Helicopter with wing augmented lift
A helicopter has a fuselage, a main rotor system connected to the fuselage and configured to rotate in a rotor direction, the main rotor system comprising a retreating rotor blade side and an opposing advancing rotor blade side, and a first wing extending from the fuselage on the retreating rotor blade side. The helicopter comprises no tail rotor system and comprises no counter-rotating rotor system coaxial with the main rotor system.
1. A helicopter, comprising:
a fuselage;
a main rotor system connected to the fuselage and configured to rotate in a rotor direction, the main rotor system comprising a retreating rotor blade side and an opposing advancing rotor blade side;
a first wing extending from the fuselage on the retreating rotor blade side, at least a portion of the first wing being located rearward relative to an axis of rotation of the main rotor system; and
a thrust generator carried by the first wing, the thrust generator being located rearward relative to the axis of rotation of the main rotor system;
wherein the helicopter comprises no tail rotor system and comprises no counter-rotating rotor system coaxial with the main rotor system; and
wherein the helicopter comprises no tail supported wing.
2. The helicopter of claim 1 , further comprising:
a flaperon carried by the first wing.
3. The helicopter of claim 2 , further comprising:
a second wing extending from the fuselage on the advancing rotor blade side.
4. The helicopter of claim 3 , further comprising:
a flaperon carried by the second wing.
5. The helicopter of claim 3 , further comprising:
a thrust generator carried by the second wing.
6. The helicopter of claim 3 , further comprising:
a flaperon carried by the second wing; and
a thrust generator carried by the second wing.
7. The helicopter of claim 2 , wherein the main rotor system comprises a hub and wherein hub forces are transferred to a crossmember so that hub forces are transmitted to the first wing.
8. The helicopter of claim 2 , wherein the thrust generator comprises an electric motor.
9. The helicopter of claim 2 , wherein the thrust generator comprises a convertible engine.
10. The helicopter of claim 2 , wherein the thrust generator comprises a turbo shaft engine.
11. The helicopter of claim 10 , wherein the turbo shaft engine selectively powers the main rotor system.
12. The helicopter of claim 2 , wherein the helicopter comprises a single engine located centered in a left-right direction.
13. The helicopter of claim 2 , wherein the thrust generator is reversible so that thrust is selectively provided in a first direction and a second direction opposite the first direction.
14. The helicopter of claim 2 , wherein the helicopter comprises a generator configured to provide electrical power to the thrust generator.
15. The helicopter of claim 2 , wherein the flaperon comprises a split flaperon configured to create drag for yaw control.
16. The helicopter of claim 2 , wherein the thrust generator comprises a reversible electric motor and an elliptical or nonsymmetrical airfoil.
17. The helicopter of claim 2 , wherein the thrust generator is movable relative to the first wing.
18. The helicopter of claim 2 , wherein the thrust generator is located on a tip of the first wing.
19. The helicopter of claim 2 , wherein the helicopter comprises a hydraulic pump configured to power the thrust generator.