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In addition to aircraft attitude depicted with pitch bars and roll markers, the microEFIS has slip/skid ball and turn coordinator. The GPS option adds the display of stabilized heading, which backs up the directional gyro (DG) or HSI. Stabilized heading is slaved to GPS ground track. In a turn, the heading display updates at the actual turn rate as determined by the gyro module, and reverts to GPS track when the turn stops.
The lower portion of the iPAQ's screen displays GPS data including, ground speed, ground track, track error, bearing to waypoint, distance to waypoint, time to waypoint, waypoint ID, and a CDI with one mile full scale. Any panel mounted GPS with a serial output or portable GPS with a NMEA output can drive the GPS portion of the display.
In the event of an electrical system failure or vacuum failure, the microEFIS allows the pilot to maintain full control of the aircraft while also providing GPS guidance to a waypoint. Since the iPAQ and AHRS run on their own batteries, the microEFIS is completely independent of any aircraft system. And, if fed from a battery powered GPS, the entire system provides attitude, heading, and navigation data without dependence upon any aircraft system.
The iPAQ is typically mounted on the yoke or panel in full view of the pilot. Since crucial GPS information is also displayed, there is no need to also have a portable GPS also located on the yoke. .
The microEFIS is designed as a backup attitude indicator for certified aircraft and experimental aircraft. Since all of the components are fully portable (including the AHRS gyro module), no approvals are required.
Another application of the microEFIS is in VFR-only aircraft as an emergency attitude indicator if IFR conditions are inadvertently encountered. The microEFIS would enable the pilot to keep the aircraft under control until VFR conditions are reached.
The microEFIS is not designed to be a primary attitude indicator for any aircraft. In experimental aircraft that are flown in IFR conditions, a functional, certified, gyroscopic attitude indicator must be installed in the aircraft.
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