Actuator arrangement and control surface arrangement, especially for an aircraft

Patent metadata

Field	Value
Publication number	US-9631711-B2
Application number	US-201314107344-A
Country	US
Kind code	B2
Filing date	Dec 16, 2013
Priority date	Dec 17, 2012
Publication date	Apr 25, 2017
Grant date	Apr 25, 2017

Abstract

An improved actuator arrangement for operating a driven element with different actuators. The actuator arrangement comprises a first actuator that drives a driven element in a first direction via a first output member and a second actuator that drives the driven element in a second direction opposite to the first direction via a second output member. The first and second actuators are configured to work in a counter-acting manner to move the driven element in the first and second directions. An additional connecting and supporting device is connected between the first and second output members to support the output members to bear transversal forces transversal to the moving direction and/or to bear pre-load force for pre-loading the actuators.

First claim

What is claimed is:

1. An actuator arrangement comprising:
a first actuator configured to drive a driven element in a first direction via a first output member;
a second actuator configured to drive the driven element in a second direction opposite to the first direction via a second output member, such that the first and second actuators are configured to work in a counter-acting manner to move the driven element in the first and second directions; and
an additional connecting and supporting device connected between the first output member and the second output member and configured to support the output members and bear a pre-load force to pre-load the actuators.

2. The actuator arrangement according to claim 1 , further comprising
a biasing element configured to at least one of bias the connecting and supporting device into a neutral position and provide the pre-load forces.

3. The actuator arrangement according to claim 1 , wherein
the connecting and supporting device comprises at least one of
a connecting rod linked between the first and second output members; and
a lever element having a first and a second lever arm and a fulcrum point there between, the lever element being linked between the first and second output members.

4. The actuator arrangement according to claim 1 , wherein
the connecting and supporting device comprises a bearing configured to support a linkage linked between the second and first output members on a support base and to enable at least one of a relative pivoting and bending movement between the support base and the linkage.

5. The actuator arrangement according to claim 3 , wherein
at least one of a centre portion of the connecting rod and a center portion of the lever element is supported by the support bearing for at least one of a pivot and bending movement of the connecting rod or the lever element respectively.

6. The actuator arrangement according to claim 3 , wherein
the connecting rod is configured to bend during operation of at least one of the first and second actuators.

7. The actuator arrangement according to claim 1 , further comprising at least one of
a first link joint configured to connect the first output member and the connecting and supporting device so that they can pivot relative to each other; and
a second link joint configured to connect the second output member and the connecting and supporting device so that they can pivot relative to each other.

8. The actuator arrangement according to claim 1 , wherein
the first and second actuators are linked to the connecting and supporting device under compressive pre-load and the preload force is borne and supported by the connecting and supporting device.

9. The actuator arrangement according claim 1 , further comprising
an adjustment component configured to adjust a pre-load force to preload the first and second actuators.

10. The actuator arrangement according to claim 1 , wherein
the connecting and support device is arranged between the first and second actuators and the driven element.

11. The actuator arrangement according to claim 1 , further comprising
at least one of a housing and a frame configured as a support base to support the actuators and the connecting and support device.

12. The actuator arrangement according to claim 1 , further comprising
a first actuator system comprising a plurality of first actuators and second actuators linked together in a closed polygonal structure, and a first output member that is configured to connect to the driven element and is moveable in the first and second directions by the first and second actuators of the first actuator system; and
a second actuator system comprising a plurality of first actuators and second actuators linked together in a closed polygonal structure, and a second output member that is configured to connect to the driven element and is moveable in the first and second directions by the first and second actuators of the second actuator system.

13. A control surface arrangement for an aircraft, the control surface arrangement comprising
a control surface element and an actuator arrangement according to claim 1 , the actuator arrangement being configured to control movement of the control surface element that is configured as the driven element.

14. The control surface arrangement according to claim 13 , wherein
the control surface element is configured as a flap of a helicopter rotor blade.

15. The actuator arrangement according to claim 2 , wherein
the connecting and supporting device comprises at least one of
a connecting rod linked between the first and second output members; and
a lever element having a first and a second lever arm and a fulcrum point there between, the lever element being linked between the first and second output members.

16. The actuator arrangement according to claim 2 , wherein
the connecting and supporting device comprises a bearing configured to support a linkage linked between the second and first output members on a support base and to enable at least one of a relative pivoting and bending movement between the support base and the linkage.

17. The actuator arrangement according to claim 2 , further comprising at least one of
a first link joint configured to connect the first output member and the connecting and supporting device so that they can pivot relative to each other; and
a second link joint configured to connect the second output member and the connecting and supporting device so that they can pivot relative to each other.

18. The actuator arrangement according to claim 2 , wherein
the first and second actuators are linked to the connecting and supporting device under compressive pre-load and the preload force is borne and supported by the connecting and supporting device.

19. The actuator arrangement according claim 2 , further comprising
an adjustment component configured to adjust a pre-load force to preload the first and second actuators.

20. The actuator arrangement according to claim 2 , wherein
the connecting and support device is arranged between the first and second actuators and the driven element.

Assignees

• Storm Stefan
• Grohmann Boris
• Eads Deutschland Gmbh

Inventors

• Storm Stefan
• Grohmann Boris

Classifications

• B64C27/72

  Means acting on blades · CPC title

• Y10T74/18888

  Reciprocating to or from oscillating · CPC title

• B64C2027/7283

  of the piezoelectric type · CPC title

• B64C13/28

  mechanical · CPC title

• B64C27/615 Primary

  including flaps mounted on blades · CPC title