Vibration isolation systems for compound helicopters

Patent metadata

Field	Value
Publication number	US-11932380-B2
Application number	US-202117154925-A
Country	US
Kind code	B2
Filing date	Jan 21, 2021
Priority date	Mar 15, 2017
Publication date	Mar 19, 2024
Grant date	Mar 19, 2024

Abstract

A compound helicopter includes a fuselage including a fuselage airframe, a translational thrust system coupled to the fuselage airframe and a pylon assembly subject to vibration. The pylon assembly includes a transmission and a rotor system having a main rotor assembly. The compound helicopter also includes a main rotor vibration isolation system including a plurality of augmented liquid inertia vibration eliminator units each having an isolation frequency and each coupled between the fuselage airframe and the pylon assembly to reduce transmission of the pylon assembly vibration to the fuselage airframe at the isolation frequency. Each augmented liquid inertia vibration eliminator unit includes at least one active tuning element movable to tune the isolation frequency thereof.

First claim

What is claimed is:

1. A compound helicopter comprising:
a fuselage including a fuselage airframe;
a translational thrust system coupled to the fuselage airframe;
a pylon assembly subject to vibration, the pylon assembly including a transmission and a rotor system having a main rotor assembly;
a main rotor vibration isolation system including a plurality of augmented liquid inertia vibration eliminator units each having an isolation frequency and each coupled between the fuselage airframe and the pylon assembly to reduce transmission of the pylon assembly vibration to the fuselage airframe at the isolation frequency, each augmented liquid inertia vibration eliminator unit including at least one active tuning element movable to tune the isolation frequency thereof;
a wing subject to rotorwash-induced vibration from the main rotor assembly, the wing including a wing airframe; and
a wing vibration isolation system including a plurality of links coupled between the wing airframe and the fuselage airframe, each link including a liquid inertia vibration eliminator unit configured to reduce transmission of the rotorwash-induced wing vibration to the fuselage airframe, the plurality of links comprising a plurality of parallel and vertically-oriented links including at least one left link and at least one right link and at least one diagonally-oriented lateral link interposed between the at least one left link and the at least one right link.

2. The compound helicopter as recited in claim 1 further comprising a tailboom extending from the fuselage, the tailboom having an aft portion;
wherein, the translational thrust system includes a pusher propeller rotatably coupled to the aft portion of the tailboom.

3. The compound helicopter as recited in claim 1 wherein the main rotor assembly further comprises a dual rotor system having coaxially disposed top and bottom rotor assemblies that counter rotate relative to one another.

4. The compound helicopter as recited in claim 1 wherein the rotor system includes a plurality of rotor blades and the pylon assembly includes a pitch control assembly to adjust a pitch of the rotor blades; and
wherein, the pitch control assembly is operatively decoupled from the pylon assembly such that the pylon assembly vibration is independent of the pitch of the rotor blades.

5. The compound helicopter as recited in claim 1 wherein the main rotor vibration isolation system further comprises one or more supplementary vibration management devices including one or more devices selected from the group consisting of a Frahm, an active hub shaker, an active force generator, a pendulum and a hub active vibration control system.

6. The compound helicopter as recited in claim 1 wherein the main rotor vibration isolation system further comprises a four corner pylon mount structural assembly, the plurality of augmented liquid inertia vibration eliminator units comprising four augmented liquid inertia vibration eliminator units each positioned at one of the four corners of the pylon mount structural assembly;
wherein, the main rotor vibration isolation system further comprises first and second pylon structures, the plurality of augmented liquid inertia vibration eliminator units coupled to the pylon assembly via the first and second pylon structures; and
wherein, the plurality of augmented liquid inertia vibration eliminator units comprises a plurality of parallel and vertically-oriented augmented liquid inertia vibration eliminator units.

7. The compound helicopter as recited in claim 1 wherein the active tuning elements are configured to change the isolation frequencies of the augmented liquid inertia vibration eliminator units based on a rotational speed of the main rotor assembly; and
wherein, the active tuning elements each comprise a piezoelectric tuning element.

8. The compound helicopter as recited in claim 1 wherein the wing vibration isolation system further comprises one or more supplementary vibration management devices including one or more devices selected from the group consisting of a Frahm, an active hub shaker, an active force generator, a pendulum and a hub active vibration control system.

9. The compound helicopter as recited in claim 1 wherein each liquid inertia vibration eliminator unit of the wing vibration isolation system comprises at least one liquid inertia vibration eliminator unit selected from the group consisting of a passive liquid inertia vibration eliminator unit and an active liquid inertia vibration eliminator unit.

10. The compound helicopter as recited in claim 1 wherein the wing airframe includes one or more spars; and
wherein, each link of the wing vibration isolation system is coupled between one of the spars and the fuselage airframe.

11. The compound helicopter as recited in claim 10 wherein the one or more spars include front and aft spars;
wherein, the plurality of parallel and vertically-oriented links comprises a plurality of front links coupled between the front spar and the fuselage airframe and a plurality of aft links coupled between the aft spar and the fuselage airframe; and
wherein, the plurality of links further comprises a plurality of diagonally-oriented links between the front links and the aft links.

12. The compound helicopter as recited in claim 10 wherein the fuselage airframe includes left and right support beams;
wherein, the at least one left link is coupled between the left support beam and the one or more spars and the at least one right link is coupled between the right support beam and the one or more spars.

13. The compound helicopter as recited in claim 12 wherein the at least one diagonally-oriented lateral link has a length equal to or greater than a distance between the left and right support beams.

14. The compound helicopter as recited in claim 1 wherein the at least one diagonally-oriented lateral link is coupled to one of the top end or bottom end of the at least one left link and to the other of the top end or bottom end of the at least one right link.

15. The compound helicopter as recited in claim 1 wherein the at least one diagonally-oriented lateral link spans a width of the fuselage.

16. The compound helicopter as recited in claim 1 wherein each liquid inertia vibration eliminator unit of the wing vibration isolation system comprises an augmented liquid inertia vibration eliminator unit.

17. The compound helicopter as recited in claim 16 further comprising a vibration control computer in communication with a plurality of vibration feedback sensors and each augmented liquid inertia vibration eliminator unit of the wing vibration isolation system;
wherein, the vibration feedback sensors are coupled to the wing and detect the rotorwash-induced wing vibration from the main rotor assembly; and
wherein, the vibration control computer changes the isolation frequencies of the augmented liquid inertia vibration eliminator units of the wing vibration isolation system based on the rotorwash-induced wing vibration detected by the vibration feedback sensors.

Assignees

• Textron Innovations Inc

Inventors

• Stamps Frank Bradley
• Smith Michael Reaugh
• Passe Bradley Joseph

Classifications

• B64C1/065

  Spars · CPC title

• B64C27/10

  arranged coaxially · CPC title

• B64C27/001 Primary

  Vibration damping devices · CPC title

• B64C27/22

  Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft · CPC title

• B64C27/26

  characterised by provision of fixed wings · CPC title