MIL-DTL-85097/1B(OS)
4.1.1.1.1.1 Resonance survey. Resonance surveys shall be conducted on both rocket catapults in three axes
at the maximum and minimum conditioning temperatures. Input vibratory acceleration of 5 g's shall be
applied successively along each of the axes noted above when sweeping between 10 an 499 hertz. Input
vibratory acceleration of 3 g's shall be applied for sweeps between 500 and 2,000 hertz. All resonances shall
be as noted. During the resonance survey a permanent, continuous record of input vibratory acceleration and
of unit response to the input vibratory acceleration shall be kept. This record shall be made on an instrument
acceptable to the Government and shall include the response along each of the three axes. Frequency shall be
varied at a rate not greater than 0.25 octave per minute.
a.
A resonance shall be defined as a frequency at which a clearly defined peak in the amplitude ratio
(ratio of the output acceleration in any of the three igniter cartridge axes to the input acceleration
as measured at the excitation attachment points) exceeds a value of 1.5 to 1.
b.
If the resonance survey indicates a frequency band wherein the amplitude ratio exceeds 1.5 to 1
(as contrasted to a clearly defined peak) this entire band width shall be considered one resonant
point. The minimum frequency band width which shall be considered a resonant band shall be
0.33 octave. If, also within this band width, there are clearly defined amplitude peaks, the most
severe of these shall be considered an additional resonant point.
4.1.1.1.1.2 Endurance vibration. One rocket catapult shall be conditioned to 40 ± 5 F and one to 160 ±
5 F. Each rocket catapult shall be vibrated for 24 hours, 8 hours in each of the three axes. The vibration
time in each axis shall be equally divided between the resonant frequencies noted in that axis during the
resonant survey. A peak input acceleration of 5 g's shall be maintained at frequencies between 10 and 499
hertz and 3 g's for frequencies between 500 and 2,000 hertz. If no resonant frequency is detected in an axis,
the rocket catapult shall be vibrated in that axis for a minimum of 2 hours at 5 g's input through the 10 to
499 hertz range and 6 hours at 3 g's input through the 500 to 2,000 hertz range. Total vibration time for the
rocket catapults shall be 24 hours which shall include resonant and nonresonant frequencies, as applicable.
At the conclusion of the tests, the rocket catapults shall be visually and radiographically inspected for damage
without disassembly of the rocket catapult. The rocket catapults shall be fired at the same temperatures they
were conditioned and vibrated.
4.2 Preproduction/production.
4.2.1 Conditioning temperatures. The conditioning temperatures and tolerances shall be as follows:
a. Cold: 40 ± 5 F
b. Hot: 160 ± 5 F
4.2.2 Conditioning period. Time for conditioning prior to static firing or during temperature cycling shall
be as follows:
a. Static firing: not less than 6 hours.
b. Temperature cycling: not less than 6 hours.
5. PACKAGING
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