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Page Title:
Heading Coupler Action in DG Mode |
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|  MIL-S-85018A(AS)
Pitch, Roll and Heading outputs
100
Monitoring and BITE
110
120
System Power Supplies
13.
System Interface circuits
14.
Switching and Test Logic
3.5.3.4.1 Heading Coupler - The Electronic Control Amplifier shall provide
a heading synchronizing angle to the Displacement Gyroscope assembly. This
angle shall be modified as required by the selected heading modes. The drive
capability of the signal shall be sufficient to transmit to the Displacement
Gyroscope assembly.
3.5.3.4.1.1 Heading Coupler Action in DG Mode - When the DG mode is
sellected on the system Controller, the synchronization angle will be modified:
(a) as commanded by the SET HEADING control on the SOARS
Controller
(b) to correct for the apparent heading drift due to the
earth's rotation at the latitude set on the Controller
by reference to a voltage and polarity transmitter from
the Controller
(c) to correct for mean directional gyro drift by reference to
a voltage and polarity transmitted from the Displacement
Gyroscope assembly.
3.5.3.4.1.2 Heading Coupler Action in SLAVED Mode - The heading coupler
shall provide magnetic slaving action when the SLAVED mode is selected on the
SOARS Controller.
3.5.3.4.1.2.1 Compass Transmitter or Detector Interface - The heading
coupler shall interface with the Compass Transmitter or Detector to obtain a
magnetic-heading-angle reference. The heading coupler shall provide filtering
of the sine and cosine of magnetic heading prior to determining synchronization
errors. The filtering break frequencies shall be selected to provide maximum
reduction of Compass Transmitter oscillation while causing minimum magnetic
heading damping. The magnetic heading shall be compensated for Coriolis
acceleration. The interface with the Compass Transmitter shall allow use of
conventional electrical compass-swinging equipment for compass calibration in
aircraft.
3.5.3.4.1.2.2 Compass Transmitter or Magnetic Azimuth Detector Excitation -
The Electronic Control amplifier shall supply 3.5 plus or minus .5 volt ac for
the Transmitter/Detector at nominal aircraft input line voltage.
3.5.3.4.1.2.3 Magnetic Synchronization Errors - The error between system
output heading and the magnetic reference shall be insensitive to the magnitude
of the earth's magnetic field. This error shall be used to obtain synchroniza-
tion between the system output heading and the reference magnetic-heading angle.
27
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