WINGS WITH SHAPE-CHANGING TUBERCLES

Abstract

The invention relates to a wing (1) with a wing body (2) which has a leading edge (4) extending transversely relative to an incoming flow (3), which leading edge has, in its longitudinal direction (L) oriented transversely to the incoming flow (3), a plurality of tubercles (5) which can be formed adjacent to one another and each have a tubercle extension maximum (6) pointing in the direction of the incoming flow (3), wherein the wing body (2) has stiffening elements (8) oriented along the incoming flow (3) and ending with end faces (10) at the leading edge (4), a shape-changing skin (9) and a deformation device for deforming the shape-changing skin (9).In order to further develop a wing (1) in such a way that the flow conditions on the wing (1) can be influenced to an increased extent, it is proposed that the deformation device is designed in such a way and that the shape-changing skin (9) is supported on the end faces (10) of the stiffening elements (8) in such a way that a tubercle expansion maximum (6) can be formed on the end faces (10) of the stiffening elements (8).

Description

TECHNICAL FIELD OF THE INVENTIONThe invention relates to a blade having a blade body which has a front edge which extends transversely relative to an inflow. The front edge of the wing body has, with respect to its longitudinal extension oriented transversely to the inflow, a plurality of tube becomings that can be formed adjacent to one another. Each shape-changing tubercle has a tubercle extension maximum, the tubercle tip of which points substantially in the direction of the incident flow. The wing body has stiffening elements oriented along the inflow and ending with their end faces at the front edge, a skin that can be shaped, and a deformation device for deforming the skin that can be shaped.The tubercles can be extended on the wing body, in particular due to the situation, in order to positively influence the flow conditions on the wing, in particular a lift-air resistance ratio.With respect to a wing of an aircraft, tuberules may have advantages during both take-off and landing operations and flight operations, particularly at low flight speeds. In other situations, for example in transonic flight, it is recommended, on the other hand, to retract the tubercle again.PRIOR ARTUS 2006 / 0 060 721 A1 discloses an aircraft with airfoils which have a plurality of projections on a leading edge against which the flow impinges, which projections follow one another in the spanwise direction of the airfoil. To form a projection, a relevant partial region of the leading edge of the wing is extended starting from a retracted starting position. Along the front edge of the wing, a sequence of projection tips is thus produced, which project with respect to a base region defining the starting position.U.S. Pat. No. 8,535,008 B2 discloses a turbine or a compressor having a rotor blade which has a plurality of tuberules formed along a leading edge at a leading edge which has an inflow. A distance between adjacent tuberkes and a shape of the tubercle are changeable to compensate flow rates that change slowly, particularly over the course of several days.CN 1 08 945 392 A discloses a wing having a wing leading edge and reinforcing ribs oriented parallel to an inflow direction, and an elastically deformable outer skin which is guided over end faces of the reinforcing ribs. Between each of two adjacent reinforcing ribs there is a plunger which displaces the outer skin outwards, forming tube becoming tubes. Tubercle minima are thereby produced at the end sides of the reinforcing ribs.U.S. Pat. No. 6,431,498 B1 discloses a wing having a wing leading edge formed from a shape-adjustable material. The wing leading edge has a device which forms successive projections in the longitudinal direction of the wing leading edge. The projections form tubercle maxima with variable deflection amplitude.The disadvantage of the disclosed prior art is that the tubercle can only change to a limited extent with regard to its shape and size. Moreover, a change of a position of a tubercle on the wing is not possible at all.OBJECT OF THE INVENTIONThe invention is based on the object of further developing a wing with variable tube becoming so much more so that the flow conditions on the wing can be influenced even more extensively.SOLUTIONThe object of the invention is achieved by the features of the independent claim. Preferred embodiments can be taken from the dependent claims.DESCRIPTION OF THE INVENTIONThe invention relates to a wing with a wing body which has a front edge extending transversely relative to an inflow and which has a plurality of tube becoming deformable adjacent to one another in its longitudinal direction oriented transversely to the inflow. Each tubercle has a tubercle extension maximum pointing in the direction of the inflow. The wing body further comprises stiffening elements oriented along the inflow and terminating with end faces at the front edge, a skin that can be shaped and a deformation device for deforming the skin that can be shaped. According to the invention, the deformation device is designed and the skin that can be changed in shape is supported on the end sides of the stiffening elements in such a way that a tubercle extension maximum can be formed on the end sides of the stiffening elements.At the front edge of the wing body, the skin that can be changed in shape is thus supported on the reinforcing elements in such a way that the skin that can be changed in shape can be formed in sections into one or more tube tubes by means of the associated deformation device with respect to the longitudinal direction of the front edge. Adjacent end faces of the stiffening elements, on which the skin that can be shaped is supported in the respective section of the front edge, can form tubercle extension maxima which protrude counter to the direction of the flow against the front edge of the wing.If a partial region of the shape-changeable skin is displaced between two adjacent stiffening elements, i.e. into the wing body, a convex protrusion of the shape-changeable skin results in the region of the end sides of the stiffening elements, with respect to a cross section of the wing body transversely to a longitudinal extension of the front edge of the wing. The end faces form the tubercle extension maxima of the tubercle that point outwards.The tuberules form a wavy leading edge of the wing and, especially in the case of an aircraft wing, can retard flow separation on the wing towards higher angles of attack. The adaptive, so-called "morphing", formation of tube becomings at the front edge of an aircraft wing is particularly advantageous in the case of take-off and landing processes of the aircraft. The lift-air resistance ratio of the wing can likewise be positively influenced, in particular at low flight speeds of the aircraft. In other situations, for example at higher flight speeds, in particular transonic flight, or at low angles of attack of the wing with respect to the incident flow, it is recommended to again break the tubercle, so that the leading edge is as rectilinear as possible and / or no longer has a wave shape.Other types of wings also benefit from the formation of tube becomings along an against-flow leading edge. As an alternative to aircraft wings, a wing according to the invention can be, for example, a rotor blade of a wind turbine, a turbine or a compressor, a fin of a watercraft, a rim of a wheel or other surfaces subjected to an incident flow.At the front edge of the wing, a plurality of tubercles are preferably provided. The number, their distance from one another and the dimensions of the tubercle are preferably determined by the size of the wing and its intended use. With respect to an aircraft wing, it is possible to form five, ten or more tubercles, for example, in the longitudinal direction of the wing oriented transversely to the incident flow, i.e. in the span-wise direction. For this purpose, the skin that can be changed in shape is either supported on a corresponding plurality of stiffening elements or, in addition to the stiffening elements, is equipped with its own dimensionally stable partial regions which can form extreme points of tuberules, i.e. tubercle expansion maxima and / or tubercle expansion minima. This will be discussed later.According to one embodiment, the wing body has a stiffening element per tubercle, which defines the position of the tubercle in the longitudinal direction of the front edge of the wing and forms the tubercle expansion maximum.The reinforcing elements of the wing body can influence the outer shape of the wing. In particular, a stiffening element can be, for example, a partial region of an outer surface of the blade, wherein the partial region is at least partially aligned along the inflow and has a free end side which is at least partially opposed to the inflow.Alternatively, a tubercle extension maximum can be predefined by an element arranged completely or predominantly within an outer contour of the wing body. Such elements located within the wing body are, for example, longitudinal struts which cross a front spar of a wing and point substantially in the direction of the inflow. Elements arranged within the wing body can particularly preferably be those which form parts of the profile structure of the wing body and are thus present in any case in the wing. If necessary, such profile elements can be varied in such a way that they can serve as stiffening elements with end faces directed against the inflow.The tubercles can have shapes and / or dimensions which are identical to one another, similar to one another or else mutually different, in particular longitudinally and / or transversely with respect to the incident flow and / or with respect to a curvature of their convex or concave shape.The support of the shape-changeable skin is preferably effected via at least two stiffening elements pointing substantially in the direction of the inflow. The shape of the skin that can be shaped can be changed in this way when acted upon by a force of the deformation device acting at least partially in the inflow direction, such that at least one tubercle is produced between the stiffening elements. The force exerted by the deformation device on the skin that can be changed in shape brings about the so-called "morphing" or an adaptive change in shape of the wing leading edge.In or on the wing, in particular the front edge, particularly preferably in the region of the tubercle to be formed, a sensor system can be placed which detects at least one parameter of the wing and / or of the environment and / or flow relating to the wing with one or more sensors. For example, current states of the aircraft, ship and / or compressor having the wing and the like, current states of the environment and / or of the wing and / or of the flow on the wing can be detected in order to decide whether and / or when a tubercle is to be formed. With respect to an aircraft, parameters can preferably be detected and / or determined by means of the already present sensor system, such as a dynamic pressure static system or an angle of attack estimator. Alternatively or additionally, further sensors can be used for controlling the tubercle formation, for example pressure sensors, optical sensors and / or acoustic sensors.Preferably, a computing device coupled to the sensors has logic which is configured to make decisions regarding the formation of tuberkes. For this purpose, matrices or tables can be stored in a data memory, for example. These matrices or tables contain, for example, data which have been acquired as part of a simulation of an incident flow of the wing, for example a flight simulation, or as part of a test operation. Scenarios can be determined and stored which are repeated in the presence of defined detection parameters. For example, data detected in the past can allow a conclusion to be drawn that the formation of tube becomings is always advantageous in a specific operating mode and should therefore be repeated in comparable situations. For example, the tubercles can be designed according to a defined preset fundamentally at each start of operation without the need to record previously current measurement data. This is associated in particular with a time saving. Furthermore, a sensor system or at least a part of a sensor system can optionally be omitted.In order to be able to advantageously change the incident front edge of the wing with respect to shape, the skin that can be changed in shape can be guided into an intermediate space bounded by two adjacent stiffening elements. Thus, the end faces of the stiffening elements protruding beyond the articulated partial regions of the deformable skin each define a tubercle extension maximum. The skin that can be changed in shape is displaced behind the original contour of the wing body by a force of the deformation device acting substantially in the inflow direction, in particular by a force pointing from the skin that can be changed in shape into the interior of the wing body. As a result, the end faces of the stiffening elements project beyond the inwardly directed partial regions of the shape-changing skin and define tubercle expansion maxima. Viewed from outside the wing, concave regions of the wing leading edge are produced between two reinforcing elements. The end faces of the stiffening elements form tubercle tips, i.e. tubercle extension maxima.The stiffening elements do not necessarily have to be stationary partial elements of the wing body, but can alternatively be dimensionally stable partial regions of the deformable skin, i.e. partial regions which belong to the deformable skin itself. Such dimensionally stable partial regions of the dimensionally variable skin can likewise form tubercle expansion maxima or optionally tubercle expansion minima. In other words, tube becomings are formed via the skin itself which can be shaped without additional stiffening elements of the wing body being required. Thus, according to one embodiment for the formation of tube becominges, a combination of stiffening elements of the wing body and dimensionally stable partial regions of the skin that can be changed in shape is possible. For example, only every second, third, fourth or x-th tubercle can be formed by an end face of a stiffening element of the wing body, while tubercle lying therebetween can be formed by stiff partial regions of the deformable skin or at least be predetermined with respect to the position thereof.It can be provided that the deformation device is furthermore designed to deflect the skin that can be changed in shape outwards beyond the end faces of the stiffening elements relative to an intermediate space delimited by two adjacent stiffening elements, so that it forms a tubercle extension minimum at the end faces of the stiffening elements. In particular, the end face of the stiffening element can preset the position of the tubercle extension minimum. A tubercle extension maximum belonging to the tubercle extension minimum, i.e. the tubercle tip, extends outwards away from the wing body. For deflecting the skin that can be shaped outwards, the deformation device can exert a force on the skin that can be shaped, which force presses the partial region located between the end faces of the stiffening elements outwards counter to the inflow direction. With respect to the original contour of the wing body (without tubercle), the tubercle tips project beyond the earlier wing contour or the end sides of the reinforcing elements.The front edge of the wing is preferably adaptive in such a way that the end faces of the stiffening elements can form both a tubercle extension maximum and a tubercle extension minimum. In particular, it is possible by means of the deformation device to displace partial regions of the wing body further outwards in the inflow direction or to draw them back in order to form tube becoming tube becomings. By changing a partial region of the skin that can be shaped from a retracted position into a deflected position, a lateral displacement of a tubercle in the span-wise direction of the wing body, i.e. transversely to the inflow direction, takes place, so that the absolute position of one or more tubercle on the wing can be varied in an advantageous manner. This results in a leaf in which not only the shape of the tubercle, in particular its amplitude between the tubercle extension maximum and Tuberkelausdehnungsminimum is adaptive, but rather the absolute position of the tubercle at the leaf leading edge can also be changed.The deformation device preferably has at least one actuator which is assigned to the skin which can be shaped and which exerts a force acting at least partially along the inflow on the skin which can be shaped. In principle, each tubercle can be assigned its own actuator. Alternatively, however, an actuator can be assigned to a plurality of regions of the deformable skin in order to form a plurality of tuberules simultaneously during an actuation. In particular, it is thus proposed that at least one actuator exerts a force on at least two regions of the deformable skin which are separated from one another by a stiffening element in order to form more than one tubercle expansion maximum simultaneously. Furthermore, it can be provided that the skin that can be changed in shape is displaced simultaneously on the one hand by a common actuator on several sections of the front edge, while on the other hand other sections of the front edge exist, on each of which a separate actuator acts.In principle, it is possible for the actuator and / or a plurality of actuators and / or the entire deformation device to be arranged outside the wing, for example on the outside of a fuselage of an aircraft or ship supporting the wing, but it is preferred that at least the at least one actuator is arranged inside the wing body, or is assigned as directly as possible to the front edge of the wing. An electronic system and / or computing device assigned to the actuator can be arranged outside the wing body. The actuator can act directly or indirectly on partial regions of the deformable skin. In particular, mechanical elements of the actuator can engage the deformable skin from the inside, i.e. within the wing body or even within the tubercle. An indirect exertion of force can be effected, for example, by a pressure change within a space bounded by the tubercle.The actuator can be a mechanical actuator and / or an electromechanical actuator and / or a hydraulic actuator and / or a piezoelectric actuator. Furthermore, the actuator can alternatively or additionally have a pump and / or a shape memory material and / or a bistable element. Suitable actuators are, for example, conventional actuators which can cause a pulling or pushing on the shape-changing skin of the wing leading edge. The application of force can be electrical, mechanical, hydraulic, electro-mechanical or electro-hydraulic, and can comprise combinations of this type. In such embodiments, the actuator has a mechanical actuating element which engages the deformable skin. For example, a linearly movable partial element of an actuator, which engages on the skin that can be shaped, can be moved out of an actuator housing and retracted again in order to act on a partial region of the skin that can be shaped. The actuator housing is preferably fastened to a stationary partial region of the wing body, for example to a front spar of the wing. A deformation of the skin that can be changed in shape can furthermore be effected by means of a piezoelectric element, which converts an electrical signal into a change in length that is sufficient to bring about a change in shape of the wing leading edge that is not negligible in terms of flow, i.e. to form a tubercle.Furthermore, actuators containing a shape memory material can be used for forming at least one tubercle or a plurality of tubercle. For example, an actuator may comprise a shape memory alloy (SMA). The actuator can be designed as a rod, wire, tube or flat in the form of a film or plate, and can bring about a pulling and / or pressing on a partial region of the skin that can be shaped. Known shape memory materials contract, for example, in the event of a temperature increase and can thus bring about a force on the shape-changing skin of the wing. Alternatively, shape memory materials exist which expand upon temperature increase, so that a partial region of the shape-changing skin can be displaced outwards, for example, via the original contours of the wing body. Depending on the type of such a shape memory actuator, it is possible for the formation of a tube tubercle for the shape memory actuator to pull the shape-changeable skin of the leading edge downstream or to press it upstream with respect to the direction of the incident flow. Upon a return to the starting position, the shape memory actuator resumes its original starting shape and causes a restoring force on the associated tubercle. If the resilience of the shape memory material is not sufficient to reach the starting position, a supplementary restoring force can additionally act on the skin which can be shaped. For example, this restoring force can be applied by a restoring element such as a restoring spring. The use of an additional restoring element can, however, be omitted if the so-called two-way effect of the shape memory actuator is sufficient to restore the shape-changeable skin itself back into its earlier initial position. Furthermore, it is possible to use rotational shape memory actuators which, for example, exert a torque as a rod element upon heating in order to deform the skin that is variable in shape.In a further embodiment, the wing leading edge itself can consist of a shape memory alloy (SMA) and / or of a shape-changeable skin with additionally embedded and / or externally contacting shape memory elements. As a result of a temperature change of the SMA, the corresponding regions of the wing leading edge can contract or expand-depending on the preset original shape of the SMA-and consequently form tuberules.The shape memory actuator can preferably be heated by electrical current, i.e. by resistance heating. In addition, it is possible to use separate heating elements, for example heating mats, or to heat them inductively. With respect to an aircraft wing, the shape memory actuator may be particularly advantageously heated by the wing de-icing system of the aircraft. Likewise, a heat flow from an engine of the aircraft could be used to heat the actuator.The actuators may also comprise bistable elements. For example, a bistable structure and / or at least one bistable element can be assigned to the actuator in order to keep the shape-changing skin in one or the other position and / or shape without additional energy expenditure. For the transfer from one form to the other or vice versa, energy must then still be supplied from the outside, for example by an electric motor, a pump or others.According to a possible embodiment, the bistable elements can be introduced directly into the shape-changing skin and / or applied to the latter. Alternatively, bistable elements of an external actuator can engage the deformable skin from the outside.Bistable elements have two stable states or one stable and one metastable state, in which these can remain without additional force being applied. For example, this is known from so-called "snack pants". For a changeover process from a first to a second stable state, mechanical energy has to be used. A bistable element can be used for changing the shape of the deformable skin, i.e. for forming a tube tubercle, in such a way that a first stable state is, for example, one in which a partial region of the deformable skin is articulated into an intermediate space bounded by two adjacent stiffening elements of the wing body, so that the stiffening elements form tubercle extension maxima. The second stable state is, for example, the initial state in which no tubercle is yet formed at the front edge of the wing. For the change between the two stable states, a servomotor can act on the bistable element, for example.In addition, locking devices and / or locking devices for the energy-saving retention of a position or a deformation state of the deformable skin or its tubercle can be used. In the form in which the deformable skin is to be held, for example, a locking of the deformable skin is carried out directly or a mechanism effecting the displacement is locked actively. For unlocking, at least slight energy is again required, wherein the skin that can be changed in shape can then be returned to the undeformed state again.For adaptive variation of the blade leading edge, according to a further embodiment, a pump can be used as actuator. The pump can generate a pressure or negative pressure at least within a partial volume of the wing body, which can bring about the change of the shape-changing skin.In particular, an intermediate space, to which two mutually adjacent stiffening elements and the skin that can be shaped adjoin, can be designed as a pressure chamber, wherein a negative pressure in the pressure chamber leads to the skin that can be shaped being deflected into the intermediate space, and wherein an overpressure in the pressure chamber leads to the skin that can be shaped being deflected out of the intermediate space. The leading edge of the vane may be associated with a plurality of pressure chambers or only a single pressure chamber. Moreover, each tubercle may be assigned its own pressure chamber or a plurality of tubercle may be assigned to the same pressure chamber. The positive or negative pressure present in the pressure chamber results in a displacement of the skin that can be changed in shape relative to end faces of the stiffening elements and / or to its own dimensionally stable partial regions of the skin that can be changed in shape. As a result of a pressure increase within the pressure chamber, the deformable skin is deflected outwards. When the pressure chamber is pressurized with a negative pressure, on the other hand, the skin that can be shaped is sucked into the pressure chamber, namely in particular into the intermediate space, which is at least partially delimited by the stiffening elements.If the reinforcing elements are reinforcing elements already present in the wing body, for example shaping partial regions of the wing body, these can preferably be designed such that they are gas-tight at the desired overpressions or suppressions and the defined pressure can thus be held stable within the intermediate space. The pressure chamber is bounded on the one hand by at least one partial region of the deformable skin and on the other hand by stiffening elements of the wing body. Further elements of the wing body can contribute to the gas-tight delimitation of the pressure chamber. The pressure conditions within the one or each pressure chamber can preferably be controlled by means of one or more pumps and an associated control device.According to one embodiment, the entire front edge of the wing body can adjoin only a single pressure chamber or delimit a plurality of pressure chambers which are arranged separately next to one another in the span-wise direction of the wing. Regardless of the number of pressure chambers, not only two but also further stiffening elements can be provided within one and the same pressure chamber, the end faces of which stiffening elements can form a tubercle expansion maximum or a tubercle expansion minimum. In this case, some of the stiffening elements protrude, for example, into the same pressure chamber, but do not restrict it in a gas-tight manner. The pressure chamber adjoining the front edge can thus form not only a single tubercle, but a plurality of tubercle.According to a further embodiment, a plurality of pressure chambers can be provided in the direction of the longitudinal extent of the front edge. This may be advantageous in order to improve the aerodynamic properties of the tubercle. In particular, the formation of a tubercle or a plurality of tubercle takes place, for example, as a result of a reduced pressure. Alternatively, it can be provided that an overpressure is set in the pressure chamber in order to use the end sides of the stiffening elements as tubercle extension minima. If either a negative pressure or an overpressure can be applied to one and the same pressure chamber, the support of the shape-changing skin on the end faces of the stiffening elements leads to a definition of either tubercle expansion maxima or tubercle expansion minima. In the event of a reversal from a negative pressure to a positive pressure, a change in position of the tubercle or tubercle in the direction of the longitudinal extent of the front edge of the wing body is also effected simultaneously.In particular, if a plurality of separate pressure chambers are formed for the adaptive shape change of the front edge, the tubercle assigned to the respective pressure chamber can assume an individual size and / or shape. As a result, the leading edge can be changed particularly individually and in a situation-related manner. For example, the number of tubercles at the front edge can also be varied by one or more of the pressure chambers having ambient pressure and in particular not forming any tubercle, while one pressure chamber or more other pressure chambers are subjected to reduced pressure, so that the skin which can be shaped is drawn into the relevant pressure chamber there.In conjunction with one or more pressure chambers, it can also be provided that the skin which can be changed in shape itself has dimensionally stable subareas which can form a tubercle expansion maximum or tubercle expansion minimum, so that the formation of a plurality of tubercle is also possible if the same pressure chamber has, for example, only two delimiting stiffening elements.The stiffening elements can be, in particular with respect to all the embodiments mentioned, shaping partial regions of the wing body or elements arranged within the wing body, in particular longitudinal struts of the wing body. The shaping stiffening elements directly influence the outer shape of the wing, for example as outer housing regions which form at least partial contour regions of the front edge and / or of one side of the wing. Elements arranged within the wing body can be in particular profile elements of the wing body aligned parallel or substantially parallel to the inflow, which profile elements fulfil stability tasks. Since aircraft wings or, for example, rotor blades of wind turbines are lightweight components, such profile elements are preferably aligned longitudinally, in particular substantially parallel to, the incident flow in order to keep the applied forces on the longitudinal sides low.Within the scope of the invention, it can be provided in particular that the wing is an aircraft wing, in particular a wing of the wing structure. The wing can furthermore be an elevator, a rudder or a so-called "winglet". According to a further embodiment, the reinforcing elements of the wing body can comprise a composite material, in particular a glass fibre laminate and / or carbon laminate. These materials are suitable in particular for lightweight construction. Alternatively or additionally, metals can be advantageous, in particular aluminum and / or steel. Other metals can likewise be used in principle and their advantages depend on the type of application.With respect to the skin that can be shaped, it is proposed that it has an elastic material, in particular rubber and / or rubber. Furthermore, the shape-changing skin may have a hybrid structure of an elastic material and a composite material and / or a flexible composite structure. A composite material and a composite structure are advantageous because a deformable skin, which for example only consists of rubber and / or rubber, could be deformed solely by the applied aerodynamic load with at the same time insufficient inherent rigidity. In particular, a hybrid structure made of a composite material and an elastic material is recommended, wherein the materials can be arranged alternately next to one another, for example, in parallel strips. In addition, a non-hybrid construction from a pure composite structure is conceivable, wherein in this case the shape-changeable regions of the composite structure must be designed as flexible as possible in order to enable a shape change.Advantageous further developments of the invention are evident from the patent claims, the description and the drawings.The advantages of features and combinations of a plurality of features mentioned in the description are merely exemplary and can be applied alternatively or cumulatively without the advantages necessarily having to be achieved by embodiments according to the invention.With regard to the disclosure content-not the scope of protection-of the original application documents and of the patent the following applies: Further features can be taken from the drawings-in particular the geometries shown and the relative dimensions of a plurality of components with respect to one another and their relative arrangement and operative connection. The combination of features of different embodiments of the invention or of features of different patent claims is likewise possible deviating from the selected relations of the patent claims and is hereby excited. This also relates to features which are illustrated in separate drawings or are mentioned in the description thereof. These features can also be combined with features of different patent claims. Features listed in the patent claims can likewise be omitted for further embodiments of the invention, but this does not apply to the independent patent claims of the issued patent.The features mentioned in the patent claims and the description should be understood in terms of their number such that exactly this number or a greater number than the mentioned number is present, without the need for explicit use of the adverb "at least". Thus, for example, when an element is mentioned, this is to be understood as meaning that exactly one element, two elements or more elements are present. The features mentioned in the patent claims can be supplemented by further features or be the only features that the subject matter of the respective patent claim has.The reference numerals included in the claims do not represent a limitation on the scope of the subject matter protected by the claims. They are intended merely to make the claims more readily understood.BRIEF DESCRIPTION OF THE FIGURESThe invention is explained and described in more detail below with reference to preferred exemplary embodiments shown in the figures. FIG. 1 shows a plan view of a front partial region of an aircraft, the wings of which have a front edge with tuberkes. FIG. 2 shows an enlarged portion of the leading edge of the wing of FIG. 1. FIG. 3 shows a partial area of the front edge, which forms a tubercle extension minimum, in a three-dimensional view. FIG. 4 shows a longitudinal section through the partial region according to FIG. 3. FIG. 5 shows a partial region of the front edge, which forms a tubercle extension maximum, in a three-dimensional view. FIG. 6 shows a plan view of a partial area of a front edge with several pressure chambers and tube becomings. FIG. 7 shows a further embodiment of a variable sub-region of a wing with an actuator. FIG. 8 shows a further embodiment of a variable sub-region of a wing with an actuator and a restoring element. FIG. 9 shows a plan view of a partial region of a front edge of a wing according to a further embodiment.DESCRIPTION OF THE FIGURESFig. 1 discloses an aircraft 13 having a pair of wings 1, here winged structures. The wings 1 have a leading edge 4 which is oriented transversely to an incident flow 3 during a forward movement of the aircraft 13. The illustrated angle between the inflow 3 and the front edge 4 is merely exemplary. It is understood that a longitudinal direction L of the leading edge 4 can alternatively assume a different angle to the incident flow 3. In particular, "transversely to the inflow 3" can be understood to mean an angle between the longitudinal direction L and the direction of the inflow 3, which is between 90° and 135°, preferably between 100° and 125°. However, other angles are alternatively possible.The invention is explained here merely by way of example on the basis of an aircraft 13 or on the basis of aircraft wings. The embodiments shown can, however, also be transferred accordingly to wings 1 of other objects exposed to an incident flow 3, for example to helicopters, wind power installations or their rotor blades, compressors, turbines and / or ships.The invention can also have significance in wings 1, which are parts of tail tail units, rudders or winglets of an aircraft 13. Furthermore, wings 1 designed according to the invention can be used in other aircraft, for example unmanned, remote-controlled aircraft, such as drones in particular.The wing 1 designed according to the invention has a wing body 2 which here has a front spar 15 as a load-bearing component, for example (see FIGS. 3 to 9 ). The front spar 15 is substantially beam-shaped in the longitudinal direction L of the wing 1 and has the task of absorbing the transverse forces and bending moments resulting from lift, air currents and inertial forces.A plurality of stiffening elements 8 extend transversely to the front spar 15, and these stiffening elements 8 can in principle determine the outer shape of the wing body 2 and / or be arranged within the wing body 2, so that these elements return behind a contour of the wing body 2 that is visible from the outside.Laid over end faces 10 of these stiffening elements 8 (see FIGS. 3 to 9 ) is a skin 9 which can be shaped and forms the front edge 4 of the wing 1 according to FIGS. 1 and 2. In FIG. 1, this leading edge 4 is adaptively modified with respect to its outer shape in such a way that it has a multiplicity of tube becomings 5 which form a distinct wave structure of the leading edge 4. The deformation device according to the invention for influencing the shape of the leading edge 4 ("morphing leading edge 4") will be described in more detail later with reference to FIGS. 3 to 9.The deformation device can be controlled as a function of measurement data of one or more sensors. For example, the wing 1 or the object having the wing 1 (for example aircraft 13, wind turbine, turbine etc.) can have a sensor which detects operating states of the aircraft 13 (or of the other objects) and, if appropriate, ambient parameters. Depending on this, a change in shape of the leading edge 4 of the wing 1 can be controlled, for example by means of an evaluation and control device of the deformation device and / or of the aircraft 13. Tubercles 5 can be extended or shaped in situ at the leading edge 4 in order to positively influence the flow conditions at the wing 1, in particular the lift-air resistance ratio in an aircraft 13. With respect to an aircraft wing, this may be advantageous, for example, at low flight speeds and / or during a takeoff and / or landing operation.FIG. 2 shows an enlarged partial region of the front edge 4 of the wing 1 according to FIG. 1, which partial region has three tubercles 5 which are arranged one behind the other in the longitudinal direction L of the front edge 4 and each have a tubercle extension maximum 6 and two tubercle extension minima 7. In FIGS. 1 and 2, the tubercles 5 of the front edge 4 are formed almost equidistantly and with a similar size and shape. However, this is not necessarily necessary, rather tubercles 5 can alternatively be formed which have mutually different dimensions and / or shapes and / or slopes. In particular, tubercles 5 can exist whose distance between tubercle extension maximum 6 and tubercle extension minimum 7 is smaller than in the case of an adjacent tubercle 5.FIGS. 3 to 5 show a partial region of the front edge 4, on which a tubercle 5 can be formed in a situationally controlled manner. The structure is such that the partial region is bounded by two substantially parallel-oriented stiffening elements 8, on the end sides 10 of which the skin 9 that can be shaped is supported. The reinforcing elements 8 are profile elements of the wing 1, which influence the outer shape of the wing body 2. However, this is not absolutely necessary in order to achieve the mode of operation described below. Here, the two reinforcing elements 8, together with a partial region of the front spar 15 of the wing body 2 and a partial region of the deformable skin 9, form an intermediate space 11 which can be subjected to defined pressure in the manner of a pressure chamber. With the aid of a pump (as at least part of the deformation device), for example, it is possible to influence the pressure existing in the intermediate space 11 in such a way that it represents a negative pressure or positive pressure with respect to the ambient pressure of the blade 1. The pump is preferably controlled as a function of measurement parameters. These measurement parameters can be data detected by sensors or data which were determined earlier, for example in the context of test operations (test flights) or laboratory tests, and have proven to be generally valid for a specific operating situation of the wing 1. For example, the wing 1 can always be varied in shape during a landing approach or a take-off process in a defined, always identical manner with respect to its leading edge 4.According to FIG. 3, a negative pressure is generated in the intermediate space 11. This has the result that the skin 9 which can be changed in shape is deflected into the intermediate space 11 delimited by the two adjacent stiffening elements 8, with the result that the end faces 10 of the stiffening elements 8 each define a tubercle expansion maximum 6. Between these tubercle extension maxima 6 there results a tubercle extension minimum 7 which is set back with respect to the plane of the tubercle extension maxima 6.FIG. 4 shows a side view of the partial region according to FIG. 3 The tubercle extension minimum 7 is moved back into the intermediate space 11 of the wing 1 with respect to the tubercle extension maxima 6, so that the tubercle extension minimum 7 is at a smaller distance from the front spar 15 than the tubercle extension maxima 6.FIG. 5, in contrast, shows a situation in which there is an overpressure in the intermediate space 11 so that the skin 9 that can be shaped bulges convexly outwards and the end sides 10 of the stiffening elements 8, on which the skin 9 that can be shaped is supported, form tubercle extension minima 7. The tubercle extension maximum 6 forms that partial region of the deformable skin 9 or tubercle 5 which has the greatest distance from the front spar 15.FIG. 6 shows an embodiment in which a plurality of intermediate spaces 11 lying next to one another are formed along the longitudinal direction L of the leading edge 4 of the wing 1. Each intermediate space 11 forms a separate pressure chamber, which is independent of the remaining intermediate spaces 11 and has a specific individual pressure. Each intermediate space 11 can be adjusted, for example, by a separate pump or a single pump with corresponding control with respect to the respective pressure in order to form outwardly pointing tubercles 5 in the region of the stiffening elements 8. The intermediate spaces 11 have, merely by way of example, substantially identical negative pressures, so that substantially identically shaped and identically sized tuberules 5 are obtained. The end faces 10 of the stiffening elements 8 define the tubercle expansion maxima 6.Although not shown in FIG. 6, the intermediate spaces 11 can alternatively be intermediate spaces 11 of a common pressure chamber that are fluidically connected, i.e. are not separated from one another in a gas-tight manner. In this case, the stiffening elements 8 are designed and / or arranged and / or connected to the front spar 15 in such a way that no gas-tight separation results. In this case, the stiffening elements 8 serve primarily for providing load-bearing and / or stabilizing properties of the wing body 2 and for providing the end faces 10 on which the skin 9 that can be shaped is supported, so that tuberules 5 can form.FIGS. 7 and 8 show further possibilities for changing the shape of the front edge 4 of a wing 1. The actuators 12 shown are each fastened on the one hand to an inner side of the deformable skin 9 and on the other hand to the front spar 15.The respective actuator 12 can be a linear motor, a piezoelectric element or the like. Furthermore, it is possible for the actuator 12 to have a shape memory material or a bistable element. The actuator 12 is configured to displace the shape-changing skin 9 back and forth.According to FIG. 7, the actuator 12 is a linear motor which can be controlled both into an extended position and into a retracted position. In the retracted position shown by dashed lines, a partial region of the skin 9 that can be shaped is displaced back in the direction of the front spar 15, i.e. into an intermediate space 11, so that a tubercle extension minimum 7 is formed between adjacent stiffening elements 8 of the wing 1. The end faces 10 of the stiffening elements 8 each form a tubercle extension maximum 6 at the front edge 4 of the wing 1. In this case, the front edge 4 can have a plurality of such actuators 12. The actuators 12 can be controlled completely independently of one another, in particular such that adjacent tubercles 5 have different shapes and / or sizes. In one embodiment, however, an individual actuator 12 can be connected to a plurality of regions of the deformable skin 9, for example via a corresponding active device (not shown in FIG. 7 ), such that the actuator 12 can form a plurality of tubercles 5 at once.FIG. 8 shows an actuator 12 designed as a shape memory actuator, which contains a shape memory material in the form of a rod or wire. The shape memory actuator contracts when heated, so that the shape-changing skin 9 is pulled in the direction of the front spar 15. The heat for heating the shape memory material can be generated, for example, electrically by resistance heating or can be provided, for example, by an engine or a defrosting device of the aircraft 13 having the wing 1. In order to bring about the restoring, i.e. the stretching of the actuator 12, a restoring element 16 is preferably provided, which is here a helical spring which exerts a stretching force on the actuator 12, i.e. the rod or wire. Alternatively, it can be provided that a shape memory material expands upon heating and contracts upon cooling.Depending on the type of actuator 12 used, the deformable skin 9 can thus be moved downstream, i.e. in the direction of the front spar 15, or upstream, i.e. away from the front spar 15, by changing the temperature. As a result of a subsequent, oppositely directed temperature change of the shape memory material, the actuator 12 either deforms back into its initial state by itself (two-way effect) or a restoring force of the separate restoring element 16 is provided in a supporting manner. In this case, the skin 9 that can be changed in shape can provide a restoring force which either acts in addition to the force of the restoring element 16 or alternatively is even the exclusive restoring force of the embodiment.In a similar manner, bistable elements can be used as actuators 12 which can assume two stable states (or a stable and a metastable state). In these states, the actuator 12 can remain without additional force being applied. Only for a change from a first stable state to a second stable or metastable state is a force application then necessary. This can be provided, for example, by an electric motor, a piezoelectric element or the like. In a further embodiment, not the actuator 12 but the shape-changing skin 9 can be embodied in a bistable manner, and / or the shape-changing skin 9 contains bistable elements and / or a combination of a bistable actuator 12 and a bistable shape-changing skin 9.FIG. 9 finally shows a further embodiment in which the skin 9 that can be changed in shape itself has dimensionally stable partial regions 14. These dimensionally stable partial regions 14 can form a tubercle expansion maximum 6 or a tubercle expansion minimum 7 due to their stabilizing property. It is not necessary for these dimensionally stable partial regions 14 to be supported on a stiffening element 8 of the wing body 2. Rather, the flexibility of the deformable skin 9 is interrupted by these dimensionally stable sub-regions 14, so that the more flexible sub-regions of the deformable skin 9 lying next to the dimensionally stable sub-region 14 can be pulled in the direction of the front spar 15 or can be directed away from the latter when a force acts on these sub-regions.The section of the wing body 2 shown in FIG. 9 has, for example, three spaces 11 which are separated from one another in a gas-tight manner and each form a pressure chamber on their own. Here, all intermediate spaces 11 have a negative pressure, so that the end sides 10 of the reinforcing elements 8 each specify tubercle expansion maxima 6 of the skin 9 that can be shaped, and tubercle expansion minima 7 are formed between these tubercle expansion maxima 6. The dimensionally stable partial region 14 of the dimensionally variable skin 9 also forms a tubercle expansion maximum 6 due to the negative pressure in the central intermediate space 11. Tubercle 5 thus arise on the front edge 4 of all three intermediate spaces 11 The tubercle 5 have different amplitudes from one another, i.e. the distances between the tubercle extension minimum 7 and the tubercle extension maximum 6 are different from one another. The tubercles 5 are formed substantially smaller in the central intermediate space 11 than in the outer intermediate spaces 11, in which the skin 9 that can be shaped is supported on the end sides 10 of the stiffening elements 8.LIST OF REFERENCE CHARACTERS1 Wing 2 Wing body 3 Incident flow 4 Front edge 5 Tubercle 6 Tubercle expansion maximum 7 Tubercle expansion minimum 8 Stiffening element 9 Shape-changing skin 10 Front side 11 Intermediate space 12 Actuator 13 Aircraft 14 Dimensionally stable subregion 15 Front spar 16 Restoring element L Longitudinal direction

Claims

Wing (1) with a wing body (2) which has a front edge (4) which extends transversely relative to an inflow (3) and which has, in its longitudinal direction (L) oriented transversely to the inflow (3), a plurality of tube becomings (5) which can be shaped adjacent to one another and each has a tubercle extent maximum (6) pointing in the direction of the inflow (3), wherein the wing body (2) has stiffening elements (8) which are oriented along the inflow (3) and terminate at the front edge (4) with end faces (10), a skin (9) which can be shaped and a deformation device for deforming the skin (9) which can be shaped, characterized in that the deformation device is designed in such a way and in that the skin (9) which can be shaped is supported on the end faces (10) of the stiffening elements (8) in such a way, that a tube tube extension maximum (6) can be formed on each of the end faces (10) of the stiffening elements (8).Wing (1) according to claim 1, wherein the deformation device is configured to deflect the skin (9) that can be changed in shape into an intermediate space (11) delimited by two mutually adjacent stiffening elements (8), so that the end sides (10) of the stiffening elements (8) each define a tubercle extension maximum (6).Wing (1) according to one of the preceding claims, wherein the deformation device is also designed to deflect the skin (9) which can be changed in shape outwards beyond the end faces (10) of the stiffening elements (8) relative to an intermediate space (11) delimited by two mutually adjacent stiffening elements (8), such that a tubercle extension minimum (7) can be formed in each case on the end faces (10) of the stiffening elements (8).Wing (1) according to one of the preceding claims, wherein the deformation device has at least one actuator (12) which is assigned to the deformable skin (9) and which exerts a force acting at least partially along the inflow (3) on the deformable skin (9), wherein in particular at least one actuator (12) exerts a force on at least two regions of the deformable skin (9) which are separated from one another by a stiffening element (8) in order to form more than one tubercle expansion maximum (6) simultaneously.The blade (1) according to claim 4, wherein the actuator (12) is a mechanical actuator and / or an electromechanical actuator and / or a hydraulic actuator and / or a piezoelectric actuator and / or comprises a pump and / or a shape memory material and / or a bistable element.The wing (1) according to any one of the preceding claims, wherein the shape-changeable skin (9) comprises at least one piezo element and / or a shape memory material and / or a bistable element.The wing (1) according to any one of the preceding claims, wherein an intermediate space (11), to which two mutually adjacent stiffening elements (8) and the shape-changeable skin (9) are adjacent, is formed as a pressure chamber, wherein a negative pressure in the pressure chamber leads to a deflection of the shape-changeable skin (9) into the intermediate space (11), and wherein an overpressure in the pressure chamber leads to a deflection of the shape-changeable skin (9) out of the intermediate space (11).The wing (1) according to claim 7, wherein the leading edge (4) of the wing (1) is assigned one or more pressure chambers and / or wherein a single pressure chamber is assigned to a plurality of tube becomings (5) of the deformable skin (9) and / or wherein a plurality of intermediate spaces (11) are partial regions of the same pressure chamber.Wing (1) according to one of the preceding claims, wherein the skin (9) which can be changed in shape has dimensionally stable partial regions (14) which can form a tubercle extension maximum (6) or tubercle extension minimum (7).Wing (1) according to one of the preceding claims, wherein the stiffening elements (8) are shaping partial regions of the wing body (2) or elements, in particular longitudinal struts, arranged within the wing body (2).Wing (1) according to one of the preceding claims, wherein the wing (1) is a wing (1), in particular a frame structure wing, of an aircraft and / or wherein the stiffening elements (8) of the wing body (2) have a composite material, in particular glass fibre and / or carbon laminate, and / or a metal, in particular aluminium and / or steel, and / or wherein the shape-changeable skin (9) has an elastic material, in particular rubber and / or rubber and / or a hybrid structure of an elastic material and a composite material and / or a flexible composite structure.

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