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Page Title:
Displacement Gyroscope Assembly |
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|  MIL-S-85018A(AS)
3.5.1.7.2 Plate of Turn Function - The Electronic Control Amplifier shall
incorporate the necessary electronics to provide derived rate of turn output to
a turn indicator.
The heading rate output shall be a direct current voltage
source proportional to the heading rate of change. When loaded with 500 ohms,
the voltage source shall provide 2 plus or minus .14 mA at 180 degrees per
minute to the load. The output shall be accurate within 7 percent or .070 mA,
whichever is larger from 0 to 225 degrees per minute. The output snail saturate
for a rate of 400 degrees per minute.
3.5.2 Displacement Gyroscope Assembly - The Displacement Gyroscope assembly
shall consist of hermetically sealed gyroscope subassemblies which in turn
consist of one or two vertical gyroscopes and directional gyroscope elements
mounted in a multiple gimbal set. The gimbal set shall incorporate a redundant
roll gimbal to avoid the gimbal-lock position. The Displacement Gyroscope
assembly shall be designed and constructed to meet the requirements of this
specification with suitable accelerometers. The arrangement shall permit
all-attitude operation and avoid any lock position at all times. No errors
exceeding 1 degree and lasting more than 5 seconds shall be developed as a
result of flight in the vertical climb and dive positions.The accelerometers
shall provide the accuracy specified by Figure 1. Gimbal outputs shall be
continuous through 360 degrees in azimuth, roll end pitch.
3.5.2.1 Function - The Displacement Gyroscope assembly provides a
stabilized vertical reference for pitch and roll, and a stabilized horizontal
reference for all headings in DG and SLAVED modes.
3.5.2.2 Weight - The weight of the Displacement Gyroscope assembly shall
not exceed 13.5 pounds.
3.5.2.3 Form Factor - The Displacement Gyroscope assembly shall have a
volume not exceeding 345 cubic inches. The external surfaces of this assembly
shall be painted color 17043, in accordance with FED-STD-595. The Displacement
Gyro form factor shall be in accordance with Figure 8.
3.5.2.4 Contents - The Displacement Gyroscope Assembly shall include
assemblies for the following functions:
3.5.2.4.1 Vertical Gyro - The vertical gyros shall be suspended in the
first vertical gyro gimbal. When so aligned, the spin axis of the vertical
gyroscopic element shall be aligned with the local gravitational vector. It
shall have sufficient angular momentum and shall be designed to meet the per-
formance specified herein.
3.5.2.4.2 Directional Gyroscope - The directional gyroscope shall have
sufficient angular momentum and shall be designed to meet the performance
specified herein. The directional gyroscope shall be suspended in a gimbal
system and stabilized by the inertia of the gyro action.
3.5.2.4.3 Vertical Gyro Erection - The vertical gyro erection mechanism
shall incorporate separate systems for pitch and roll. Erection shall be
accomplished by acceleration sensors and erection torquers. The erection
sensors shall be positioned and aligned on the gimbals in a manner that will
isolate their outputs from the pitch and roll displacements of the aircraft; in
part particular, the output of the roll erection sensor shall not be affected by
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