Helicopter transmission mount system

Patent metadata

Field	Value
Publication number	US-9365294-B2
Application number	US-201314086372-A
Country	US
Kind code	B2
Filing date	Nov 21, 2013
Priority date	Nov 21, 2013
Publication date	Jun 14, 2016
Grant date	Jun 14, 2016

Abstract

A mount system for supporting a transmission in an aircraft can include a first link coupled between a structure of the aircraft and the transmission, the first link having a first axis; a second link coupled between the structure of the aircraft and the transmission, the second link having second axis; a third link coupled between the structure of the aircraft and the transmission, the third link having a third axis; and a fourth link coupled between the structure of the aircraft and the transmission, the fourth link having fourth axis. A forward focal point of the first axis and the second axis has a different waterline component compared to an aft focal point of the third axis and the fourth axis.

First claim

The invention claimed is:

1. A mount system for supporting a transmission in an aircraft, the mount system comprising:
a first link coupled between a structure of the aircraft and the transmission, the first link having a first axis;
a second link coupled between the structure of the aircraft and the transmission, the second link having second axis;
a third link coupled between the structure of the aircraft and the transmission, the third link having a third axis;
a fourth link coupled between the structure of the aircraft and the transmission, the fourth link having fourth axis;
wherein the first link and the second link are oriented such that the first axis and the second axis intersect at a forward focal point;
wherein the third link and the fourth link are oriented such that the third axis and the fourth axis intersect at an aft focal point;
wherein the forward focal point has a different waterline location compared to the aft focal point;
wherein the first link and the second link are coupled to the transmission at different locations;
wherein the third link and the fourth link are coupled to the transmission at different locations; and
wherein the forward focal point and the aft focal point are located within an interior portion of the transmission so that a virtual roll axis extending between the forward focal point and the aft focal point passes through a portion of the transmission.

2. The mount system according to claim 1 , wherein the forward focal point has a lower waterline location compared to the aft focal point.

3. The mount system according to claim 1 , wherein the forward focal point lies on a zero buttline plane of the aircraft.

4. The mount system according to claim 1 , wherein the aft focal point lies on a zero buttline plane of the aircraft.

5. The mount system according to claim 1 , wherein the first link, the second link, the third link, and the fourth link are coupled to the transmission with a plurality of spherical bearings.

6. The mount system according to claim 1 , wherein the first link, the second link, the third link, and the fourth link are coupled to the airframe with a plurality of spherical bearings.

7. The mount system according to claim 1 , wherein the structure of the aircraft is a pylon assembly.

8. The mount system according to claim 1 , wherein the first link, the second link, the third link, and the fourth link having one or more moving parts for vibration attenuation.

9. The mount system according to claim 1 , wherein the first link, the second link, the third link, and the fourth link are configured such that the overall length can change during vibration attenuation.

10. The mount system according to claim 1 , further comprising:
a fifth link coupled between the structure of the aircraft and the transmission, the fifth link having a fifth axis that is approximately parallel with a longitudinal axis of the aircraft;
a sixth link coupled between the structure of the aircraft and the transmission, the sixth link having a sixth axis that is approximately parallel with the longitudinal axis of the aircraft.

11. The mount system according to claim 1 , further comprising:
a seventh link coupled between the structure of the aircraft and the transmission, the seventh link having a seventh axis that is approximately parallel with a lateral axis of the aircraft.

12. The mount system according to claim 1 , wherein the aircraft is a helicopter.

13. The mount system according to claim 1 , wherein the forward focal point has a fuselage station location that is forward to a fuselage station of the aft focal point by a longitudinal distance, and wherein a waterline location of the forward focal point is lower than a waterline location of the aft focal point by a vertical distance.

14. The mount system according to claim 13 , wherein the vertical distance is greater than the longitudinal distance.

15. The mount system according to claim 1 , wherein the forward focal point is separated from the aft focal point by a longitudinal distance as measured along a centerline longitudinal axis of the aircraft, and wherein the forward focal point is separated from the aft focal point by a vertical distance as measured along a vertical axis of the aircraft.

16. The mount system according to claim 15 , wherein the vertical distance is greater than the longitudinal distance.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Griffin Maurice D
• Hendricks Matthew W

Classifications

• B64C2027/004

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

• B64D35/00 Primary

  Transmitting power from power plants to propellers or rotors; Arrangements of transmissions · CPC title

• B64C2027/002

  mounted between the rotor drive and the fuselage · CPC title

• B64C27/001

  Vibration damping devices · CPC title