Icing and stalling on the surfaces of aircraft wings endanger flight safety. The object of this research is a nanosecond pulsed dielectric-barrier-discharge plasma actuation unit with a distributed layout, and the aerodynamic performance of aircraft wing surfaces under icing and stalling conditions is improved by changing the plasma actuation electrical parameters. Actuated under low voltage and frequency, the unit acts as a sensor to judge icing according to the change in electrical parameters. Actuated under high voltage and frequency, the discharge is severe and generates a large amount of heat, giving rise to an anti-icing unit; anti-icing is carried out through distributed-layout plasma actuation, forming modulated ice with evenly spaced distribution, which acts as a vortex generator and lessens the deterioration of aircraft aerodynamic performance under icing conditions. Actuating under high voltage and low frequency enables flow control, delays stalling, and increases lift. The different plasma-actuation functions are realized by connecting multiple units, which offers improved aircraft survivability in complex weather conditions.
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2022
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