Weight efficient servo attachment scheme for rigid coaxial rotor control system

Patent metadata

Field	Value
Publication number	US-2016200432-A1
Application number	US-201414915151-A
Country	US
Kind code	A1
Filing date	Aug 7, 2014
Priority date	Aug 28, 2013
Publication date	Jul 14, 2016
Grant date	—

Abstract

A mounting assembly for connecting a first surface to a second surface and for holding a first servo which moves an adjacent first component is provided including a leg. A first end of the leg is attachable to the first surface and a second end of the leg is attachable to the second surface. The leg is generally bent such that the first end of each leg is arranged at an angle to the second end of each leg so as to transmit forces between the first and second surface. A bracket connected to the leg includes a notch configured to receive the first servo. When the first servo is positioned within the first notch, a free end of the first servo is operably coupled to the adjacent first component and the leg reacts forces generated by the first servo into the first and second surfaces.

First claim

What is claimed is:

1 . A mounting assembly for connecting a first surface to a second surface and holding a first servo which moves an adjacent first component, the mounting assembly comprising:
a leg having a first end attachable to the first surface and a second end attachable to the second surface, the leg being generally bent such that the first end of each leg is arranged at an angle to the second end of each leg so as to transmit forces between the first and second surface; and a bracket connected to the leg and including a notch configured to receive the first servo, wherein when the first servo is positioned within the first notch, a free end of the first servo is operably coupled to the adjacent first component and the leg reacts forces generated by the first servo into the first and second surfaces.

2 . The mounting assembly according to claim 1 , wherein the first end of the leg is shaped to be coupled to a cylindrical sleeve arranged about a rotating shaft.

3 . The mounting assembly according to claim 2 , further comprising additional legs, wherein the leg and the additional legs are spaced equidistantly about the cylindrical sleeve.

4 . The mounting assembly according to claim 1 , wherein the second end of the leg is configured to couple to an airframe of a rotary wing aircraft.

5 . The mounting assembly according to claim 1 , wherein each bracket further comprises a second notch configured to receive a second servo.

6 . The mounting assembly according to claim 5 , wherein when the second servo is positioned within the second notch, a free end of the second servo is operably coupled to an adjacent second component.

7 . The mounting assembly according to claim 6 , wherein the adjacent first component comprises a first stationary swashplate, and the free end of the first servo is operably coupled to the first stationary swashplate and the adjacent second component comprises a second stationary swashplate, and the free end of the second servo is operably coupled to the second stationary swashplate.

8 . A mounting assembly for connecting a first surface to a second surface, the mounting assembly comprising:
a leg having a first end attachable to the first surface and a second end attachable to the second surface, the leg being generally bent such that the first end of each leg is arranged at an angle to the second end of each leg so as to transmit forces between the first and second surface; and a rib extending from the leg near the second end thereof, the rib being configured to connect to and support a portion of an active vibration control system.

9 . The mounting assembly according to claim 8 , wherein the portion of the active vibration control system includes at least one force generator.

10 . The mounting assembly according to claim 8 , wherein the rib is integrally formed with the leg.

11 . A rotary wing aircraft, comprising:
an airframe; a main rotor system configured to rotate about a first axis of rotation; a first stationary swashplate operably coupled to at least one first blade of the main rotor system; and a mounting assembly configured to transfer loads from the main rotor system to the airframe, the mounting assembly including:
a first leg having a first end and a second end, the first end of the first leg being coupled to the main rotor system, and the second end of the first leg being connected to the airframe; and
a bracket being integrally formed with the first leg and including a first notch configured to receive a first servo, wherein a free end of the first servo is operably coupled to the first stationary swashplate.

12 . The rotary wing aircraft according to claim 11 , wherein operation of the first servo adjusts a pitch of the at least one first blade via the first stationary swashplate.

13 . The rotary wing aircraft according to claim 11 , further comprising:
a second stationary swashplate operably coupled to at least one second blade of the main rotor system, wherein the bracket further comprises a second notch configured to receive a second servo such that a free end of the second servo is operably coupled to the second stationary swashplate, and operation of the second servo adjusts a pitch of the at least one second blade via the second stationary swashplate.

14 . The rotary wing aircraft according to claim 11 , wherein a portion of an active vibration control system is mounted to the first leg of the mounting assembly.

15 . The rotary wing aircraft according to claim 14 , wherein the portion of the active vibration control system includes at least one force generator mounted to the leg.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Darrow Jr David A
• Poulin Stephen V
• Mayrides Bryan D

Classifications

• B64C2027/004

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

• B64C27/001

  Vibration damping devices · CPC title

• B64C27/10 Primary

  arranged coaxially · CPC title

• B64C27/32 Primary

  Rotors · CPC title

• B64C2027/002

  mounted between the rotor drive and the fuselage · CPC title