Method and system for dynamic stall control of helicopter rotor

Abstract

The invention relates to a stall control method and system for a helicopter rotor airfoil. In the helicopter rotor airfoil stall control method, synthetic jet exciters are arranged within the range of 0.7R to 0.9R on the blade and 15% c away from the leading edge of the blade, and the distance between the synthetic jet exciters is about 2.6% R, R is the length of the blade, and c is the chord length, including: obtaining the current operating parameters of the driver and the current flight state parameters of the aircraft; determining the instantaneous angle of attack of the helicopter rotor according to the current operating parameters of the driver and the current flight state parameters of the aircraft; Determine the stall angle of attack according to the current flight state parameters of the aircraft; judge whether the instantaneous angle of attack is greater than the stall angle of attack, if so, turn on the synthetic jet exciter, and simultaneously control the upward deflection of the trailing edge winglet at 0.7R~0.9R on the blade for 0~ 5 degrees; if not, turn off the synthetic jet exciter, and control the trailing edgelet at 0.7R-0.9R on the blade to deflect downward by 0-5 degrees. By adopting the control method and system provided by the present invention, the aerodynamic characteristics of the rotor can be efficiently improved and the dynamic stall of the rotor can be controlled.

Description

technical field [0001] The invention relates to the field of improving the dynamic stall of the helicopter rotor, in particular to a method and system for controlling the dynamic stall of the helicopter rotor. Background technique [0002] When the helicopter is flying, the left and right airflow of the rotor is asymmetrical. In order to maintain balance, the blade needs to increase the pitch angle (periodic pitch change) when the blade is on the backward side to offset the adverse effect of the reduced profile velocity. When the flight speed is high, the backward side blades are prone to stall due to excessive angle of attack, and because the profile angle of attack and speed change periodically during the movement of the blades, a unique stall phenomenon of helicopter rotors is formed—— — Dynamic stall. The sudden drop of blade lift and aerodynamic moment oscillation caused by stall will directly lead to an increase in the vibration level of the helicopter, and even affec...

AI Technical Summary

Problems solved by technology

[0012] The purpose of the present invention is to provide a dynamic stall control method and system for a helicopter rotor to solve the problems of low control degree of stall phenomenon, easy fluctuation of aerodynamic parameters and vortex structure oscillation in the existing synthetic jet method to control helicopter rotor airfoil stall

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