A jet-based rotor flow control system and method

Abstract

This invention discloses a jet-based rotor flow control system and method, relating to the field of helicopter aerodynamics. It includes an engine bleed air inlet, an air filter, a one-way valve, a high-pressure air source chamber, a pressure reducing valve, and a proportional valve, connected sequentially via pipes. The proportional valve is connected to a pressure damper and an air supply slip ring via pipes. The proportional valve is electrically connected to a power supply and a signal generator. The stator of the air supply slip ring is fixed to the helicopter fuselage, and the rotor of the air supply slip ring is connected to a hollow rotor shaft. The outlet of the rotor of the air supply slip ring is connected to an air supply pipe. An internal air pipe communicating with the air supply pipe is arranged inside the rotor blade. Multiple jet outlets are distributed on the upper wing face of the rotor blade. The aerodynamic excitation generated by this invention has advantages such as high strength, simple structure, and minimal impact on the original aerodynamic profile, showing significant advantages and application potential in rotor retreat blade stall separation control.

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