Reducing Helicopter Vibration Loads by Individual Blade Control with Genetic Algorithm

A rotor that can realize individual blade pitch control was designed. This paper focuses on finding the trend of helicopter vibration loads after applying multiple high-order harmonic control. The Glauert inflow model introduced to calculate induced velocity blades in a disk plane, and Leishman Beddoes (L-B) unsteady dynamic employed aerodynamic forces each section blade. It found influence load reduction is similar different advanced ratios. After these calculations, genetic algorithm used best combination amplitude phase higher order under specific flight state. Under effect high input, hub could be reduced by about 65%. These results theoretically applied design law reduce loads.