Aeronautics and astronautics – Aircraft control – Automatic
Patent
1992-02-03
1997-01-07
Kashnikow, Andres
Aeronautics and astronautics
Aircraft control
Automatic
244185, 244 87, G05D 108, G05D 110, B64C 900
Patent
active
055908535
ABSTRACT:
An aircraft control system for computing a yaw compensated angle of attack is disclosed. The system includes an angle of attack sensor for generating a signal which represents an aircraft's angle of attack as determined by an angle of attack vane and a transverse accelerometer for generating a signal in response to the lateral acceleration of the aircraft. A summing device sums the two signals to thereby provide a yaw compensated angle of attack signal. The system may also include a rudder deflection sensor for generating a signal which represents the deflection of an aircraft's rudder. The rudder deflection signal is then subtracted from the yaw compensated angle of attack in the summing device. A stall warning system incorporating the yaw compensation system includes a stall warning computer for comparing the yaw compensated angle of attack signal to a predetermined value. The stall warning computer then triggers a stall warning device when the yaw compensated angle of attack signal exceeds the predetermined value.
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Dougherty David E.
Kashnikow Andres
Mejica Lissi
Safe Flight Instrument Corporation
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