Gearbox for a dual rotor, rotary wing aircraft

Patent metadata

Field	Value
Publication number	US-10676181-B2
Application number	US-201515507178-A
Country	US
Kind code	B2
Filing date	Sep 25, 2015
Priority date	Oct 1, 2014
Publication date	Jun 9, 2020
Grant date	Jun 9, 2020

Abstract

An aircraft is provided including an airframe, an extending tail, a counter-rotating, coaxial main rotor assembly having an upper rotor assembly and a lower rotor assembly, and a translational thrust system including a propeller positioned at the extending tail. The translational thrust system is configured to provide translational thrust to the airframe when the aircraft is in a non-autorotation state and to generate power when in an autorotation state. A gearbox interconnects the propeller and the main rotor assembly to drive the main rotor assembly and the translational thrust system in the non-autorotation state. When the aircraft is in autorotation, the power generated by the propeller drives rotation of the main rotor assembly via the gearbox.

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 including a propeller positioned at the extending tail, the translational thrust system configured to provide translational thrust to the airframe when the aircraft is in a non-autorotation state, and to generate power when the aircraft is in an autorotation state; and
a gearbox interconnecting the propeller and the main rotor assembly to drive the main rotor assembly and the translational thrust system in the non-autorotation state, wherein when the aircraft is in the autorotation state, the power generated by the propeller drives rotation of the main rotor assembly via the gearbox.

2. The aircraft according to claim 1 , wherein when the aircraft is in the autorotation state, a position of at least one of a plurality of blades of the propeller is positioned in a windmill-brake state to generate the power.

3. A method of operating an aircraft, comprising:
adjusting a pitch of at least one of a plurality of propeller blades of a translational thrust system of the aircraft from a pitch which generates thrust to a pitch which generates power; and
driving rotation of a main rotor assembly of the aircraft using the power generated by the translational thrust system while the propeller blades are at the adjusted pitch.

4. The method according to claim 3 , wherein the pitch of the at least one of a plurality of propeller blades is adjusted by a fly-by-wire flight control system.

5. The method according to claim 4 , wherein the fly-by-wire flight control system is configured to adjust the pitch of the at least one of the plurality of propeller blades in response to a manual input.

6. The method according to claim 4 , wherein the fly-by-wire flight control system is configured to adjust the pitch of the at least one of the plurality of propeller blades in response to an automatic input.

7. The method according to claim 3 , wherein the main rotor assembly and the translational thrust assembly are operably coupled by a gearbox.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Eller Erez
• Luszcz Matthew T
• Eadie William J
• Weiner Steven D

Classifications

• B64C27/54

  Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement · CPC title

• B64C27/08

  with two or more rotors · CPC title

• B64C2027/8236

  including pusher propellers · CPC title

• B64C13/04

  actuated personally · CPC title

• G05D1/0204

  to counteract a sudden perturbation, e.g. cross-wind, gust · CPC title