Chapter 17, Inertial Navigation Systems Flashcards
What output is produced from an
accelerometer after the first integration
process?
Velocity
If the applied force on an accelerometer is
maintained, the mass
Returns to the neutral position
During the ‘align’ mode, local vertical is
sensed by
Accelerometers
Establishing the orientation of true north is achieved by sensing
The earth’s rotation
Inertial navigation system errors are a factor
of
How long the system has been in the ‘navigation’ mode
Align mode is selected by the crew on the
Mode select unit
During flight, with zero output from the
accelerometers, the aircraft’s ground speed
and distance travelled are
Constant ground speed, increasing distance
travelled
Magnetic north can be derived by an inertial
reference system through
Knowledge of the present position and local magnetic variation
Once aligned, the inertial navigation computer
is always referenced to
True north
Errors in an inertial navigation system are
Random and build up as a function of time
Magnetic variation depends on
Where the observer is on the earth’s surface
Alignment of the inertial navigation system is
possible
Only when the aircraft is on the ground and
stationary
In ‘attitude’ mode, the inertial navigation
system provides
Pitch and roll information
The angle between the actual track and
desired track is called
Track angle error
During the alignment mode, a flashing align
light indicates
The aircraft was moved during align mode
