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|  MIL-C-38418E(AS)
4.6.7 Power Consumption - The control assembly shall give specified
performance from a category B power source as defined in MIL-STD-704.
The power required at nominal voltage and frequency shall not exceed the
following values, exclusive of power supplied from the control assembly
to operate associated external equipment.
a.
ac power (three phase) 115/200V, 400 Hz.
75W, starting; 50W, running.
(1)
Displacement gyroscope:
control
(2)
electronic
ASK-321A24G-39 or
ASK-44/A24G
amplifier and the compass system controller: 50W.
b.
ac/dc power: 5V
(1)
5.OW.
Compass system controller lighting:
4.6.8 Vibration Error - The control assembly shall be operated in the
SLAVED mode, synchronized to the simulated azimuth detector, and
subjected to a vibration error test .
During this test, the input
vibration to the control assembly shall coincide with a power spectral
2
density of 0.015 g /Hz for each frequency from 20 to 2,000 Hz. TO
accomplish this representation, the loading effect of the component under
This random
test shall be eliminated by proper load compensation.
vibration shall be applied to the component along the three mutually
perpendicular axes of the component. The signal source shall be either a
prepared magnetic tape or a noise generator. To properly observe errors,
the duration shall be from 10 to 15 minutes.
The control assembly
outputs of pitch, roll, and heading shall not vary by more than 3/4
from the initial position established with 10 percent of this vibration
level, and shall return to the initial position when the vibration is
again reduced to 10 percent of the test vibration level.
4.6.8.1 DG Mode - The control assembly shall be operated in the DG mode
and subjected to the vibration error test. During this test, the input
vibration to the control assembly shall coincide with a power spectral
density of 0.002g2/Hz for each frequency from 20 to 2,000 Hz. TO
accomplish this representation, the loading effect of the components
under test shall be eliminated by proper load compensation. The random.
vibration shall be applied to the component along the three mutually
perpendicular axes of each component. The signal source shall be either
a prepared magnetic tape or a noise generator. The duration of the test
shall be 15 minutes.
The control assembly heading change shall not
exceed 1/20 when corrected for the earth's rotation.
77
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