Low drag sail fairing for coaxial rotor

Patent metadata

Field	Value
Publication number	US-11370532-B2
Application number	US-201916431341-A
Country	US
Kind code	B2
Filing date	Jun 4, 2019
Priority date	Jun 4, 2019
Publication date	Jun 28, 2022
Grant date	Jun 28, 2022

Abstract

A rotary wing aircraft and a rotor assembly of a rotary wind aircraft is disclosed. The rotary wing aircraft includes at least one engine, and the rotor assembly is coupled to the at least one engine. The rotor assembly includes a first rotor hub, a second rotor hub, and a shaft fairing between the first rotor hub to the second rotor hub, the shaft fairing defined by a chord that varies between the first rotor hub and the second rotor hub.

First claim

What is claimed is:

1. A rotor assembly, comprising:
a first rotor hub;
a second rotor hub; and
a shaft fairing between the first rotor hub to the second rotor hub and including a front surface, a rear edge, a first axial end adjacent the first rotor hub, and a second axial end adjacent the second rotor hub, the shaft fairing defined by a chord that extends between the front surface and the rear edge, wherein the chord varies between the first rotor hub and the second rotor hub, and further wherein the shaft fairing defines an inflection point at which a minimum chord length occurs and the inflection point is closer to the first axial end than the second axial end,
wherein a thickness-to-chord ratio of the shaft fairing is constant for each axial cross-section of the shaft fairing.

2. The rotor assembly of claim 1 , wherein the shaft fairing comprises an hour glass shape along the main rotor axis configured to reduce flow separation at the aft portions of the first and second rotor hubs compared to a shaft fairing having a constant thickness along the main rotor axis.

3. The rotor assembly of claim 1 , wherein a thickness of the shaft fairing has an inflection point at the location of the inflection point of the minimum chord length.

4. The rotor assembly of claim 1 , wherein the first rotor hub is an upper rotor hub and the second rotor hub is a lower rotor hub.

5. The rotor assembly of claim 1 , wherein the shaft fairing is structured to comprise a rotor shaft, that operatively connects the first rotor hub and the second rotor hub.

6. The rotary wing aircraft of claim 1 , wherein the shaft fairing includes a first chord length at the first rotor hub and a second chord length at the second rotor hub, and the first chord length is less than the second chord length.

7. The rotary wing aircraft of claim 1 , wherein the shaft fairing includes a height that is constant from a main rotor axis to the trailing rear edge.

8. The rotary wing aircraft of claim 1 , wherein the shaft fairing includes a height that is constant from a main rotor axis to the rear edge.

9. A rotary wing aircraft, comprising:
at least one engine; and
a rotor assembly coupled to the at least one engine, the rotor assembly comprising:
a first rotor hub;
a second rotor hub; and

a shaft fairing between the first rotor hub to the second rotor hub and including a front surface, a rear edge, a first axial end adjacent the first rotor hub, and a second axial end adjacent the second rotor hub, the shaft fairing defined by a chord that extends between the front surface and the rear edge, wherein the chord varies between the first rotor hub and the second rotor hub, and further wherein the shaft fairing defines an inflection point at which a minimum chord length occurs and the inflection point is closer to the first axial end than the second axial end,
wherein a thickness of the shaft fairing has an inflection point at the location of the inflection point of the minimum chord length.

10. The rotary wing aircraft of claim 9 , wherein a thickness-to-chord ratio of the shaft fairing is constant for each axial cross-section of the shaft fairing.

11. The rotary wing aircraft of claim 9 , wherein the shaft fairing comprises an hour glass shape along the main rotor axis configured to reduce flow separation at the aft portions of the first and second rotor hubs compared to a shaft fairing having a constant thickness along the main rotor axis.

12. The rotary wing aircraft of claim 9 , wherein the first rotor hub is an upper rotor hub and the second rotor hub is a lower rotor hub.

13. The rotary wing aircraft of claim 9 , wherein the shaft fairing is structured to comprise a rotor shaft, the rotor shaft being operatively connected to the at least one engine.

14. The rotary wing aircraft of claim 9 , wherein the shaft fairing includes a first chord length at the first rotor hub and a second chord length at the second rotor hub, and the first chord length is less than the second chord length.

15. The rotary wing aircraft of claim 9 , wherein the shaft fairing includes a height that is constant from a main rotor axis to the trailing rear edge.

16. A rotary wing aircraft, comprising:
at least one engine; and
a rotor assembly coupled to the at least one engine, the rotor assembly comprising:
a first rotor hub;
a second rotor hub; and

a shaft fairing extends between the first rotor hub and the second rotor hub, the shaft fairing including a front surface, a rear edge, a first axial end adjacent the first rotor hub and a second axial end adjacent the second rotor hub, wherein the shaft fairing is defined by a chord that extends between the front surface and the rear edge and the chord varies between the first axial end and the second axial end, and
further wherein a first chord length is at the first axial end, a second chord length is at the second axial end, and a third chord length is closer to the first axial end than the second axial end, the third chord length defines an inflection point and a minimum chord length of the shaft fairing,
wherein a thickness of the shaft fairing has an inflection point at the location of the inflection point of the minimum chord length.

17. The rotary wing aircraft of claim 16 , wherein the first chord length is less than the second chord length.

18. The rotary wing aircraft of claim 16 , wherein the shaft fairing comprises an hour glass shape along the main rotor axis configured to reduce flow separation at the aft portions of the first and second rotor hubs compared to a shaft fairing having a constant thickness along the main rotor axis.

19. The rotary wing aircraft of claim 16 , wherein a thickness-to-chord ratio of the shaft fairing is constant for each axial cross-section of the shaft fairing.

Assignees

• Lockheed Corp

Inventors

• Bowles Patrick Ormande
• Battisti Margaret G
• Wake Brian Ernest
• Lorber Peter F
• Min Byung-Young

Classifications

• B64C27/10 Primary

  arranged coaxially · CPC title

• B64C7/00

  Structures or fairings not otherwise provided for · CPC title

• B64C2027/8272

  comprising fins, or movable rudders · CPC title

• B64C2027/8281

  comprising horizontal tail planes · CPC title

• B64C2027/8236

  including pusher propellers · CPC title