Helicopter rotor wing type determination method and system

Abstract

The invention discloses a helicopter rotor wing type determination method and a system. The method comprises the following steps: randomly generating airfoil profile sample points by adopting a Latinhypercube sampling method; according to the airfoil profile sample points, determining upper and lower airfoil profile representation equations of the airfoil profile by adopting a category shape function transformation method; carrying out dynamic characteristic simulation on the airfoil profile by adopting a computational fluid mechanics method according to the upper and lower airfoil profile representation equations to obtain flow field characteristics of the airfoil profile; establishing a mapping relationship between airfoil profile sample points and flow field characteristics by adoptinga Kriging model, and training the mapping relationship by adopting a maximum likelihood estimation method and an expected value criterion to obtain a trained mapping relationship; determining an optimal airfoil profile sample point by adopting an NSGA-II algorithm according to the trained mapping relationship; and determining the rotor wing type according to the optimal wing type sample point. The aerodynamic characteristics of the airfoil profile in the variable incoming flow-variable attack angle state are optimally designed, and the dynamic stall characteristic in the state can be effectively relieved.

Description

technical field [0001] The invention relates to the technical field of rotor airfoil design, in particular to a method and system for determining a helicopter rotor airfoil. Background technique [0002] The rotor is the key lift and control component of the helicopter, and the aerodynamic characteristics of the airfoil have an important influence on the aerodynamic performance and handling characteristics of the rotor and the helicopter. When the helicopter flies forward, the rotor blades rotate, flap and change pitch at the same time, so that the blade profile is under the periodically changing incoming flow and angle of attack, and a dynamic stall may occur on the backward side, resulting in a sharp drop in lift. The sudden increase of drag and torque is not conducive to flight. Therefore, alleviating or even suppressing the occurrence of airfoil dynamic stall in the rotor environment is of great significance to improve the aerodynamic performance and control performance...

AI Technical Summary

Problems solved by technology

However, these works mainly consider the static characteristics of the airfoil and the dynamic characteristics under the condition of constant speed and variable angle of attack. At present, there is still a gap in the design of rotor airfoils under the state of variable flow and variable angle of attack in the actual rotor environment.

Images