Adjustable blade-to-hub lead-lag damper attachment

Patent metadata

Field	Value
Publication number	US-10532810-B2
Application number	US-201715603119-A
Country	US
Kind code	B2
Filing date	May 23, 2017
Priority date	May 21, 2014
Publication date	Jan 14, 2020
Grant date	Jan 14, 2020

Abstract

An aircraft includes a rotor blade and a rotor hub system. The rotor hub system includes a lead-lag damper having a rod end and being operably associated with the rotor blade; a blade adapter having a first arm and an opposing second arm; a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm.

First claim

What is claimed is:

1. A rotor hub system for an aircraft, comprising:
a lead-lag damper operably associated with a rotor blade of the aircraft;
a blade adapter, having:
a first arm and an opposing second arm;

a pin carried by the blade adapter and secured in position via the first arm and the second arm, the pin supporting a rod end of the lead-lag damper; and
a first interchangeable spacer and a second interchangeable spacer, both spacers being configured to receive the pin therethrough and configured to retain the rod end of the lead-lag damper secured to the pin at a selected distance relative to the first arm and second arm;
wherein the pin is a telescoping pin; and
wherein translation of the telescoping pin causes translation of the rod end between the first arm and the second arm.

2. The system of claim 1 , wherein the first spacer and the second spacer each have a longitudinal length; and wherein the longitudinal length of the first spacer is less than the longitudinal length of the second spacer, thus retaining the rod end at a non-equal distance between the first arm and the second arm.

3. The system of claim 1 , wherein the first spacer and the second spacer each have a longitudinal length; and wherein the longitudinal length of the first spacer is equal to the longitudinal length of the second spacer, thus retaining the rod end at an equal distance between the first arm and the second arm.

4. The system of claim 1 , wherein the rotor hub system is an articulate rotor hub system.

5. The system of claim 4 , wherein the articulated rotor hub system is a soft-in-plane assembly.

6. The system of claim 1 , wherein the rotor hub system is operably associated with at least three rotor blades.

7. An aircraft, comprising:
a rotor blade; and
a rotor hub system, having:
a lead-lag damper having a rod end and being operably associated with the rotor blade;
a blade adapter, having:
a first arm and an opposing second arm;

a pin carried by the blade adapter and secured in position via the first arm and the second arm, the pin supporting a rod end of the lead-lag damper;
an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm; and
a first spacer and a second spacer, both spacers being configured to receive the pin therethrough and configured to retain the rod end of the lead-lag damper secured to the pin at a selected distance relative to the first arm and second arm.

8. The aircraft of claim 7 , wherein the aircraft is a helicopter.

9. The aircraft of claim 7 , wherein the rotor hub system is an articulate rotor hub system.

10. The aircraft of claim 9 , wherein the articulated rotor hub system is a soft-in-plane assembly.

11. The aircraft of claim 7 , wherein the rotor hub system is operably associated with at least three rotor blades.

12. The aircraft of claim 7 , wherein the actuator is autonomously controlled.

13. A method to increase flight performance of an aircraft, comprising:
providing the aircraft of claim 7 ; and
adjusting the position of the rod end relative to the first arm and the second arm via an actuator.

14. The method of claim 13 , further comprising;
autonomously controlling the adjustment of the rod end.

15. The method of claim 13 , wherein the pin is a threaded helical pin;
wherein the process of adjusting the position of the rod end is achieved via the threaded helical pin operably associated with the rod end of the actuator.

16. The method of claim 15 , wherein the actuator rotates the helical threaded rod.

17. The method of claim 13 , wherein the pin is a telescoping pin;
wherein the process of adjusting the position of the rod end is achieved via the telescoping pin operably associated with the rod end and the actuator.

18. The method of claim 17 , wherein the actuator translates the telescoping pin.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Rauber Richard E
• Yuce Mithat
• Parham Jr Thomas C
• Newman Thomas J
• Wiinikka Mark A

Classifications

• F16C23/02

  Sliding-contact bearings · CPC title

• F16C11/0614

  the female part of the joint being open on two sides · CPC title

• B64C27/51

  Damping of blade movements · CPC title

• F16C2326/43

  Aeroplanes; Helicopters · CPC title

• F16C11/0695

  Mounting of ball-joints, e.g. fixing them to a connecting rod · CPC title