Patent ID: 6352219
Filing Date: 2002-03-05
Classification: B64C

Abstract:
An aircraft comprised of:a fuselage; a drive shaft rotatably disposed in said fuselage, said drive shaft having an end; an aerodynamic generator disposed around said end of said shaft consisting of an aerodynamic rotor attached to said end of said shaft; and an aerodynamic stator fixed to said fuselage over said rotor; a control device fixedly attached to said fuselage; said control device having an actuator; said control device controlling said aerodynamic generator with said actuator; said control device being responsive to a plurality of commands; wherein said aerodynamic generator produces an aerodynamic force in response to one of said commands whose intensity, direction and sense of direction can be controlled through said control device; wherein vertical lifting and landing are achieved by orienting the direction and sense of direction of the aerodynamic force vertically in respect to the horizon plane; wherein said aerodynamic rotor further comprises a blade carrier fixedly attached to said shaft end; four aeroprofiles disposed symmetrically about said shaft on said blade carrier, said aeroprofiles having a Main Axis and a Guided Axis; said control device including an eccentric bearing having an eccentric axis; a guide linkably connecting said eccentric bearing and said guided axis of said aeroprofile; wherein the aeroprofiles are rotatably connected to said blade carrier about the Main Axis of the aeroprofile; said aeroprofiles rotating around the Drive Shaft and oscillating in circles around the main axis of the aeroprofile wherein the Eccentric Bearing can be translated with respect to the Drive Shaft and can rotate around a center of Drive Shaft from 0 to 360Â°; wherein translating the center of the Eccentric Bearing with respect to the Drive Shaft provokes an eccentricity of the Eccentric Bearing which is then transmitted by the Guide-bar to the Guided Axis on the rotor aeroprofiles, causing rotation of the aeroprofile around the Main Axis for the angle of attack proportional to the eccentricity of the Guide-bar and which in one full revolution changes as function of a sinus of an angle of the aeroprofile with respect to a center of Drive Shaft.