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Investigation of a Stall Deterrent System Utilizing an Acoustic Stall Sensor
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English
Abstract
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.
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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.Also In
References
- Chevalier Howard L. “Aerodynamic Spoiler for Preventing Airplane Stall/Spin Type Accidents,” Final Report No. FAA-RD-75-21, U.S. Department of Transportation Federal Aviation Administration December 1974
- Chevalier Howard L. Brusse Joseph C. “A Stall/Spin Prevention Device for General-Aviation Aircraft,” SAE Paper No. 730333 April 3-6 1973
- Coker Cecil “Lift Reserve Indicator,” Internal Report Aerospace and Aerophysics Engineering Department, Mississippi State University October 1956
- Roberts S. C. Boaz V. Gaddis M. “Design and Evaluation of an Acoustic Stall Warning Indicator,” Research Report No. 11 Aerophysics and Aerospace Engineering Department, Mississippi State University July 1965
- Simpson Don E. “An Experimental Investigation of the Output Characteristics of an Acoustic Stall Sensor,” M.S. Thesis Aerophysics and Aerospace Engineering Department, Mississippi State University August 1975