CN-110406656-B - Control surface actuation mechanism

Abstract

The present invention provides a control surface actuation mechanism for moving a control surface relative to a stationary airfoil portion of an aircraft. The control surface actuation mechanism includes a hinge support, a sliding member located on the hinge support and coupled to the control surface, the sliding member arranged to slide relative to the hinge support, a rail having a path for attachment to the stationary airfoil portion, and a rigid connection element connected to the first rail and to the sliding member. The first end of the first rigid connection element is configured to passively move along a path as the sliding member is driven by the actuator to slide relative to the hinge support.

Inventors

• Jason kuruvira
• Pradip gajakosh
• Akshay srinivasamesi
• Lakshmi lagawan bellol
• Samit Kumar Malik
• Gayatri swaminatan
• VINAYAK RAMACHANDRA PATIL
• Afniash Kumar Yadav

Assignees

• 空中客车简化股份公司

Dates

Publication Date

20260512

Application Date

20190425

Priority Date

20180427

Claims (15)

1. 1. A control surface actuation mechanism for moving a control surface relative to a stationary airfoil portion of an aircraft, the control surface actuation mechanism comprising: a hinge support for pivotal coupling to the stationary airfoil portion about a generally spanwise pivot axis; a sliding member having a proximal end mounted on the articulating support and having a distal end for coupling to the control surface, the sliding member being arranged to slide along a generally chordal axis relative to the articulating support; a first rail for attachment to the stationary airfoil portion and defining a first path, and A first rigid connection element connected at a first end to the first rail and at a second end to a fixed point on the sliding member, Wherein the first end of the first rigid connection element is configured to passively move along the first path as the sliding member is driven by an actuator to slide relative to the hinge support.
2. 2. The control surface actuation mechanism of claim 1, wherein the first rigid connection element is pivotally connected to the first rail at a first end.
3. 3. The control surface actuation mechanism of claim 1 or 2, wherein the first rigid connection element is pivotally connected to the sliding member at a second end.
4. 4. The control surface actuation mechanism of claim 1 or 2, wherein the first path has a nonlinear portion.
5. 5. The control surface actuation mechanism of claim 1 or 2, wherein the articulation support is configured to rotate about the spanwise pivot axis in response to movement of the first end of the first rigid connection element along the first track.
6. 6. The control surface actuation mechanism of claim 1 or 2, wherein the control surface translates relative to the articulation support as the slide member translates.
7. 7. The control surface actuation mechanism of claim 1 or 2, comprising a second rigid connection element connected at a first end to the sliding member and at a second end to a second track defining a second path, wherein the second end of the second rigid connection element is configured to move along the second path.
8. 8. A control surface actuation mechanism according to claim 1 or 2, comprising a third rigid connection element, wherein the third rigid connection element causes rotation of the control surface relative to the articulating support.
9. 9. The control surface actuation mechanism of claim 7, comprising a third rigid connection element, wherein the third rigid connection element causes rotation of the control surface relative to the articulating support, and wherein a second end of the third rigid connection element coincides with a second end of the second rigid connection element.
10. 10. The control surface actuation mechanism of claim 8, wherein the third rigid connection element is connected to a third track defining a third path.
11. 11. The control surface actuation mechanism of claim 8, wherein the first end of the third rigid connection element is connected to a second sliding member having a proximal end mounted on the articulating support and having a distal end for coupling to the control surface, the sliding member being arranged to slide along a generally chordal axis relative to the articulating support.
12. 12. An airfoil of an aircraft comprising a stationary airfoil portion, a control surface and the actuation mechanism of any of claims 1 to 11.
13. 13. The airfoil of an aircraft of claim 12, wherein the hinged support provides an aerodynamic outer surface of the airfoil.
14. 14. An airfoil as claimed in claim 12 or 13 in which the stationary airfoil section has a rear spar and a tail rib and the first track is located on the tail rib.
15. 15. The airfoil of an aircraft of claim 14 wherein the actuator is a linear actuator that moves parallel to the rear spar.

Description

Control surface actuation mechanism Technical Field The present invention relates to a control surface actuation mechanism for moving a control surface relative to a stationary airfoil portion of an aircraft. Background The control surface actuation mechanism may use a plurality of cams to achieve the desired various deflections of the control surface. These mechanisms can be complex, cumbersome, require long manufacturing lead times, and increase drag due to extension into the airflow. Disclosure of Invention According to one aspect of the invention, there is provided a control surface actuation mechanism for moving a control surface relative to a fixed airfoil portion of an aircraft, the control surface actuation mechanism comprising a hinged support for pivotal coupling to the fixed airfoil portion about a generally spanwise pivot axis, a sliding member having a proximal end mounted on the hinged support and having a distal end for coupling to the control surface, the sliding member being arranged to slide along a generally chordwise axis relative to the hinged support, a first rail for attachment to the fixed airfoil portion and defining a first path, and a first rigid connection element connected to the first rail at a first end and to the sliding member at a second end, wherein the first end of the first rigid connection element is configured to move passively along the first path as the sliding member is driven by an actuator to slide relative to the hinged support. Another aspect of the invention provides an airfoil of an aircraft, the airfoil comprising a stationary airfoil portion, a control surface and the actuation mechanism of the first aspect. An advantage of the invention is that the translation and/or rotation of the control surface can be controlled more simply with fewer components than before. Driving the sliding member relative to the articulation support causes translation of the control surface, while the path of the track is capable of causing rotation of the control surface by rotating the articulation support using the rigid connection element. The path of the track can be tailored to give a specific control surface response so that the degree of translation and rotation of the control surface can be controlled at all stages of deployment. Here, the term "substantially spanwise" refers to a direction substantially along the spanwise direction within a small angular difference. Here, the term "substantially chordwise" refers to a direction substantially along the chordwise direction within a small angular difference. The term "rigid connecting element" as used herein refers to a connecting element having a fixed length, i.e. the connecting element is substantially inextensible. The first rigid connection element may be pivotally connected to the first rail at a first end. Although the first rigid connection element is movable along the first track, the first rigid connection element may also pivot relative to the first track at any point along the first track. This may assist in moving the first end of the first rigid connection element along the track when the path of the track has a non-linear portion, so that the angle of the first rigid connection element relative to the local path of the track can be varied. The first rigid connection element may be pivotally connected to the sliding member at the second end. The first path may have a nonlinear portion. The non-linear portion of the first path may allow the relative rate of translation of the slide member and the relative rate of rotation of the articulation support to change as the slide member moves. This can then change the degree of translation and rotation of the control surface at different stages/states of deployment of the control surface. The hinge support may be configured to rotate about the spanwise pivot axis in response to movement of the first end of the first rigid connection element along the first track. This may provide passive rotation of the hinge support determined by the path of the first track, such that both rotation and translation of the control surface in any stage/state of deployment can be predetermined by the position of the first end of the first rigid connection element along the path of the first track. The control surface may translate relative to the articulating support as the slider translates. This may allow the control surface to translate relative to the fixed airfoil portion of the aircraft to alter the aerodynamic profile of the wing. The control surface actuation mechanism may include a second rigid connection element that may be connected to the sliding member at a first end and may be connected to a second track defining a second path at a second end, wherein the second end of the second rigid connection element may be configured to move along the second path. The control surface actuation mechanism may comprise a third rigid connection element, wherein the third rigid connection ele