Investigation of a Stall Deterrent System Utilizing an Acoustic Stall Sensor 770473
A simple rugged acoustic stall sensor which has an output proportional to angle of attack near wing stall has been evaluated on a Cessna 319 aircraft. A sensor position has been found on the wing where the sensor output is only slightly affected by engine power level, yaw angle, flap position and wing roughness. The NASA LRC General Aviation Simulator has been used to evaluate the acoustic sensor output as a control signal for active stall deterrent systems. It has been found that a simple control algorithm is sufficient for stall deterrence.
Citation: Bennett, A., Owens, J., and Harris, R., "Investigation of a Stall Deterrent System Utilizing an Acoustic Stall Sensor," SAE Technical Paper 770473, 1977, https://doi.org/10.4271/770473. Download Citation
Author(s):
A. G. Bennett, J. K. Owens, R. L. Harris
Affiliated:
Mississippi State University
Pages: 12
Event:
National Business Aircraft Meeting and Engineering Display
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Stall
Aircraft
Yaw
Wings
Sensors and actuators
Simulators
Acoustics
Flaps
Mathematical models
Durability
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