Rotorcraft vibration suppression system in a four corner pylon mount configuration

Patent metadata

Field	Value
Publication number	US-10330166-B2
Application number	US-201715723510-A
Country	US
Kind code	B2
Filing date	Oct 3, 2017
Priority date	Jan 10, 2012
Publication date	Jun 25, 2019
Grant date	Jun 25, 2019

Abstract

The vibration suppression system includes a vibration isolator located in each corner in a four corner pylon mount structural assembly. The combination of four vibration isolators, two being forward of the transmission, and two being aft of the transmission, collectively are effective at isolating main rotor vertical shear, pitch moment, as well as roll moment induced vibrations. Each opposing pair of vibration isolators can efficiently react against the moment oscillations because the moment can be decomposed into two antagonistic vertical oscillations at each vibration isolator. A pylon structure extends between a pair of vibration isolators thereby allowing the vibration isolators to be spaced a away from a vibrating body to provide increased control.

First claim

The invention claimed is:

1. A vibration suppression system for an aircraft, comprising:
a pylon mount structural assembly configured to control pitch and roll dynamics of a vibrating body within the aircraft, the pylon mount structural assembly having a pylon structure configured to support the vibrating body at a point of coupling; and
a vibration isolator located at each end of the pylon structure to control the transmission of vibrations through the aircraft, the vibration isolator being spaced away from the vibrating body, the vibration isolator having;
a piston spindle resiliently coupled to an upper housing with an upper elastomer member, the piston spindle being resiliently coupled to a lower housing with a lower elastomer member; and
a spherical bearing assembly having an attachment member, the spherical bearing assembly is located at least partially around the lower housing for coupling to the pylon structure;
wherein the spherical bearing assembly is configured to compensate for misalignment in loading between the pylon mount structural assembly and the vibrating body.

2. The vibration suppression system according to claim 1 , wherein the pylon structure is conformed to locate the point of coupling inboard of the vibration isolator.

3. The vibration suppression system according to claim 1 , wherein the pylon structure is located above a roof beam.

4. The vibration suppression system according to claim 1 , wherein the vibration isolator is spaced away from the vibrating body to be at least one of forward of the vibrating body and aft of the vibrating body.

5. The vibration suppression system according to claim 1 , wherein the pylon structure is configured to correlate the motion of the vibrating body by suspending a portion of the vibrating body between a plurality of vibration isolators along the pylon mount.

6. The vibration suppression system according to claim 1 , the spherical bearing assembly further comprising:
a spherical elastomeric member having;
an elastomeric material bonded between a non-resilient concave member and a non-resilient convex member.

7. The vibration isolator according to claim 1 , wherein the spherical bearing assembly is located to have a waterline location equal to a waterline location of a driveshaft axis.

8. The vibration isolator according to claim 1 , wherein the piston spindle is configured for coupling to the vibrating body.

9. The vibration isolator according to claim 1 , wherein the piston spindle is configured for coupling to a pylon assembly of an aircraft.

10. The vibration isolator according to claim 1 , wherein the spherical bearing assembly is configured for coupling to a roof structure of an aircraft.

11. The vibration isolator according to claim 1 , wherein the vibrating body is at least one of an aircraft engine, an aircraft transmission, an aircraft propeller, or an aircraft rotor.

12. The vibration isolator according to claim 1 , further comprising:
a vibration control system configured to detect and convey vibration data through a plurality of feedback sensors to regulate an isolation frequency of at least one vibration isolator.

13. A vibration suppression system for an aircraft, comprising:
a pylon mount structural assembly configured to control pitch and roll dynamics of a vibrating body within the aircraft, the pylon mount structural assembly having a pylon structure configured to support the vibrating body at a point of coupling; and
a vibration isolator located at each end of the pylon structure to control the transmission of vibrations through the aircraft, the vibration isolator being spaced away from the vibrating body, the vibration isolator having;
a piston spindle resiliently coupled to an upper housing with an upper elastomer member, the piston spindle being resiliently coupled to a lower housing with a lower elastomer member; and
a spherical bearing assembly having;
an attachment member; and
a spherical elastomeric member having;
an elastomeric material bonded between a non-resilient concave member and a non-resilient convex member;

wherein the spherical bearing assembly is located at least partially around the lower housing for coupling to the pylon structure;
wherein the spherical bearing assembly is configured to compensate for misalignment in loading between the pylon mount structural assembly and the
vibrating body; and
wherein the pylon structure is conformed to locate the point of coupling inboard of the vibration isolator.

14. The vibration isolator according to claim 13 , wherein the piston spindle is configured for coupling to the vibrating body.

15. The vibration isolator according to claim 13 , wherein the piston spindle is configured for coupling to a pylon assembly of an aircraft.

16. The vibration isolator according to claim 13 , wherein the spherical bearing assembly is configured for coupling to a roof structure of an aircraft.

17. The vibration isolator according to claim 13 , wherein the vibrating body is at least one of an aircraft engine, an aircraft transmission, an aircraft propeller, or an aircraft rotor.

18. A vibration suppression system for an aircraft, comprising:
a pylon mount structural assembly configured to control pitch and roll dynamics of a vibrating body within the aircraft, the pylon mount structural assembly having a pylon structure configured to support the vibrating body at a point of coupling; and
a vibration isolator located at each end of the pylon structure to control the transmission of vibrations through the aircraft, the vibration isolator being spaced away from the vibrating body, the vibration isolator having;
a piston spindle resiliently coupled to an upper housing with an upper elastomer member, the piston spindle being resiliently coupled to a lower housing with a lower elastomer member; and
a spherical bearing assembly having;
an attachment member; and
a spherical elastomeric member having;
an elastomeric material bonded between a non-resilient concave member and a non-resilient convex member;

wherein the spherical bearing assembly is located to have a waterline location equal to a waterline location of a driveshaft axis;
wherein the spherical bearing assembly is located at least partially around the lower housing for coupling to the pylon structure;
wherein the spherical bearing assembly is configured to compensate for misalignment in loading between the pylon mount structural assembly and the
vibrating body; and
wherein the pylon structure is conformed to locate the point of coupling inboard of the vibration isolator.

19. The vibration suppression system according to claim 18 , wherein the vibration isolator is spaced away from the vibrating body to be at least one of forward of the vibrating body and aft of the vibrating body.

20. The vibration suppression system according to claim 18 , wherein the pylon structure is configured to correlate the motion of the vibrating body by suspending a portion of the vibrating body between a plurality of vibration isolators along the pylon mount.

Assignees

• Textron Innovations Inc

Inventors

• Lee Taeoh
• Heverly Ii David E
• Hendricks Matthew W
• Griffin Maurice
• Smith Michael R

Classifications

• B64C27/001 Primary

  Vibration damping devices · CPC title

• B64C2027/002

  mounted between the rotor drive and the fuselage · CPC title

• F16F13/24

  the central part of the unit being supported by one element and both extremities of the unit being supported by a single other element, i.e. double acting mounting · CPC title

• F16F7/00 Primary

  Vibration-dampers; Shock-absorbers (using fluid F16F5/00, F16F9/00; specific for rotary systems F16F15/10 {; belt tensioners F16H7/12}) · CPC title