition time (ms)
0
25
0
25
0
20
3851
Rocket burn time (ms)
235
200
285
175
270
4251
Rocket action time (ms)
290
240
355
210
320
7,3001
Rocket motor resultant thrust (max)
3,165
4,935
3,700
5,800
4,750
1,0271
1,0271
1,0271
Rocket motor impulse (lb-s)
-
-
-
Output cartridge (psi max)
1,080
2,100
-
-
1,080
2,100
1
System requirements.
2
At end of catapult stoke measured over the interval from 31 to 43 inches travel.
4. QUALITY ASSURANCE PROVISIONS
4.1 Examination and tests.
4.1.1 Preproduction.
4.1.1.1 Environmental.
4.1.1.1.1 Vibration. For the AEPS covered by this specification sheet, the following test procedures shall
be used in lieu of those specified in the general specification. Two rocket catapults shall be subjected to
vibration testing. One rocket catapult shall be temperature conditioned for a minimum of 8 hours at
40 ± 5 F and the other at 160 ± 5 F. The rocket catapults shall be maintained at specified conditioning
temperatures during these tests. If the rocket catapult must be removed from the conditioning chamber or if
the rocket catapult temperature falls outside the specified temperature limits for more than 5 minutes, the
testing shall stop and the rocket catapult shall be reconditioned. A reconditioning time of 2 minutes for every
minute the rocket catapult spent outside the specified temperature envelope shall be required, up to a
maximum of 8 hours. A continuous temperature history of the rocket catapult shall be kept for all
conditioning and test time. Excitation shall be applied through the aircraft seat attachment fittings unless
otherwise noted in the contract. Accelerometers to measure acceleration along the axis perpendicular to the
longitudinal axis of the rocket catapult shall be placed midway between the attachment points. Longitudinal
vibration shall be measured at either end of the rocket catapult.
4
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