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Page Title:
Synchronization Angle Modification |
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|  MIL-S-85018A(AS)
3.5.3.4.1.2.4 Normal Synchronization - the synchronizing angle shall be
incremented at the specified slaving rate in the direction that will reduce the
synchronizing error to zero in a minimum period of time.
3.5.3.4.1.2.4.1 Synchronization Angle Modification - The synchronization
angle shall be modified in the SLAVED mode to:
1. Correct for the apparent heading drift due to the
earth's rotation as determined by the latitude set on the system Controller by
reference to a voltage and polarity transmitted from the Controller.
2. Correct the mean directional gyro drift by reference to
a voltage and polarity transmitted from the Displacement Gyroscope.
3.
Provide slaving as specified herein.
3.5.3.4.1.2.4.2 Fast Synchronization - Circuitry shall be provided to cause
synchronization of the azimuth output at a fast rate when the system is
operating in the SLAVED mode and the SET HEADING switch on the controller is
depressed.
3.5.3.4.1.3 Heading Coupler Action in EMERGENCY Mode - When the EMERGENCY
mode is selected, the magnetic heading derived from the Transmitter/Detector
shall be insensitive to the magnetic field strength and shall be transmitted
directly to the heading synchro repeater electronics. The directional gyro
output heading resolver shall not be used in the EMERGENCY mode. The index,
one-cycle, and two-cycle error compensation shall remain in the magnetic heading
loop.
3.5.3.4.1.4 Heading Coupler Action in SLAVED Mode - In the SLAVED mode the
output heading shall be referenced to magnetic heading. True heading for
internal functions shall be derived by combining the output heading and the
magnetic variation.
3.5.3.4.2 Initialization Control - The Electronic Control Amplifier shall
automatically sequence erection in pitch and roll following the application of
power and upon a manual demand as specified herein. When the erection control
senses a null at the time specified herein, normal erection shall begin
automatically.
3.5.3.4.3 Outer Roll Servo Control - The Electronic Control Amplifier shall
control the outer roll vertical gyro gimbal.
3.5.3.4.4 Electronic Repeaters - The solid state synchro type data
repeaters in each of the three axes of the system shall contain no moving parts.
The repeaters shall not require any adjustment when transferred as an electronic
assembly.
3.5.3.4.5 Rate-of-Turn Function - The Electronic Control Amplifier shall
incorporate the necessary electronics to provide derived rate of heading to the
turn indicator.
3.5.3.4.6 Malfunction Monitor - BITE - The equipment shall include BITE
provisions for organizational level maintenance. BITE shall obviate the need
for any external test equipment for the performance of preflight, postflight, or
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