While you read this section, refer to figure
8-24. As the aircraft accelerates in the sensitive
vertical direction, the suspended armature tends
to remain behind due to its inertia. This reaction
varies the reluctance of the magnetic circuit set
up by the E pickoff windings and armature (view
B). The armature completes the magnetic circuit
through a small air gap. The relative motion
between the armature and E pickoff varies the
reluctance through the signal output windings.
This variation results in a signal that is
proportional to acceleration. When operating, the
output voltage is either in phase or 180 degrees
out of phase with the excitation, depending on
the direction of acceleration.
COORDINATION INPUT. --In some air-
craft, a dynamic vertical sensor detects lateral
accelerations (slip or skid) of the aircraft. The
sensor supplies a signal to position the rudder to
correct the slip or skid, coordinating the turn.
The signal is proportional to the amount of the
aircraft deviation from the vertical axis of the
aircraft. In other aircraft, a horizontally mounted
accelerometer aligned with the lateral axis of the
aircraft provides the same information. Only
the dynamic vertical sensor is covered in this
TRAMAN.
The dynamic vertical sensor consists of a
viscous-damped pendulum mechanically con-
nected to the rotor shaft of a transmitter synchro.
The cutaway view of the sensor (fig. 8-25) shows
the mechanism assembly, which includes a
synchro transmitter with a pendulum and vane
assembly attached to the rotor. The vane moves
in an oil-filled chamber. The damping effect of
Figure 8-24.-Accelerometer transmitter.
Figure 8-25.-Cutaway view of a dynamic vertical sensor.
8-21