Helicopter yaw and propulsion mechanism

A helicopter which includes:

• a fuselage;
• a vertical stabilizer connected to said fuselage;
• a rudder connected to said stabilizer;
• a single main lifting rotor rotatably connected to said fuselage for lifting and propelling said helicopter;
• a motor connected to said fuselage and rotatably connected to said rotor;
• and a mechanism for controlling yaw and providing thrust augmentation to aid in propelling the helicopter forward which comprises:
• an air inlet in said fuselage;
• a duct positioned in said fuselage, connected at one end thereof to said inlet so that air may pass through said inlet to said duct;
• a first nozzle positioned in the rear portion of said fuselage, connected to said duct so air may pass from said duct and exit through said first nozzle generating a force which acts in a first direction tending to counteract torque generated when said motor drives said rotor;
• a second nozzle positioned in the rear portion of said fuselage on the side thereof opposite said first nozzle connected to said duct so air may pass from said duct and exit through said second nozzle thereby generating a force which acts in a second direction opposite said first direction;
• a third nozzle positioned in the rear portion of said fuselage connected to said duct so air may pass from said duct and exit through said thrid nozzle generating a force which acts in a third direction tending to propel said aircraft forward;
• a first valve mounted in said first nozzle for controlling the volume of air which may pass there through;
• a second valve mounted in said second nozzle for controlling the volume of air which may pass there through;
• a third valve pivotally mounted in said third nozzle for controlling the volume of air which may pass there through;
• a fan mounted in said duct for driving air from said inlet to said nozzles, operably connected to said motor;
• and
• a control means, including a pilot operable member connected to said rudder, connected to said fuselage, and connected to said first, second and third valves to vary the position of said valves, said control means maintaining said second and third valves in a closed position below a predetermined first velocity of the helicopter while varying the position of said first valve in response to pilot movements of said pilot operable member, said control means maintaining said first and second valves in a closed position above a predetermined second velocity of the helicopter while maintaining said third valve in an open position, and said control means varying the position of said second valve in response to pilot movements of said pilot operable member below said first predetermined velocity in the event autorotation occurs so that the forces generated by said first nozzle and said second nozzles cooperate to control the yaw of said aircraft.