Stopped rotor aircraft

• US 9,944,387 B2
• Filed: 05/18/2017
• Issued: 04/17/2018
• Est. Priority Date: 05/24/2016
• Status: Active Grant

• Current Assignee: Kitty Hawk Corporation
• Original Assignee: Kitty Hawk Corporation
• Inventors: Vander Lind, Damon, Horn, Gregory Mainland
• Primary Examiner(s): Bonzell, Philip J
• Assistant Examiner(s): Kreiner, Michael B
• Application Number:
  US15/599,184
• Publication Number:
  US 20170341740A1
• Time in Patent Office: 334 Days
• CPC Class Codes: B64C 2027/8236 including pusher propellers
• CPC Class Codes: B64C 2027/8272 comprising fins, or movable rudders
• CPC Class Codes: B64C 2027/8281 comprising horizontal tail planes
• CPC Class Codes: B64C 27/14 Direct drive between power plant and rotor hub
• CPC Class Codes: B64C 27/26 characterised by provision of fixed wings
• CPC Class Codes: B64C 27/30 with provision for reducing drag of inoperative rotor
• CPC Class Codes: B64C 27/467 Aerodynamic features
• CPC Class Codes: B64C 27/82 characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
• CPC Class Codes: B64C 31/024 with auxiliary power plant

Abstract

A stoppable rotor, which includes a first and second blade and rotates about a substantially vertical axis, is stopped with the first blade pointing forward and the second blade pointing backward while the aircraft is mid-flight. Anti-torque is provided using a set of one or more combination rotors in a first mode of operation in order to counter torque produced by the stoppable rotor when the stoppable rotor is rotating where the set of combination rotors rotate about a substantially longitudinal axis. Forward thrust is provided using the set of combination rotors in a second mode of operation when the stoppable rotor is not rotating.

Claims

1. An aircraft, comprising:

a stoppable rotor which includes a first blade and a second blade, wherein;

the stoppable rotor is configured to rotate about a substantially vertical axis; and

the stoppable rotor is configured to stop with the first blade pointing forward and the second blade pointing backward while the aircraft is mid-flight; and

a set of one or more combination rotors, wherein;

the set of combination rotors is configured to rotate about a substantially longitudinal axis;

in a first mode of operation, the set of combination rotors are configured to provide anti-torque in order to counter torque produced by the stoppable rotor when the stoppable rotor is rotating; and

in a second mode of operation, the set of combination rotors are configured to provide forward thrust when the stoppable rotor is not rotating, wherein at least one combination rotor in the set of combination rotors rotates in a first direction during the first mode of operation and rotates in a second direction during the second mode of operation.

2. The aircraft recited in claim 1, wherein the first blade is shorter than the second blade.

3. The aircraft recited in claim 1 further including a dedicated anti-torque rotor.

4. The aircraft recited in claim 1, wherein at least one of the first blade and the second blade includes a flap.

5. The aircraft recited in claim 1, wherein:

the first blade is shorter than the second blade; and

the second blade includes a tailfin.

6. The aircraft recited in claim 1, wherein:

the first blade is shorter than the second blade; and

the second blade includes a double-sided tailfin.

7. A method, comprising:

stopping a stoppable rotor which includes a first blade and a second blade, wherein;

the stoppable rotor is configured to rotate about a substantially vertical axis; and

the stoppable rotor is configured to stop with the first blade pointing forward and the second blade pointing backward while an aircraft, which includes the stoppable rotor, is mid-flight;

providing anti-torque using a set of one or more combination rotors in a first mode of operation in order to counter torque produced by the stoppable rotor when the stoppable rotor is rotating, wherein the set of combination rotors is configured to rotate about a substantially longitudinal axis; and

providing forward thrust using the set of combination rotors in a second mode of operation when the stoppable rotor is not rotating, wherein;

the aircraft further includes the set of combination rotors; and

at least one combination rotor in the set of combination rotors rotates in a first direction during the first mode of operation and rotates in a second direction during the second mode of operation.

8. The method recited in claim 7, wherein the first blade is shorter than the second blade.

9. The method recited in claim 7, wherein the aircraft further includes a dedicated anti-torque rotor.

10. The method recited in claim 7, wherein at least one of the first blade and the second blade includes a flap.

11. The method recited in claim 7, wherein:

the first blade is shorter than the second blade; and

the second blade includes a tailfin.

12. The method recited in claim 7, wherein:

the first blade is shorter than the second blade; and

the second blade includes a double-sided tailfin.

13. A computer program product, the computer program product being embodied in a non-transitory computer readable storage medium and comprising computer instructions for:

stopping a stoppable rotor which includes a first blade and a second blade, wherein;

the stoppable rotor is configured to rotate about a substantially vertical axis; and

the stoppable rotor is configured to stop with the first blade pointing forward and the second blade pointing backward while an aircraft, which includes the stoppable rotor, is mid-flight;

providing anti-torque using a set of one or more combination rotors in a first mode of operation in order to counter torque produced by the stoppable rotor when the stoppable rotor is rotating, wherein the set of combination rotors is configured to rotate about a substantially longitudinal axis; and

providing forward thrust using the set of combination rotors in a second mode of operation when the stoppable rotor is not rotating, wherein;

the aircraft further includes the set of combination rotors; and

at least one combination rotor in the set of combination rotors rotates in a first direction during the first mode of operation and rotates in a second direction during the second mode of operation.

14. The computer program product recited in claim 13, wherein the first blade is shorter than the second blade.

15. The computer program product recited in claim 13, wherein the aircraft further includes a dedicated anti-torque rotor.

16. The computer program product recited in claim 13, wherein at least one of the first blade and the second blade includes a flap.

17. The computer program product recited in claim 13, wherein:

the first blade is shorter than the second blade; and

the second blade includes a tailfin.

18. The computer program product recited in claim 13, wherein:

the first blade is shorter than the second blade; and

the second blade includes a double-sided tailfin.