MIL-DTL-48568D(OS)
4.3.1 Environmental tests.
4.3.1.1 High temperature. The rocket catapult assembly shall be subjected to the high-temperature storage
test in accordance with Method 501 of MIL-STD-810. The test items will be maintained at 165 F for 50
hours minimum. Operation of the rocket catapult shall be only as specified in table III.
4.3.1.2 Vibration. The rocket catapult assembly shall be subjected to random vibration for jet aircraft in
accordance with MIL-STD-2102 with the exception that the duration will be for 6 hours, with 2 hours on
each axis. Before vibration, units shall be temperature conditioned in accordance with table III for a minimum
of 8 hours. The input vibratory acceleration must have a Wo factor of 0.1 g2/Hz and the reduction factor must
be 0 g2/Hz-dB. If the rocket catapult must be removed from the environmental conditioning chamber or if the
temperature falls outside the specified temperature limits for more than 5 minutes, the testing will be stopped
and the unit reconditioned. A reconditioning time of 2 minutes for every minute outside the specified
temperature envelope is required. A continuous temperature history of the unit will be kept for all
conditioning and testing time. Unless otherwise noted, the rocket catapult must be mounted on a text fixture
in a manner that will simulate actual seat/aircraft installation and excited through the attachment fittings.
4.3.1.3 Temperature shock. The rocket catapult assembly will be subjected to the temperature shock test in
accordance with Method 503 of MIL-STD-810. The test temperature extremes will be 65 F and 165 F and
the duration of exposure at each temperature shall be 8 hours. Operation of the rocket catapult shall be only
as specified in table III.
4.3.1.4 Thirty-day storage. Three rocket catapults shall be placed in storage at 65 F and three at 165 F
for 30 days each. Ensure that the proper temperature is maintained throughout storage. Operation of the
rocket catapult shall be only as specified in table III.
4.3.2 Static firing test. Within 30 days after completion of environmental exposure the rocket catapults must
be static fired at the Indian Head Division, Naval Surface Warfare Center, Indian Head, MD 20640-5000.
The sample shall be temperature conditioned per table III for a minimum of 8 hours and test fired within 10
minutes after removal from the conditioning chamber to verify conformance to the requirements of 3.4. Data
specified in table I shall be analyzed in accordance with MIL-STD-414, Section B, Part I, using the
procedures of B-5 through B-7. Nonconformance with table I, or any requirement of 3.4.1.1, shall be cause
for rejection of the first article sample.
4.3.3 Propellant aging. Three blocks of cured propellant from each batch of propellant used in the first
article sample shall be submitted for aging testing to the Indian Head Division, Naval Surface Warfare
Center, Indian Head, MD 20640-5000, Attn: Code 5120. High-temperature aging shall be conducted for 84
days with an atmosphere of 22 percent relative humidity and at 165 ± 5 F. At zero time and at the end of the
28-, 56-, and 84-day aging, physical properties shall conform to MIL-P-82680, Class I. The rate for
stress/strain determination shall be 2.0 inches/minute. The sample shall be cast into rectangular cardboard
containers approximately 1.5 inches high by 8 inches wide by 11 inches long. All samples submitted shall be
bare propellant, individually wrapped in moistureproof packaging and properly identified as to propellant lot
and batch number. Failure of the propellant to meet the requirements of MIL-P-82860, Class I, shall be cause
for rejection of the propellant batch.
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