The inertial navigation system provides
information similar to that supplied by a doppler system, and it also gives
readings of latitude and longitude when desired. The inertial system utilizes
extremely sensitive gyros and accelerometers to develop signals from which
navigation information is computed.
The heart of the Collins INS-61 inertial
system is the inertial sensor unit (ISU) which contains the
inertial measurement unit (IMU), the system
power supply, and the battery charger. The IMU is manufactured by the Kearfott
Systems Division of Singer- General Precision, Incorporated.
This unit contains a stabilized platform on
which are mounted two 2 degrees-of-freedom gyros, a two axis accelerometer, and
401 a single-axis accelerometer. The stable platform is isolated from angular
motions in the aircraft by a shock-mounted gimbal system providing isolation
from aircraft vibration.
The IMU is contained within a fixed outer
frame which serves to mount the platform, the IMU connectors, and the
electronics for instrument compensation and electrical adjustments.
Aircraft pitch, roll, and heading data is
provided by synchros mounted on the platform-gimbal axis. The gyros in the IMU
sense pitch, roll, and yaw and produce signals which are converted to usable
information by the computer.
Acceleration in any direction is sensed by
the accelerometers, and this information is also employed by the computer to
provide navigation information. The information developed by the computer is
displayed on the control/ display panel.
The following information is available:
track angle and ground speed, true heading and drift angle, crosstrack distance
and trackangle error, present position in latitude and longitude, latitude and
longitude of any of the nine way points stored in the system, wind speed and
direction, distance and time to the next way point, desired track, from or to a
way point, way-point alert, system-failure warning, battery mode of operation
annunciation, and attitude reference-mode annunciation.
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