CIRCULATION CONTROL FOR ROTOR SYSTEM FOR HELICOPTER TYPE AIRCRAFT

摘要

The present invention relates to a circulation flow control rotor system for an aircraft which includes rotor blades provided with slit shaped blower nozzles further comprising control devices for obtaining a cyclic or multicyclic or collective rotor blade angle control under utilization of individual pressure gas flow from a pressure chamber to the nozzle slits; further including deformable control members which are going to be deformed in accordance with certain rules underlying the requisite control.