The present document describes a yaw control system for a helicopter having a controllable aft rudder. The system comprises a fan for blowing low pressure air impinging upon the controllable aft rudder. During flight, the main rotor assembly drives the fan and the air flow impinging upon the control
The present document describes a yaw control system for a helicopter having a controllable aft rudder. The system comprises a fan for blowing low pressure air impinging upon the controllable aft rudder. During flight, the main rotor assembly drives the fan and the air flow impinging upon the controllable aft rudder creates a side force which enables yaw control.
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1. A yaw control system for a helicopter having a controllable aft rudder, an engine and a main rotor assembly, the yaw control system comprising: a low pressure fan for producing a low pressure air flow impinging upon the controllable aft rudder, the low pressure fan being mechanically connected to
1. A yaw control system for a helicopter having a controllable aft rudder, an engine and a main rotor assembly, the yaw control system comprising: a low pressure fan for producing a low pressure air flow impinging upon the controllable aft rudder, the low pressure fan being mechanically connected to the main rotor assembly;wherein during flight, the main rotor assembly drives the low pressure fan without a direct load path from the engine to the low pressure fan and the low pressure air flow impinging upon the controllable aft rudder creates a side force which enables yaw control. 2. The yaw control system of claim 1, further comprising a coupling device between the main rotor assembly and the low pressure fan for providing the mechanical connection therebetween. 3. The yaw control system of claim 2, wherein the coupling device comprises a clutch for selectively mechanically disconnecting the low pressure fan from the main rotor assembly. 4. The yaw control system of claim 3, further comprising a speed sensing device for detecting a forward speed of the helicopter, the speed sensing device sending a control signal to the clutch to control selectively the disconnecting of the low pressure fan from the main rotor assembly. 5. The yaw control system of claim 2, wherein the main rotor assembly comprises a main rotor mast and where the coupling device provides the mechanical connection is between the main rotor mast and the low pressure fan. 6. The yaw control system of claim 5, wherein the coupling device comprises a clutch for selectively mechanically disconnecting the low pressure fan from the main rotor assembly. 7. The yaw control system of claim 2, wherein the coupling device comprises one of a transmission and a belt drive. 8. The yaw control system of claim 1, further comprising a duct for directing the air from the low pressure fan to the controllable aft rudder. 9. The yaw control system of claim 8, wherein the duct is located substantially between the low pressure fan and the controllable aft rudder. 10. A helicopter comprising: a main rotor assembly;an engine;a controllable aft rudder;a yaw control system comprising a low pressure fan for producing a low pressure air flow impinging upon the controllable aft rudder, the low pressure fan being mechanically connected to the main rotor assembly;wherein during flight, the main rotor assembly drives the low pressure fan without a direct load path from the engine to the low pressure fan and the low pressure air flow impinging upon the controllable aft rudder creates a side force which enables yaw control. 11. The yaw control system of claim 10, further comprising a coupling device between the main rotor assembly and the low pressure fan for providing the mechanical connection therebetween. 12. The yaw control system of claim 11, wherein the main rotor assembly comprises a main rotor mast and where the coupling device provides the mechanical connection is between the main rotor mast and the low pressure fan. 13. The helicopter of claim 12, wherein the main rotor assembly comprises main rotor blades each of which comprises an air passage and tip jets, upon exiting the tip jets, air drives the main rotor assembly. 14. The helicopter of claim 13, wherein the main rotor mast comprises a hollow portion for feeding air to the air passage of the main rotor blades. 15. The helicopter of claim 10, further comprising a duct for directing the air from the low pressure fan to the controllable aft rudder. 16. The helicopter of claim 15, wherein the duct is located substantially between the low pressure fan and the aft rudder. 17. A yaw control system for a helicopter having an aft rudder, an engine and a main rotor assembly, the yaw control system comprising: a fan for producing an air flow impinging upon the aft rudder, the fan being mechanically connected to the main rotor assembly;wherein during flight, the main rotor assembly drives the fan without a direct load path from the engine to the low pressure fan and the air flow impinging upon the aft rudder creates a side force which enables yaw control. 18. The yaw control system of claim 17, wherein the aft rudder forms part of the yaw control system and comprises a controllable aft rudder. 19. The yaw control system of claim 17, wherein the fan comprises a low pressure fan for producing a low pressure air flow impinging upon the aft rudder.
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Ramme Maurice (6326 Beach Dr. SW. Seattle WA 98136) Ramme Monte (17620 - 15th Pl. W. Alderwood Manor WA 98036), Air jet reaction contrarotating rotor gyrodyne.
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