Coaxial helicopter
AssigneeAirscooter Corporation
InventorEugene F. Rock
Life of this patent
Estimating the term…
Abstract
A coaxial helicopter, comprising a first rotor carried by a first shaft and a second rotor carried by a second shaft; wherein one of the first and second rotors has cyclic pitch control and the other rotor does not have cyclic pitch control, at least pitch and roll control being implemented by cyclic blade pitch control of only one rotor of the coaxial rotor set. Provisions for yaw control can include differential collective control of the first and second rotors, providing yaw paddles and/or a tail rotor, ducted fan, or an air jet configured for yawing the coaxial helicopter.
Claims27
A helicopter having a coaxial rotor set, comprising;
- a first teeterable rotor carried by a first shaft;
- a second teeterable rotor carried by a second shaft;
- wherein the first rotor is configured for cyclic pitch control, and the second rotor does not have cyclic pitch control, whereby pitch and roll control of the helicopter by means of the coaxial helicopter rotor set is effected by cyclic pitch control of the first rotor.
A coaxial helicopter having a coaxial rotor set including a lower rotor carried by an outer drive shaft and an upper rotor carried by an inner drive shaft, comprising:
- a cyclic blade pitch control linkage operatively coupled to only one of the upper rotor and the lower rotor;
- control of pitch and roll of the helicopter being effected by said cyclic blade pitch control linkage through only one of the upper rotor and the lower rotor;
- and
- wherein the lower rotor and the upper rotor each have a respective diameter, the respective diameters being substantially the same.
A coaxial helicopter, comprising:
- an airframe;
- a power assembly operatively connected to an inner driveshaft and an outer driveshaft;
- an upper rotor carried by the inner driveshaft and having a first diameter;
- a lower rotor carried by the outer driveshaft and having a second diameter that is substantially the same as the first diameter;
- a control system, further comprising:
- a cyclic blade pitch control linkage operatively coupled to only one of the upper and lower rotors;
- control of at least pitch and roll of the helicopter being effected by said cyclic blade pitch control linkages.
A coaxial helicopter having a first rotor and a second rotor counter-rotating with respect to the first, wherein provisions for control of the aircraft comprise:
- a cyclic control for one rotor of said first and second rotors only, and no cyclic control for the other rotor of said first and second rotors;
- a yaw control;
- wherein pitch and roll control are provided by the cyclic control of said one rotor only;
- and
- wherein the first rotor and the second rotor each have a respective diameter, the respective diameters being substantially the same.
Dependencies are inferred from the claim text.