RAT ACTUATOR FINE ADJUSTMENT ASSEMBLY

• US 20130292509A1
• Filed: 05/01/2012
• Published: 11/07/2013
• Est. Priority Date: 05/01/2012
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Original Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Inventors: Russ, David Everett, Sasscer, Gary
• Granted Patent: US 9,714,098 B2
• Time in Patent Office: Days
• US Class Current: 244/58
• CPC Class Codes: B64D 41/007 Ram air turbines
• CPC Class Codes: F16H 2025/2059 Superposing movement by two screws, e.g. with opposite thread direction
• CPC Class Codes: Y10T 74/18576 including screw and nut
• CPC Class Codes: Y10T 74/18704 Means to selectively lock or retard screw or nut

Abstract

A ram air turbine system includes an actuator having a threaded portion, a rod having a threaded region at or near one end and an eyelet at an opposite end, and a bushing. The bushing has a first thread engaged with the threaded portion of the actuator, and a second thread engaged with the threaded region of the rod, such that an actuation force can be transmitted between the actuator and the rod through the bushing. The first and second threads of the bushing have different pitches.

Claims

1. A ram air turbine system comprising:

an actuator having a threaded portion;

a rod having a threaded region at or near one end and an eyelet at an opposite end; and

a bushing having a first thread engaged with the threaded portion of the actuator, and a second thread engaged with the threaded region of the rod, such that an actuation force can be transmitted between the actuator and the rod through the bushing, wherein the first and second threads of the bushing have different pitches.

2. The system of claim 1, wherein the first thread of the bushing has a coarse pitch, and wherein the second thread of the bushing has a fine pitch such that length adjustment is possible to approximately 25.4 μ

m (0.001 inch) increments through rotation of the bushing.

3. The system of claim 1, wherein the first thread of the bushing is an internal thread.

4. The system of claim 1, wherein the first thread of the bushing is an external thread.

5. The system of claim 4, wherein the second thread of the bushing is an internal thread.

6. The system of claim 1, wherein the second thread of the bushing is an internal thread, and wherein the first thread is selected from the group consisting of an internal thread and an external thread.

7. The system of claim 1 and further comprising:

a first rotational locking device engaged between the actuator and the bushing.

8. The system of claim 7 and further comprising:

a second rotational locking device engaged between the bushing and the rod.

9. A method for use with an actuator assembly for a ram air turbine, the method comprising:

providing a rod;

providing a cylinder; and

operably engaging a threaded bushing between the rod and the cylinder such that the rushing is rotatable relate to both the rod and the cylinder.

10. The method of claim 9 and further comprising:

securing at least one locking device to limit rotational movement of the bushing.

11. The method of claim 9 and further comprising:

measuring a clearance distance between a portion of the ram air turbine and an airframe element when the ram air turbine is stowed; and

threadably adjusting a bushing to adjust the clearance distance while the actuator remains engaged.

12. The method of claim 9, wherein the step of threadably adjusting the bushing accomplishes fine adjustment after coarse adjustment has previously been completed.

13. The method of claim 9, wherein, during the step of threadably adjusting the bushing, a rod member of the actuator assembly having an eyelet at one end and a threaded engagement to the bushing at an opposite end is held rotationally fixed.

14. The method of claim 13, wherein, during the step of threadably adjusting the bushing, an actuator cylinder having a threaded engagement to the bushing is held rotationally fixed.

15. A ram air turbine system carried relative to an airframe element, the system comprising:

a deployable turbine assembly having a turbine supported by a strut;

an actuator cylinder having a threaded portion and a spring;

a rod having a threaded region at or near one end and an eyelet at an opposite end; and

a bushing having a first thread engaged with the threaded portion of the actuator, and a second thread engaged with the threaded region of the rod, such that an actuation force can be transmitted between the actuator and the rod through the bushing, wherein the first thread of the bushing has a coarse pitch, wherein the second thread of the bushing has a fine pitch, and wherein the bushing is rotatably adjustable while the rod and the threaded portion of the actuator cylinder are rotationally stationary.

16. The system of claim 15, wherein the first thread of the bushing is an internal thread.

17. The system of claim 15, wherein the first thread of the bushing is an external thread.

18. The system of claim 17, wherein the second thread of the bushing is an internal thread.

19. The system of claim 15, wherein the second thread of the bushing is an internal thread, and wherein the first thread is selected from the group consisting of an internal thread and an external thread.

20. The system of claim 15 and further comprising:

a first locking device engaged between the actuator cylinder and the bushing; and

a second locking device engaged between the bushing and the rod.