Electromechanically controlled decoupling device for actuators

Patent metadata

Field	Value
Publication number	US-9506543-B2
Application number	US-201414469321-A
Country	US
Kind code	B2
Filing date	Aug 26, 2014
Priority date	Aug 27, 2013
Publication date	Nov 29, 2016
Grant date	Nov 29, 2016

Abstract

An aircraft includes an electromechanical actuator and a decoupling device. A form-fit between a drive element and a linkage point outside of the actuator element can be reversibly decoupled and recoupled. The decoupling device allows the actuator element to run freely in the event of a malfunction, which effectively prevents a jam.

First claim

What is claimed is:

1. An actuator element, comprising:
a drive unit, having a first drive element and a second drive element, wherein the first drive element and the second drive element are arranged to functionally interact in such a manner to effect a change in length of the actuator element;
a decoupling device;
two linkage points having a span extending from one to the other of the two linkage points, wherein one of the drive elements is connected to one of the two linkage points;
an output piston connected to the other one of the two linkage points,
wherein the span of the two linkage points in a coupled state of the decoupling device is adjustable by driving one of the first and second drive element, and
wherein the span of the two linkage points in a decoupled state of the decoupling device is adjustable by application of an external force on one of the two linkage points,
wherein the decoupling device comprises
a motor, a plurality of ball elements, and a sleeve element with recesses,
wherein the motor is arranged to move the sleeve element between a first position and a second position,
wherein the sleeve element is coupled with the output piston in the first position by retaining the plurality of ball elements in corresponding recesses in the output piston, and
wherein the sleeve element is decoupled from the output piston in the second position by accommodating the plurality of ball elements in the recesses of the sleeve element.

2. The actuator element of claim 1 , wherein the drive unit is a spindle drive, a ball screw drive, a planetary roller drive, or a trapeze screw drive.

3. The actuator element of claim 2 , wherein the first drive element is a hollow spindle and the output piston is arranged inside a hollow space of the hollow spindle.

4. The actuator element of claim 3 , wherein
the output shaft is freely displaceable inside the hollow spindle in the second position of the sleeve element.

5. The actuator element of claim 1 , wherein the first drive element and the second drive element are a ball spindle and ball nut of a ball screw drive.

6. The actuator element of claim 5 , further comprising:
a motor element,
wherein the ball nut is rotatable using the motor element, wherein a translation of the ball spindle changes the length of the actuator element.

7. The actuator element of claim 6 , wherein translation of the first drive element causes a translation of the output piston when the sleeve element is in the first position.

8. The actuator element of claim 1 , wherein
the sleeve element is rotatable using the drive unit.

9. The actuator element of claim 1 , further comprising:
a housing; and
a sealing element arrangement arranged in such a manner that a region of the plurality of ball elements, sleeve element, output piston and housing are constructed in a seal-tight manner and the region is filled with a lubricant.

10. The actuator element of claim 9 , further comprising:
rod seals, wherein the rod seals provide a seal for the lubricant during a test of the actuator element.

11. The actuator element of claim 9 , wherein one of the two linkage points is arranged on one end of the housing of the actuator element and the other linkage point is arranged on an external end of the output piston.

12. The actuator element of claim 1 , wherein
the decoupling device is arranged so that it can be decoupled in the course of a test; and
the decoupling device is arranged so that it can be re-coupled after completion of the test without disassembling the actuator element.

13. The actuator element of claim 1 , wherein conductive connections between the decoupling device and an aircraft are provided solely to a stationary part of the decoupling device so that a movement of a movable part of the decoupling device does not require any movability of the conductive connection.

14. An actuator arrangement, comprising:
at least two actuator elements, each of the at least two actuator elements comprising
a drive unit, having a first drive element and a second drive element, wherein the first drive element and the second drive element are arranged to functionally interact in such a manner to effect a change in length of the actuator element;
a decoupling device;
two linkage points having a span extending from one to the other of the two linkage points, wherein one of the drive elements is connected to one of the two linkage points;
an output piston connected to the other one of the two linkage points,
wherein the span of the two linkage points in a coupled state of the decoupling device is adjustable by driving one of the first and second drive element, and
wherein the span of the two linkage points in a decoupled state of the decoupling device is adjustable by application of an external force on one of the two linkage points,
wherein the decoupling device comprises
a motor, a plurality of ball elements, and a sleeve element with recesses,
wherein the motor is arranged to move the sleeve element between a first position and a second position;
wherein the sleeve element is coupled with the output piston in the first position by retaining the plurality of ball elements in corresponding recesses in the output piston,
wherein the sleeve element is decoupled from the output piston in the second position by accommodating the plurality of ball elements in the recesses of the sleeve element, and

wherein the at least two actuator elements are arranged in a force-parallel manner so that a length change of the actuator arrangement can be effected by one actuator element alone or by both actuator elements at the same time.

15. The actuator arrangement of claim 14 , wherein in event of a defect of a drive unit of one of the two actuator elements, the decoupling device triggers the decoupling mechanism of the actuator element having a defect so that the actuator element is functionally decoupled and the length change of the actuator arrangement continues to be affected by the non-decoupled actuator element.

16. An aircraft, comprising:
an aerodynamically active element, which is driven by an actuator element comprising
a drive unit, having a first drive element and a second drive element, wherein the first drive element and the second drive element are arranged to functionally interact in such a manner to effect a change in length of the actuator element;
a decoupling device;
two linkage points having a span extending from one to the other of the two linkage points, wherein one of the drive elements is connected to one of the two linkage points;
an output piston connected to the other one of the two linkage points,
wherein the span of the two linkage points in a coupled state of the decoupling device is adjustable by driving one of the first and second drive element, and
wherein the span of the two linkage points in a decoupled state of the decoupling device is adjustable by application of an external force on one of the two linkage points,
wherein the decoupling device comprises
a motor, a plurality of ball elements, and a sleeve element with recesses
wherein the motor is arranged to move the sleeve element between a first position and a second position,
wherein the sleeve element is coupled with the output piston in the first position by retaining the plurality of ball elements in corresponding recesses in the output piston, and
wherein the sleeve element is decoupled from the output piston in the second position by accommodating the plurality of ball elements in the recesses of the sleeve element.

17. The aircraft of

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Naubert Alexander
• Christmann Markus

Classifications

• F16H2025/2081

  Parallel arrangement of drive motor to screw axis · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• B64C13/42

  having duplication or stand-by provisions · CPC title

• F16H25/2204

  with balls · CPC title

• F16H25/2025 Primary

  with means to disengage the nut or screw from their counterpart; Means for connecting screw and nut for stopping reciprocating movement (F16H25/2015 takes precedence) · CPC title