Actuation mechanism, control surface, and aircraft with flexible control surface

Abstract

The present disclosure relates to an actuating mechanism for a flexible control surface of an aircraft, a control surface and an aircraft having the flexible control surface. The actuating mechanism includes a base element and a rotating element having an articulation axis hinged on the base element. The actuating mechanism also includes at least two attachment rods, each of which has three articulation axes, wherein the first articulation axis of each attachment rod is rotatably articulated on the rotating element, the second articulation axis arranged at the first end of each attachment rod is designed to be articulated on the first skin wall plate of the control surface, and the third articulation axis arranged at the second end of each attachment rod is designed to be articulated on the second skin wall plate of the control surface. The actuating mechanism also includes: at least one connecting element, each of which has an articulation axis at both ends, wherein the first articulation axis of the connecting element is articulated on the base element, and the second articulation axis of the connecting element is articulated on one of the at least two attachment rods; and an actuator designed to rotate the rotating element relative to the base element.

Description

Technical Field

[0001] The invention relates to an actuation mechanism for a flexible control surface of an aircraft, a flexible control surface having a corresponding actuation mechanism, and an aircraft having at least one such control surface. Background Art

[0002] In order to control an aircraft, movable parts are arranged on the components through which the air flows (for example, wings or tail fins) in order to influence the flow of air. Thus, flaps or rudders are arranged at the leading edge (airflow impact edge) and / or the trailing edge (airflow separation edge) of the wing or tail fin, which flaps or rudders can change the flow direction of the air flowing through the components depending on the flight situation.

[0003] At the transition between the fixed outer skin of the wing or tail and such flaps or rudders, kinks or even openings in the outer skin deteriorate the aerodynamic properties of the aircraft and thus increase fuel consumption. In order to improve the aerodynamic properties, flexible control surfaces have been proposed, which have a stretchable and / or bendable outer skin. However, the movement mechanisms for setting a specific shape of said flexible control surfaces are quite complex and therefore prone to failure. Summary of the invention

[0004] The object on which the invention is based is to provide an actuation mechanism for a flexible control surface of an aircraft which is simple in form and which enables a trouble-free movement of the control surface. Furthermore, the aim is to provide a control surface with such an actuation mechanism which ensures a continuous transition between the movable skin of the control surface and the fixed skin of the wing or tail.

[0005] To this end, the teaching of the present invention relates to an actuation mechanism for a flexible control surface of an aircraft, wherein the actuation mechanism comprises a base element and a rotary element, the rotary element having an articulation axis articulated on the base element. While the base element is fixed relative to the flexible control surface and in particular relative to the rotary element, the rotary element can rotate relative to the base element. For example, one or more articulations arranged in the articulation axis of the rotary element can form a rotatable fastening of the rotary element on the base element.

[0006] The actuation mechanism further comprises at least two attachment rods, each of which has three articulation axes, wherein a first articulation axis of each attachment rod is rotatably articulated on a rotary element, wherein a second articulation axis arranged at a first end of each attachment rod is designed to be articulated on a first skin panel of the control surface, and wherein a third articulation axis arranged at a second end of each attachment rod is designed to be articulated on a second skin panel of the control surface. In this case, one or more articulations can also be arranged in each of the rotation axes, the one or more articulations forming a rotatable fastening of the attachment rod on the rotary element or a rotatable fastening of the first skin panel or the second skin panel of the control surface on the attachment rod.

[0007] The attachment rods can be arranged parallel to each other. In this way, a symmetrical orientation of the skin panels can be achieved. In addition, during the movement of the skin panels and thus the control surfaces, their symmetry can be more easily ensured by means of the parallel arrangement of the attachment rods.

[0008] In addition, the actuating mechanism further comprises at least one connecting element, which has an articulation axis at each end, wherein a first articulation axis of the connecting element is articulated on the base element, and wherein a second articulation axis of the connecting element is articulated on one of the at least two attachment rods. One or more articulation portions arranged in the corresponding articulation axis of the connecting element form a rotatable fastening of the connecting element on the base element or the attachment rod, whereby the interface realizes force transmission between the base element and the attachment rod via the connecting element.

[0009] Finally, the actuation mechanism also includes an actuator, which is designed to rotate the rotating element relative to the base element. Here, the at least one connecting element can cause the attachment rod hinged on the second hinge axis of the connecting element to rotate around its first hinge axis and relative to the rotating element based on the rotation of the rotating element relative to the base element. This rotation of the attachment rod hinged on the connecting element is achieved by means of force transmission between the two hinge axes of the connecting element (thrust or pull in the longitudinal direction of the connecting element), wherein a force is generated on the connecting element due to the offset of the first hinge axis of the attachment rod and thus the position of the entire attachment rod relative to the position of the first hinge axis of the connecting element attached to the base element.

[0010] Since the first skin panel and the second skin panel are each rotatably fastened to the at least two attachment rods, which in turn are rotatably fastened to the rotating element, the rotational movement of the rotating element causes a common rotational movement of the first skin panel and the second skin panel (together with the rotating element), and the rotation of one attachment rod caused by the connecting element causes the displacement of the first skin panel and the second skin panel relative to each other. In other words, the first skin panel and the second skin panel each move relative to the rotating element, wherein the skin panels move in opposite directions relative to each other. Due to the flexibility of the control surface (i.e., the skin panels), the two skin panels can bend due to their opposite movement, for example when they are rotationally fixedly connected to each other at one point.

[0011] Thus, the control surface can be moved by means of a simple construction of the actuating mechanism, i.e. with a small number of components and a single actuator. In addition, the actuating mechanism can be of compact design, whereby space is available for other elements between the two skin surfaces. Since the actuating mechanism consists of only a small number of articulated components, it is also less prone to failures. Finally, the combination of the rotary movement of the rotary element with the rotary movement of the attachment rod allows an increase in the freedom of movement of the skin panel of the control surface, thereby enhancing the small-scale movement of the actuator. This also allows a spatially compact design of the actuator.

[0012] In one design variant, the articulation axis of the rotary element and the respective first articulation axis of each attachment rod are arranged parallel to each other and perpendicular to a common line. With this arrangement of the articulation axes, a counter-movement of the skin panel relative to the rotary element is facilitated. With this arrangement of the articulation axes, a rotational movement of the at least two attachment rods can be achieved while maintaining the optional parallel arrangement of the attachment rods.

[0013] In another design variant, each attachment rod can be arranged perpendicularly to the respective first articulation axis of the corresponding attachment rod and, moreover, can be arranged perpendicularly to the common line when the swivel element is in the basic position relative to the base element. In other words, each attachment rod is also in the basic position, wherein the basic position of the attachment rods allows a symmetrical arrangement of the first skin panel and the second skin panel relative to the common line of the articulation axes of the swivel element and the attachment rods.

[0014] Another variant provides that each of the at least one connecting element crosses a common line of the articulation axis of the rotary element and the articulation axis of the attachment rod. This crossing of the at least one connecting element with the common line strengthens the movement of the skin panel in accordance with the rotary movement of the rotary element relative to the base element. Otherwise (if the at least one connecting element is completely on one side of the common line), the rotary movement of the rotary element relative to the base element would cause a counter-rotational movement of the attachment rod and thus of the skin panel. As a result, the rotary movement of the rotary element will be at least partially eliminated again due to the counter-rotational movement of the attachment rod.

[0015] In addition, the at least one connecting element may include two traction cables. Here, the first traction cable of the two traction cables crosses the common line of the hinge axis of the rotating element and the attachment rod in a different direction from the second traction cable of the two traction cables. In other words, the first traction cable is rotatably connected to the attachment rod on the first side of the common line, and the first traction cable is rotatably connected to the base element on the second side of the common line opposite to the first side. In turn, the second traction cable is rotatably connected to the attachment rod on the second side of the common line and is rotatably connected to the base element on the first side of the common line. Depending on the rotation direction of the rotating element relative to the base element, one of the two traction cables applies a pulling force to the attachment rod, thereby realizing the rotational movement of the attachment rod relative to the rotating element. The use of traction cables allows a flat construction of the actuating mechanism.

[0016] Alternatively, the at least one connecting element may comprise a shear-resistant traverse. The shear-resistant traverse is also rotatably connected to the attachment rod on a first side of the common line at one end and is rotatably connected to the base element on a second side of the common line opposite to the first side at an opposite end. Since the shear-resistant traverse is capable of transmitting thrust and tension between the attachment rod and the base element, the single connecting element is sufficient to achieve a relative rotational movement of the attachment rod relative to the rotating element for both directions of rotation of the rotating element relative to the base element. The use of a single shear-resistant traverse allows weight reduction relative to the use of multiple connecting elements.

[0017] In another embodiment, each of the first articulation axes of the respective attachment rods can be arranged in the middle of the respective attachment rod. In this way, a symmetrical construction of the actuating mechanism can be achieved. Alternatively, each first articulation axis of the respective attachment rods can also be arranged to be spaced apart from the middle of the respective attachment rod by an equal amount. Thereby, a predetermined asymmetry of the actuating mechanism can be achieved, which predetermined asymmetry allows, for example, pre-aligning the skin panels (of the control surface) to one side (of the common line).

[0018] In another embodiment, the second articulation axis of the connecting element is articulated between the first articulation axis and the second articulation axis of the attachment rod or between the first articulation axis and the third articulation axis of the attachment rod. The further the second articulation axis of the connecting element is from the first articulation axis of the attachment rod, the greater the lever arm of the connecting element and the articulated attachment rod can be rotated relative to the rotating element more easily. In addition, the spacing between the second articulation axis of the connecting element and the first articulation axis of the attachment rod determines the degree of relative movement of the attachment rod with respect to the rotating element. The smaller the spacing, the greater the relative movement.

[0019] In another embodiment, the actuator may include a shear beam rotatably fastened to the rotary element. The shear beam may, for example, be rotatably fastened to the rotary element, wherein the rotatably fastened articulation axis of the shear beam on the rotary element is spaced apart from the articulation axis of the rotary element. In this way, a rotational movement of the rotary element about its articulation axis may be achieved by means of a simple linear movement of the shear beam.

[0020] Alternatively or additionally, the actuator can include a pneumatic or hydraulic drive. The actuator can then include a pneumatically or hydraulically operated piston, which can perform a linear movement. This linear movement can be transmitted to the rotary element, for example, by means of a connecting rod or a shear beam, wherein the connecting rod or the shear beam is rotatably fastened to the rotary element. As a result, the rotary movement of the rotary element about its articulation axis is generated in a manner that depends on the spacing of the rotatable fastening of the connecting rod or the shear beam from the articulation axis of the rotary element.

[0021] Alternatively or additionally, the actuator may also include an actuating motor. The actuating motor may, for example, be designed to rotate a gear and move the gear to an arbitrary position (e.g. relative to a base element). A rack or other gear may mesh with the gear. The rack may be rotatably coupled to a rotating element, wherein the articulation axis of the rack at the connection point with the rotating element is spaced apart from the articulation axis of the rotating element. In the case of other gears, the other gear may be fastened to the rotating element or integrated therein, wherein the axis of rotation of the other gear coincides with the articulation axis of the rotating element. In both cases, the rotation of the gear by means of the actuating motor realizes the rotational movement of the rotating element around its articulation axis.

[0022] In each design variant of the actuator, the actuator may additionally comprise a gearing. By means of a corresponding transmission ratio in the gearing, the actuator can be designed to be smaller (more compact) and can also be arranged closer to the articulation axis of the rotary element.

[0023] Finally, the actuator may be provided or integrated in the base element.

[0024] According to another aspect, a control surface for an aircraft comprises an actuation mechanism according to the described aspect or one of the described embodiments and variants. In addition, the control surface may comprise a flexurally elastic first skin panel rotatably fastened to the second articulation axis of each attachment rod and a flexurally elastic second skin panel rotatably fastened to the third articulation axis of each attachment rod. In other words, the first skin panel is rotatably fastened to each attachment rod, and the second skin panel is also rotatably fastened to each attachment rod. Thus, the first skin panel is fastened to the first end of each attachment rod, and the second skin panel is fastened to the corresponding opposite end of each attachment rod.

[0025] The skin panels of the control surface can each extend between the corresponding ends of each attachment rod and further extend beyond the corresponding ends in two directions. In the basic position of the attachment rod, at least one of the skin panels can be arranged perpendicular to the attachment rod. In addition, in the area of ​​connection, at least one of the skin panels can be bent or curved. In addition, the first skin panel and the second skin panel of the control surface are connected to each other at a position away from the actuating mechanism. The first skin panel and the second skin panel thus form a body open on one side, wherein the attachment rod and part of the rotating element are arranged in the opening of the body thus formed. The length of the attachment rod in this case determines the spacing between the first skin panel and the second skin panel in the opening area of ​​the body thus formed.

[0026] Alternatively, the first skin panel and the second skin panel can be made of a continuous material, wherein the material extends away from the actuating mechanism in the region of the first skin panel, forms an inflection point and extends back to the actuating mechanism in the region of the second skin panel. The material can be a fiber-reinforced plastic or a metal, such as aluminum.

[0027] In each case, the control surface has a region which is spaced apart to the greatest extent from the actuating means. Said region may form the airflow impact edge (leading edge) or the airflow separation edge (trailing edge) of the wing or tail.

[0028] Furthermore, the control surface may comprise at least one spar arranged between the first and second skin panels. The at least one spar is arranged between the first and second skin panels in a region where no actuation means and in particular no attachment rods are arranged.

[0029] Here, the at least one spar can include a flexurally elastic spar connected to the first and second skin panels in a rotationally fixed manner. The flexurally elastic spar can have a curved shape (e.g. approximately semicircular) in the cross section of the wing or tail, wherein the opening of this curved shape points towards the actuating mechanism. Firstly, the at least one flexurally elastic spar stabilizes the control surface formed by the first and second skin panels due to the connection of the spar to the two skin panels. Secondly, due to the reverse movement of the first skin panel relative to the second skin panel achieved by the actuating mechanism, the at least one flexurally elastic spar also allows bending of at least one of the skin panels.

[0030] Alternatively or additionally, the at least one spar may comprise a rigid spar which is connected to the first skin panel by means of a hinge and to the second skin panel by means of a hinge. The rigid spar also stabilizes the two skin panels of the control surface and also allows the first skin panel to move in the opposite direction relative to the second skin panel by means of the arrangement of the hinge. The hinge is arranged on the inner side of the two skin panels facing each other. In addition, the spacing between the first skin panel and the second skin panel is also maintained by means of the rigid spar when the two skin panels move in the opposite direction relative to each other.

[0031] According to another aspect, an aircraft comprises at least one flexible control surface in one of the described embodiments and variants.

[0032] The aircraft also comprises a wing and / or a tail, wherein the base element of the actuating mechanism included in the control surface is fastened or integrated on an immovable part of the wing or tail. The immovable part of the wing or tail may be a spar arranged longitudinally of the wing or tail. Obviously, the base element of the actuating mechanism may also be fastened or integrated on one or more ribs arranged transversely of the wing or tail.

[0033] Alternatively or additionally, the first skin panel of the control surface can be arranged flush with the first outer skin of the wing or tail. In addition, the second skin panel of the control surface can be arranged flush with the second outer skin of the wing or tail opposite to the first outer skin. In other words, the first skin panel and the second skin panel form sections of the two outer skins of the wing or tail, which sections are opposite to each other in the cross section of the wing or tail.

[0034] Due to the counter-movement of the first skin panel relative to the second skin panel, a stretchable outer skin section can be arranged between the respective outer skin of the wing or tail and the corresponding skin panel. Alternatively, the first skin panel and / or the second skin panel can at least partially comprise a stretchable material, so that no opening is formed at the transition between the skin panel and the remaining outer skin of the wing or tail due to the movement of the control surface caused by the actuating mechanism.

[0035] In addition, the first skin panel and the second skin panel form the airflow impact edge (leading edge) or the airflow separation edge (trailing edge) of the wing or the tail. In other words, the control surface is arranged at the airflow impact edge or the airflow separation edge of the wing or the tail, wherein the first skin panel and the second skin panel are the outer skin of the wing or the tail forming the airflow impact edge or the airflow separation edge.

[0036] The arrangement of the components of the actuating mechanism and the control surfaces described here particularly relates to a cross-sectional view of a wing or tail. Thus, for example, all the articulation axes of the actuating mechanism described here can be arranged parallel to each other and substantially perpendicular to the cross-section of the wing or tail. The articulation axes of the actuating mechanism can also be arranged parallel to the longitudinal direction of the wing or tail.

[0037] In addition, the air flows over the skin panels of the control surface, and the direction of the air flow is sought to be changed by the skin panels. Thus, when viewed in the longitudinal direction of the wing or tail, all the articulation axes of the actuation mechanisms are arranged parallel to the outer skin of the wing or tail. The articulation axes can, for example, be substantially perpendicular (i.e. at an angle of 90° + / - 10°) to the air flow direction.

[0038] Instead of aircraft, the actuators and control surfaces described herein may also be arranged on other vehicles including motor vehicles and watercraft. Due to the control by means of the actuator, the flow of any fluid flowing on the skin panels of the control surface may be affected. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Exemplary embodiments of the present invention will be described in detail below based on the accompanying drawings.

[0040] Figure 1 Schematically illustrates a cross section of an exemplary actuation mechanism having two skin panels forming corresponding control surfaces;

[0041] Figure 2 Schematically illustrates a cross section of another exemplary actuation mechanism having two skin panels forming corresponding control surfaces;

[0042] Figure 3 Schematically showing the Figure 1 deflection of the control surface by an actuating mechanism;

[0043] Figure 4 Schematically showing the Figure 1 The actuation mechanism of the control surface is Figure 3 Deflection in the direction opposite to the deflection;

[0044] Figure 5 A control surface having a curved elastic spar is schematically shown;

[0045] Figure 6schematically shows a control surface having a rigid, rotatably mounted spar; and

[0046] Figure 7 An aircraft is shown having a number of exemplary control surfaces. DETAILED DESCRIPTION

[0047] According to the invention described herein, an actuation mechanism for a control surface, a control surface for an aircraft and a corresponding aircraft are proposed.

[0048] Figure 1 The exemplary actuation mechanism 10 is illustrated in cross-section of a wing or tail of an aircraft that may include the actuation mechanism. Figure 1 The air flows around the actuator 10 on the left and right sides of the Figure 1 The actuating mechanism 10 comprises a base element 12 and a rotating element 14. The rotating element 14 has an articulated shaft 15, which is articulated on the base element 12. One or more articulated parts (in the X-axis direction, which corresponds to the flight direction or longitudinal axis of the aircraft) are provided. Figure 1 The hinge (covered) may be located on the hinge axis 15, the one or more hinges rotatably fastening the rotating element 14 to the base element 12.

[0049] The actuating mechanism 10 also includes two attachment rods 22, 23, each of which has three articulated axes. Here, the attachment rods 22, 23 can be arranged parallel to each other. The first 25 or 26 of the articulated axes is rotatably hinged on the rotating element 14. Here, an articulation portion (not explicitly shown) is also provided on the corresponding articulation axis 25, 26, whereby the corresponding attachment rods 22, 23 are rotatably fastened to the rotating element. A second articulation axis 28 is also arranged at each end of each attachment rod 22, 23, and the first skin wall panel 31 can be hinged on the second articulation axis 28. A third articulation axis 29 is arranged on the opposite side of each attachment rod 22, 23, and the second skin wall panel 32 can be hinged on the third articulation axis 29. An articulation portion can also be provided on each of the second articulation axis 28 and the third articulation axis 29 for rotatably fastening the corresponding skin wall panels 31, 32.

[0050] The skin panels 31, 32 form the outer skin of the wing 101 or the tail 102, 103 of the aircraft. Figure 7 Here, the skin panels 31, 32 form the control surface 50 at the airflow separation edge ("trailing edge") of the wing 101 or the tail 102, 103. In the embodiment described here, the control surface 51 can also be formed at the airflow impact edge or leading edge of the wing 101 or the tail 103.

[0051] exist Figure 1 In the case of the control surface 50 illustrated in the figure, the Z axis shown extends perpendicularly to the plane of the drawing, wherein in the aircraft the Z axis approximately forms an axis extending perpendicularly through the aircraft. Therefore, the control surface 50 illustrated is arranged in a section of the vertically arranged tail 102. Obviously, the control surfaces 50, 51 shown can also be control surfaces 50, 51 in the wing 101 or the horizontal tail 103. For this purpose, it is only necessary to interchange the identification of the Y axis and the identification of the Z axis (wherein in the aircraft the Y axis approximately forms a horizontal direction extending perpendicularly to the flight direction).

[0052] In order to form the airflow separation edge or the airflow impact edge, the two skin panels 31, 32 are connected to each other. Alternatively, the skin panels 31, 32 are made of workpieces that are turned or bent (have an inflection point) correspondingly at the airflow separation edge or the airflow impact edge. Figure 1 , in which the skin panels 31 and 32 intersect at an acute angle. However, especially at the airflow impact edge, the skin panels 31 and 32 can form a continuous, aerodynamically efficient curve.

[0053] The base element 12 included in the actuation mechanism 10 can be fastened to a fixed part 104 of the wing 101 or the tail 102, 103. Alternatively, the base element 12 of the actuation mechanism 10 can be integrated in such a part 104, so that the rotating element 14 is hinged on the fixed part 104. Also alternatively or additionally, the part 104 of the wing 101 or the tail 102, 103 itself can also be part of the movable part of the wing 101 or the tail 102, 103. In this way, the actuation mechanism and the skin panels 31, 32 can realize an additional movement of a section of the wing 101 or the tail 102, 103.

[0054] The actuating mechanism 10 further comprises at least one connecting element 21. Figure 1 The connecting element 21 has in each case one articulation axis at opposite ends, wherein the first articulation axis 24 of the connecting element 21 is articulated on the base element 12 and the second articulation axis 27 of the connecting element 21 is articulated on one of the at least two attachment rods 22, 23. Figure 1 The actuating mechanism 10 illustrated in FIG. 1 has a connecting element 21 which is hinged on an attachment rod 22 which is closest to the base element 12. In this way, the connecting element 21 can be designed to be lighter than if it were fastened on an attachment rod 23 which is further away from the base element 12, which would however enable a better leverage effect.

[0055] Finally, the actuation mechanism 10 also comprises an actuator designed to rotate the rotating element 14 relative to the base element 12. Figure 1 In the simple design shown in FIG. 1 , the actuator has a shear beam 16 rotatably fastened to a rotating element 14. The shear beam 16 can be moved by any moving device (not shown). Figure 1 The rotating element 14 is displaced in the X-axis direction, and the rotating element 14 rotates relative to the base element 12 around the hinge axis 15 of the rotating element.

[0056] The articulation axis 15 of the swivel element 14 and the first articulation axis 25, 26 of each attachment rod 22, 23 are arranged parallel to one another (at right angles to the axis 14). Figure 1 in the Z-axis direction of the drawing) and are located on a common line (e.g., on a line parallel to Figure 1 The common line may form an axis of symmetry of the rotation element 14 and / or the base element 12.

[0057] also, Figure 1 The basic position of the actuating mechanism 10 is shown, in which the rotating element 14 is in the basic position relative to the base element 12. In this basic position, each attachment rod 22, 23 is arranged perpendicular to the common line. Thus, the skin panels 31, 32 are in the basic position. For example, the airflow separation edge formed by the skin panels 31, 32 (as in Figure 1 ) can also be located on this common line, whereby the skin panels 31 , 32, the attachment rods 22 , 23 and the rotation element 14 can be arranged symmetrically with respect to this common line.

[0058] Obviously, the flow separation edge or flow impact edge can also be arranged spaced apart from this common line, ie the skin panels 31, 32 point in a specific direction. The aerodynamic properties of the wing 101 or the tail 102, 103 may require a deviation from this common line.

[0059] At least one connecting element 21 intersects the common line of the articulation axis 15 of the rotation element 14 and the articulation axes 25, 26 of the attachment rods 22, 23. Here, a single connecting element 21 (such as in Figure 1 ) in the actuating mechanism 10 is sufficient.

[0060] Figure 2Another embodiment of at least one connecting element 21 is shown, which enables a lighter actuating mechanism 10. In this further embodiment, two traction cables (a first traction cable 21a, a second traction cable 21b) are provided in the actuating mechanism 10 instead of the shear-resistant connecting element 21. All other components of the actuating mechanism 10 and the skin panels 31, 32 are connected to the Figure 1 corresponding to the design.

[0061] The first traction cable 21a and Figure 1 The shear-resistant connecting element 21 crosses the common line of the articulation axis 15 of the rotating element 14 and the articulation axes 25, 26 of the attachment rods 22, 23 in the same or similar manner. However, since the first traction cable 21a cannot transmit thrust, a second traction cable 21b is provided, which crosses the common line of the articulation axis 15 of the rotating element 14 and the articulation axes 25, 26 of the attachment rods 22, 23 in the opposite direction. In other words, the second traction cable 21b has a first articulation axis 24b, which is articulated on the base element 12 and is located on the opposite side of the common line relative to the first articulation axis 24a of the first traction cable 21a. In addition, the second articulation axis 27b of the second traction cable 21b is articulated on the attachment rod 22 and is located on the opposite side of the common line relative to the second articulation axis 27a of the first traction cable 21a.

[0062] Reference Figure 1 and Figure 2 The second articulation axis 27, 27a of the connecting element 21 and the first traction cable 21a are therefore articulated between the first articulation axis 25 and the second articulation axis 28 of the attachment rod 22, and with reference to Figure 2 The second articulation axis 27 b of the connecting element (here the second traction cable 21 b ) is articulated between the first articulation axis 25 and the third articulation axis 29 of the attachment rod 22 .

[0063] This corresponding arrangement of the at least one connecting element 21, the first traction cable 21a, the second traction cable 21b (hereinafter collectively referred to as 21) and the first articulation axis 24, 24a, 24b (hereinafter collectively referred to as 24) of the at least one connecting element 21 on the base element 12 enables the rotation of the attachment rod 22 (on which the second articulation axis 27, 27a, 27b (hereinafter collectively referred to as 27) of the connecting element 21 is articulated). This rotation of the attachment rod 22 takes place relative to the rotating element 14 about the first articulation axis 25 of the attachment rod 22 when the actuator rotates the rotating element 14 relative to the base element 12 and the connecting element 21 acts on the articulated attachment rod 22. Furthermore, the skin panels 31 , 32 are rotatably fastened on the respective articulation axis 28 or 29 of the attachment rod 22 or 23 , so that a rotational movement of the attachment rod 22 causes a counter displacement of the skin panels 31 , 32 relative to one another.

[0064] This is Figure 3 and 4 Example in. exist Figure 3 , the actuator moves upward, i.e. the rotary element 14 rotates clockwise about its articulation axis 15 relative to the base element 12. The shear beam 16 can in this case be moved substantially linearly by the value X1. As a result, the second articulation axis 27 of the shear-resistant connecting element 21 is also moved about the articulation axis 15 of the rotary element 14. However, since the spacing between the two articulation axes 24 and 27 of the connecting element 21 remains the same due to the shear-resistant connecting element 21, the attachment rod 22 is also rotated clockwise relative to the rotary element 14. When two traction cables (first traction cable 21a, second traction cable 21b) are arranged Figure 2 ), the attachment rod 22 is also rotated clockwise relative to the rotation element 14, since the spacing of the first articulation axis 24b to the second articulation axis 27b of the second traction cable 21b remains the same.

[0065] Thus, the first skin panel 31 rotatably fastened on the second articulation axis 28 of the attachment rod 22 is moved relative to the rotation element 14 by a distance X2, which is transmitted to the second attachment rod 23 and in particular to its second articulation axis 28 via the skin panel 31. Likewise, the second skin panel 32 rotatably fastened on the third articulation axis 29 of the attachment rods 22 and 23 is in each case moved in the opposite direction by a value X3 relative to the rotation element 14. If the spacing between the second articulation axis 28 of the attachment rods 22, 23 and the respective first articulation axis 25, 26 is equal to the spacing between the third articulation axis 29 of the attachment rods 22, 23 and the respective first articulation axis 25, 26, then X2 and X3 are also equal. By changing the position of the respective first articulation axis 25, 26 of the attachment rods 22, 23, the ratio of X2 to X3 can be changed accordingly.

[0066] Due to the rigid attachment rods 22 and 23 and the ratio of the length of the attachment rods 22, 23 to the relative movement X2 and X3 which are smaller than the length of the attachment rods 22, 23, the spacing between the skin panels 31, 32 in the area of ​​the attachment rods 22, 23 changes only very slightly, so that the relative movement of the skin panels 31, 32 with respect to the rotating element 14 is approximately a linear movement.

[0067] By means of the flexurally elastic material of the skin panels 31, 32 and the common connection point (or inflection point) of the skin panels 31, 32, the skin panels 31, 32 undergo bending in the direction of the rotation of the rotating element 14 relative to the base element 12. As a result, the common connection point of the skin panels 31, 32 moves by a distance Y1 in the clockwise direction corresponding to the movement of the rotating element 14 relative to the base element 12. By means of this arrangement and the opposite relative movement of the skin panels 31, 32, the movement of the connection point of the skin panels 31, 32 is enhanced. In other words, the connection point of the skin panels 31, 32 is deflected further than if the connection point is deflected only based on the rotational movement of the rotating element 14 relative to the base element 12.

[0068] Figure 4 A movement in the opposite direction is shown, in which the shear beam 16 of the actuator for example moves by the value X4 and causes a counterclockwise rotational movement of the rotation element 14 relative to the base element 12. Correspondingly, the skin panels 31, 32 are linearly (again approximately) moved in the opposite direction relative to the rotation element 14 by means of the attachment rods 22, 23 by the distances X5 and X6, while the connection points of the skin panels 31, 32 are correspondingly moved by the distance Y2 in the counterclockwise direction.

[0069] The spar may be located in the region between the skin panels 31 , 32 and in the range between the common connection points (or inflection points) of the rotation elements 14 or attachment rods 22 , 23 and the skin panels 31 , 32 . Figure 5 Such a spar 41 is exemplified, which is made of a flexurally elastic material and is fixedly connected at its respective ends to the first skin panel 31 and the second skin panel 32 . Figure 6 An alternative spar 42 is shown which is produced from a rigid, shear-resistant material and is rotatably connected to the respective skin panel 31 or 32 at a corresponding hinge 43 , 44 .

[0070] The spars 41, 42 improve the stability of the skin panels 31, 32 and thus the control surfaces 50, 51. Due to the flexibility of the spars 41 and the rotatable fastening of the spars 42 to the skin panels 31, 32, it is ensured that Figure 3 and 4 The movements of the skin panels 31 , 32 relative to the rotating element 14 are illustrated in FIG. 1 (see movements X1 , X2 , X5 and X6 as well as Y1 and Y2 ).

[0071] Finally, it is especially pointed out that the variants, embodiments and exemplary embodiments discussed above are merely used to describe the claimed teachings, but do not limit said teachings to these variants, embodiments and exemplary embodiments.

Claims

1. An actuating mechanism (10) for a flexible control surface (50, 51) of an aircraft (100), wherein the actuating mechanism comprises: a base member (12); A rotating element (14), the rotating element (14) having a hinge shaft (15) hinged on the base element (12); At least two attachment rods (22, 23), each of which has a first, a second and a third articulation axis, wherein the first articulation axis of each attachment rod (22, 23) is rotatably articulated on the rotation element (14), wherein the second articulation axis (28) arranged at the first end of each attachment rod (22, 23) is designed to be articulated on a first skin panel (31) of the control surface (50, 51), and wherein the third articulation axis (29) arranged at the second end of each attachment rod (22, 23) is designed to be articulated on a second skin panel (32) of the control surface (50, 51); at least one connecting element (21) having a hinge axis at each end, wherein a first hinge axis (24) of the connecting element (21) is hinged on the base element (12), and wherein a second hinge axis (27) of the connecting element (21) is hinged on one of the at least two attachment rods (22, 23); and an actuator designed to rotate the rotating element (14) relative to the base element (12), The at least one connecting element (21) causes a first attachment rod of the at least two attachment rods (22, 23) which is hinged on a second hinge axis (27) of the connecting element (21) to rotate about its first hinge axis (25) and relative to the rotating element (14) based on the rotation of the rotating element (14) relative to the base element (12).

2. Actuating mechanism (10) according to claim 1, wherein the articulation axis (15) of the rotation element (14) and the respective first articulation axis of each attachment rod (22, 23) are arranged parallel to each other and perpendicular to a common line.

3. An actuation mechanism (10) according to claim 2, wherein each of the attachment rods (22, 23) is arranged perpendicular to the respective first articulation axis of the corresponding attachment rod (22, 23), and further, when the rotation element (14) is in a basic position relative to the base element (12), each of the attachment rods (22, 23) is arranged perpendicular to the common line.

4. The actuating mechanism (10) according to claim 2, wherein each of the at least one connecting element (21) intersects a common line of the articulation axis (15) of the rotation element (14) and the first articulation axes of the at least two attachment rods (22, 23).

5. An actuation mechanism (10) according to claim 4, wherein the at least one connecting element (21) comprises two traction cables (21a, 21b), and wherein a first traction cable (21a) of the two traction cables crosses a common line of the articulation axis (15) of the rotating element (14) and the first articulation axis of the at least two attachment rods (22, 23) in a different direction than a second traction cable (21b) of the two traction cables.

6. The actuation mechanism (10) according to claim 1, wherein the at least one connecting element (21) comprises a shear beam.

7. The actuating mechanism (10) according to claim 1, wherein each of the first articulation axes of the respective attachment rods (22, 23) is arranged in the middle of the corresponding attachment rod (22, 23).

8. The actuating mechanism (10) according to claim 1, wherein the second articulation axis (27) of the connecting element (21) is articulated between the first articulation axis (25) and the second articulation axis (28) of the first attachment rod or between the first articulation axis (25) and the third articulation axis (29) of the first attachment rod.

9. The actuating mechanism (10) according to claim 1, wherein the actuator comprises a shear beam (16) rotatably fastened to the rotating element (14), a pneumatic drive, an actuating motor and / or a gear arrangement.

10. A control surface (50, 51) for an aircraft (100), comprising: The actuating mechanism (10) according to claim 1; a first flexurally elastic skin panel (31) which is rotatably fastened to a second hinge axis (28) of each attachment rod (22, 23); as well as A second flexurally elastic skin panel (32) is rotatably fastened to the third hinge axis (29) of each attachment rod (22, 23).

11. The control surface (50, 51) according to claim 10, further comprising: At least one spar (41, 42) is arranged between the first skin panel (31) and the second skin panel (32).

12. A control surface (50, 51) according to claim 11, wherein the at least one spar (41, 42) comprises a flexurally elastic spar (41) which is connected to the first skin panel (31) and the second skin panel (32) in a rotationally fixed manner and / or a rigid spar (42) which is connected to the first skin panel (31) by means of a first hinge (43) and to the second skin panel (32) by means of a second hinge (44).

13. An aircraft (100) comprising at least one control surface (50, 51) according to claim 10.

14. The aircraft (100) according to claim 13, further comprising: a wing (101); and / or Tail (102, 103), The base element (12) of the actuating mechanism (10) included in the control surface (50, 51) is fastened or integrated on an immovable part (104) of the wing (101) or the tail (102, 103).

15. The aircraft (100) according to claim 14, wherein a first skin panel (31) of the control surface (50, 51) is arranged flush with a first outer skin of the wing (101) or the tail (102, 103), and wherein a second skin panel (32) of the control surface (50, 51) is arranged flush with a second outer skin of the wing (101) or the tail (102, 103) opposite to the first outer skin.

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