Transmission for coaxial multi-rotor system

• US 10,053,212 B2
• Filed: 05/22/2015
• Issued: 08/21/2018
• Est. Priority Date: 05/29/2014
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Sheridan, William G.
• Primary Examiner(s): Scott, Jacob S.
• Assistant Examiner(s): Dang, Tinh
• Application Number:
  US15/313,730
• Publication Number:
  US 20170190415A1
• Time in Patent Office: 1,187 Days
• CPC Class Codes: B64C 2027/8236 including pusher propellers
• CPC Class Codes: B64C 27/10 arranged coaxially
• CPC Class Codes: B64C 27/12 Rotor drives
• 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: F16H 1/46 Systems consisting of a plurality of gear trains each with orbital gears, i.e. systems having three or more central gears

Abstract

A coaxial, dual rotor system includes a first rotor assembly located at a rotor axis and rotatable thereabout and a second rotor assembly located at the rotor axis radially inboard of the first rotor assembly and rotatable thereabout. A rotationally fixed static mast is located radially between the first rotor assembly and the second rotor assembly. A transmission includes a rotor input shaft including a first sun gear and a second sun gear. A star gear arrangement is operably connected to the first sun gear and to the static mast to drive rotation of the first rotor assembly about the rotor axis and a planetary gear arrangement is operably connected to the second sun gear and to the static mast to drive rotation of the second rotor assembly about the rotor axis.

Claims

1. A coaxial, dual rotor system comprising:

a first rotor assembly disposed at a rotor axis and rotatable thereabout;

a second rotor assembly disposed at the rotor axis radially inboard of the first rotor assembly and rotatable thereabout;

a rotationally fixed static mast disposed radially between the first rotor assembly and the second rotor assembly; and

a transmission including;

a rotor input shaft including a first sun gear and a second sun gear;

a star gear arrangement operably connected to the first sun gear and the static mast to drive rotation of the first rotor assembly about the rotor axis; and

a planetary gear arrangement operably connected to the second sun gear and the static mast to drive rotation of the second rotor assembly about the rotor axis.

2. The rotor system of claim 1, wherein the star gear arrangement includes:

a plurality of star gears interactive with the first sun gear, the plurality of star gears disposed at the static mast and rotatably secured thereto; and

a first ring gear fixed to the first rotor assembly and interactive with the plurality of star gears to transfer rotation of the first sun gear to the first rotor assembly via the plurality of star gears.

3. The rotor system of claim 1, wherein the planetary gear arrangement includes:

a second ring gear fixed to the static mast; and

a plurality of planet gears rotatably secured to the second rotor assembly and interactive with the second sun gear and the second ring gear, the rotation of the second sun gear thus driving rotation of the second rotor assembly about the rotor axis.

4. The rotor system of claim 1, wherein the first rotor assembly is driven in a first direction about the rotor axis and the second rotor assembly is driven about the rotor axis in a second direction opposite to the first direction.

5. The rotor system of any of claim 1, further comprising a first rotor bearing to support the first rotor assembly at the static mast.

6. The rotor system of claim 1, further comprising a second rotor bearing to support the second rotor assembly at the static mast.

7. A dual coaxial rotor rotorcraft comprising:

an airframe;

a drive system disposed at the airframe; and

a coaxial, dual rotor system operably connected to the drive system including;

a first rotor assembly disposed at a rotor axis and rotatable thereabout;

a second rotor assembly disposed at the rotor axis radially inboard of the first rotor assembly and rotatable thereabout;

a rotationally fixed static mast disposed radially between the first rotor assembly and the second rotor assembly and fixed to the airframe; and

a transmission including;

a rotor input shaft including a first sun gear and a second sun gear;

a star gear arrangement operably connected to the first sun gear and the static mast to drive rotation of the first rotor assembly about the rotor axis; and

a planetary gear arrangement operably connected to the second sun gear and the static mast to drive rotation of the second rotor assembly about the rotor axis.

8. The rotorcraft of claim 7, wherein the star gear arrangement includes:

a plurality of star gears interactive with the first sun gear, the plurality of star gears disposed at the static mast and rotatably secured thereto; and

a first ring gear fixed to the first rotor assembly and interactive with the plurality of star gears to transfer rotation of the first sun gear to the first rotor assembly via the plurality of star gears.

9. The rotorcraft of claim 7, wherein the planetary gear arrangement includes:

a second ring gear fixed to the static mast; and

a plurality of planet gears rotatably secured to the second rotor assembly and interactive with the second sun gear and the second ring gear, the rotation of the second sun gear thus driving rotation of the second rotor assembly about the rotor axis.

10. The rotorcraft of claim 7, wherein the first rotor assembly is driven in a first direction about the rotor axis and the second rotor assembly is driven about the rotor axis in a second direction opposite to the first direction.

11. The rotorcraft of claim 7, further comprising a first rotor bearing to support the first rotor assembly at the static mast.

12. The rotorcraft of claim 7, further comprising a second rotor bearing to support the second rotor assembly at the static mast.

13. The rotorcraft of claim 7, wherein the drive system is connected to the transmission via an output shaft.

14. The rotorcraft of claim 7, further comprising a translational thrust system including a propeller operably connected to the drive system via the output shaft.

15. The rotorcraft of claim 14, further comprising a propeller gear reduction to operably connect the propeller to the output shaft, the propeller gear reduction including:

a tail sun gear fixed to the output shaft;

a fixed tail ring gear; and

a plurality of tail planet gears rotatably secured to a propeller shaft and operably connected to the tail sun gear and the tail ring gear, such that rotation of the output shaft drives rotation of the propeller shaft.