Sealed hub and shaft fairing for rotary wing aircraft

Patent metadata

Field	Value
Publication number	US-11235869-B2
Application number	US-202016832307-A
Country	US
Kind code	B2
Filing date	Mar 27, 2020
Priority date	Oct 1, 2014
Publication date	Feb 1, 2022
Grant date	Feb 1, 2022

Abstract

An aircraft includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail. The translational thrust system provides translational thrust to the airframe. An upper hub fairing is positioned at the upper rotor assembly. A lower hub fairing is positioned at the lower rotor assembly. A shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The upper hub fairing is substantially sealed to the shaft fairing and the lower hub fairing is substantially sealed to the shaft fairing.

First claim

What is claimed is:

1. An aircraft comprising:
an airframe;
an extending tail;
a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly;
a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe;
an upper hub fairing positioned at the upper rotor assembly;
a lower hub fairing positioned at the lower rotor assembly; and
a shaft fairing disposed between the upper hub fairing and the lower hub fairing;
wherein the upper hub fairing is substantially sealed to the shaft fairing and the lower hub fairing is substantially sealed to the shaft fairing.

2. The aircraft of claim 1 wherein, the upper hub fairing is contoured to match an upper surface of the shaft fairing.

3. The aircraft of claim 1 wherein, the lower hub fairing is contoured to match a lower surface of the shaft fairing.

4. The aircraft of claim 1 wherein:
the shaft fairing is generally airfoil shaped.

5. The aircraft of claim 4 wherein, the shaft fairing is shaped to minimize drag.

6. The aircraft of claim 1 wherein, the upper hub fairing, lower hub fairing and shaft fairing are disposed about an axis of rotation of the main rotor assembly.

7. The aircraft of claim 1 wherein, at least 80% of the shaft fairing length is located aft of the axis of rotation of the main rotor assembly.

8. The aircraft of claim 7 wherein, at least 85% of the shaft fairing length is located aft of the axis of rotation of the main rotor assembly.

9. The aircraft of claim 1 wherein, the upper hub fairing, the shaft fairing and the lower hub fairing are coated with a conductive material.

10. The aircraft of claim 1 wherein, the main rotor assembly is a rigid rotor system.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Egolf Thomas Alan
• Beatty Robert D
• Law Gary
• Butler Chris P
• Nussenblatt Eric Lucien
• Reed Edward

Classifications

• B64C27/10 Primary

  arranged coaxially · CPC title

• B64C27/82

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• B64C2027/8272

  comprising fins, or movable rudders · CPC title

• B64C2027/8236

  including pusher propellers · CPC title

• B64C27/14

  Direct drive between power plant and rotor hub · CPC title