Helicopter transmission mount system

Patent metadata

Field	Value
Publication number	US-9254914-B2
Application number	US-201314086446-A
Country	US
Kind code	B2
Filing date	Nov 21, 2013
Priority date	Nov 21, 2013
Publication date	Feb 9, 2016
Grant date	Feb 9, 2016

Abstract

A restraint system for a transmission in an aircraft can include a first strut having a first fluid chamber, a first piston resiliently coupled to a first housing with a first elastomeric member. The restraint system can include a second strut having second fluid chamber, a second piston resiliently coupled to a second housing with a second elastomeric member. The restraint system can include a fluid line between the first fluid chamber and the second fluid chamber. The first strut and the second strut collectively provide not only torque restraint, but also torque measurement and fore/aft vibration isolation.

First claim

The invention claimed is:

1. An Aircraft transmission restraint system, wherein the restraint system comprising: a first strut having a first piston resiliently coupled to a first housing with a first elastomeric member, wherein the first housing, the first piston, and the first elastomeric member form a first fluid chamber; a second strut having a second piston resiliently coupled to a second housing with a second elastomeric member, wherein the second housing, the second piston, and the second elastomeric member form a second fluid chamber; a fluid line placing the first fluid chamber and the second fluid chamber in fluid communication; a fluid in the first fluid chamber, the second fluid chamber, and the fluid line; wherein an actuation of the first piston and the second piston in a first direction causes a portion of the fluid to move into one of the first fluid chamber and the second fluid chamber.

2. The restraint system according to claim 1 , wherein a first load on the first piston in the first direction, and a second load on the second piston in an opposite direction from the first direction causes a fluid lock.

3. The restraint system according to claim 2 , wherein the fluid lock acts to prevent the first piston from translating relative to the first housing.

4. The restraint system according to claim 2 , wherein the fluid lock acts to prevent the second piston from translating relative to the second housing.

5. The restraint system according to claim 1 , wherein the first strut is oriented parallel to the second strut.

6. The restraint system according to claim 1 , wherein the first piston and the second piston are coupled to an airframe of the aircraft.

7. The restraint system according to claim 1 , wherein the first housing and the second housing are coupled to the transmission.

8. The restraint system according to claim 1 , wherein the first piston and the second piston are oriented parallel to a longitudinal axis of the aircraft.

9. The restraint system according to claim 1 , further comprising:
a pressure sensor configured to measure a pressure of the fluid.

10. The restraint system according to claim 9 , wherein the pressure sensor is configured to provide a measurement of torque experienced by the transmission.

11. The restraint system according to claim 1 , wherein the aircraft is a helicopter.

12. The restraint system according to claim 1 , wherein the transmission is coupled to a main rotor mast of a rotor hub.

13. The restraint system according to claim 1 , wherein the portion of fluid that moves into one of the first fluid chamber and the second fluid chamber has an inertial mass that cancels a force that actuates the first piston and the second piston.

14. An Aircraft transmission restraint system, wherein the restraint system comprising: a first strut having a first piston resiliently coupled to a first housing with a first elastomeric member, wherein the first housing, the first piston, and the first elastomeric member form a first fluid chamber; a second strut having a second piston resiliently coupled to a second housing with a second elastomeric member, wherein the second housing, the second piston, and the second elastomeric member form a second fluid chamber; a fluid line between the first fluid chamber and the second fluid chamber; and a fluid in the first fluid chamber, the second fluid chamber, and the fluid line; wherein a first load on the first piston in a first direction, and a second load on the second piston in an opposite direction from the first direction, causes a fluid lock.

15. The restraint system according to claim 14 , wherein the fluid lock causes the first strut and the second strut to behave rigidly.

16. The restraint system according to claim 14 , wherein the first load and the second load are generated from a torque load on the transmission.

17. The restraint system according to claim 14 , further comprising:
a pressure sensor configured to measure a fluid pressure of the fluid.

18. The restraint system according to claim 14 , wherein the first piston and the second piston are coupled to an airframe of the aircraft.

19. The restraint system according to claim 14 , wherein the first housing and the second housing are coupled to the transmission.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Hendricks Matthew W
• Griffin Maurice D
• Smith Michael R
• Lee Taeoh

Classifications

• B64C2027/002

  mounted between the rotor drive and the fuselage · CPC title

• B64C2027/004

  using actuators, e.g. active systems · CPC title

• B64C27/001 Primary

  Vibration damping devices · CPC title

• F16F15/10

  Suppression of vibrations in rotating systems by making use of members moving with the system (by balancing F16F15/22 {; yielding couplings F16D3/00} ; with flywheels acting variably or intermittently F16H {; construction providing resilience or vibration-damping for gear elements F16H55/14}) · CPC title