Maximum performance aviation instrument for engine failure operation of aircraft
OwnerWilliam E. Lawsoninventor
Life of this patent
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Abstract
A maximum performance instrument for an aircraft is configured to aid a pilot in taking corrective action, after loss of functionality of one of the aircraft engines, in order to maintain as much control of the aircraft as possible. The information is provided to the pilot on a single instrument display in a format that is familiar to most pilots so that the information is immediately usable by the pilot without a high degree of proficiency or training with the instrument.
Claims20
An aviation instrument for use by a pilot of an aircraft in the event of loss or reduction of functionality of an engine of the aircraft, the aviation instrument comprising:
- a display device;
- and
- processing circuitry coupled to the display device and configured to control the display device to display a performance indication graphic which indicates to the pilot corrective action needed to control the aircraft to counteract adverse yaw motion caused by the event of loss or reduction of functionality of the engine of the aircraft.
An aviation instrument for use by a pilot of an aircraft in the event of loss or reduction of functionality of an engine of the aircraft, the aircraft including a rudder controlled by left and right rudder pedals, the aircraft also including flaps controlled by a flap control device, the aviation instrument comprising:
- a display device;
- and
- processing circuitry coupled to the display device and configured to control the display device to display a performance indication graphic which indicates to the pilot corrective action needed to control the aircraft to counteract adverse yaw motion of the aircraft caused by the event of the loss or reduction of functionality of the engine, the corrective action indicated by the performance indication graphic including an indication of which of the left and right rudder pedals should be deflected to deflect the rudder and thereby counteract the adverse yaw motion of the aircraft, wherein the processing circuitry is further configured to control the display device to indicate to the pilot of the aircraft an optimum angle of attack for the aircraft, responsive to the event of loss or reduction of functionality of the engine of the aircraft.
Dependencies are inferred from the claim text.