Patent Description:
From document <CIT> a wing is known which comprises a drooping leading edge device, in which the leading edge structure that droops is pivotally mounted, by a single pivot inside the wing, upon the front spar structure of the wing and is of substantially constant shape. A gap which would otherwise open up between the upper skin of the main part of the wing and the upper skin of the leading edge structure, when the leading edge droops, is filled by an upper flexible skin section secured to the main part of the wing and extending forward first into contiguity with the rear edge of the upper skin of the leading edge structure and then inside said leading edge structure. At the underneath of the wing, a rear flexible portion of the lower skin of the leading edge device extends back to meet the forward edge of the lower skin of the main part of the wing. When the leading edge droops, the profile of the upper flexible skin section is controlled by links inside the structure which are hinged at their upper ends on the upper flexible skin section and at their lower ends on inner structure of the leading edge device.

From document <CIT> a wing is known which comprises a wing leading edge high-lift generating device in the form of a spanwise slat segment having both an upper and a lower surface, faired into an airfoil configured leading edge of a relatively stationary portion of the wing therebehind and movable with respect thereto by a downwardly extending hinge arm pivotally related to a downwardly extending hinge bracket from the wing within a fairing structure which also includes an actuator between the hinge arm and bracket for biasing the hinge arm connected to the leading edge device away from and downwardly with respect to the hinge bracket of the wing about the pivotal connection therewith.

The wing of the present invention is defined according to appended claim <NUM>, and comprises a main wing and a leading edge high lift assembly movable relative to the main wing to increase lift of the wing. The leading edge high lift assembly comprises a high lift body and a connection assembly. The high lift body is preferably a droop high lift body referred to as droop nose, droop leading edge, droop flap or slat, in particular sealed slat. The connection assembly is configured for connecting the high lift body to the main wing, in particular to the leading edge of the main wing, in such a way that the high lift body is movable relative to the main wing between a stowed position and a deployed position. The stowed position relates to a position where the wing profile has a lower curvature and might also be referred to as straight position, normal position, cruise position or retracted position, while the deployed position relates to a position where the wing profile has a higher curvature and might also be referred to as drooped position, landing position or extended position.

The connection assembly comprises at least one rotation element, such as a rotation rod or a part of the high lift body structure, that is mounted to the high lift body and that is mounted to the main wing rotatably about an axis of rotation. The rotation element is mounted to the high lift body directly or indirectly and in a fixed or rotatable manner, preferably in a fixed, non-rotatable manner, e.g. by a hinge between the end of the rotation element and the high lift body and additionally by a fixing link that is hinged to the rotation element and that is hinged to the high lift body spaced apart from the rotation element, so that a relative rotation of the high lift body and the rotation element is prevented. The axis of rotation is preferably arranged at a lower part of the main wing near or at a lower skin and preferably extends in parallel to the span direction and/or in parallel to the extension of leading edge along the wing, so that the high lift body is preferably rotated about the axis of rotation when moved between the stowed position and the deployed position.

The main wing comprises an upper skin panel for contact with an ambient flow on an upper side of the main wing, and a lower skin panel for contact with an ambient flow on a lower side of the main wing. The upper skin panel has a leading edge portion in the area of a leading edge of the main wing and facing the high lift body. The upper skin panel and the lower skin panel might be joined at the leading edge of the main wing, or might have an open end at the leading edge of the main wing, where they might be connected or supported against each other via a front spar.

The high lift body extends between a leading edge and a trailing edge, the trailing edge preferably in parallel to the axis of rotation. The trailing edge of the high lift body is configured to move, preferably slide, along the outer surface of the leading edge portion of the upper skin panel of the main wing, preferably in contact with the outer surface of the leading edge portion of the upper skin panel, when the high lift body is moved between the stowed position and the deployed position. The contact might generally seal the high lift body to the upper skin panel for essential flow, but it might also be formed such that a leakage flow is permitted. It is also possible that the trailing edge of the high lift body moves along the outer surface of the leading edge portion of the upper skin panel of the main wing out of contact with the outer surface of the leading edge portion of the upper skin panel, when the high lift body is moved between the stowed position and the deployed position, so that a defined gap is formed between the trailing edge of the high lift body and the outer surface of the leading edge portion of the upper skin panel during movement of the high lift body, thereby allowing a defined leakage flow or even essential flow through the gap.

Similar wings are known in the art. By increasing the curvature of the wing profile when the high lift body is moved to the deployed position, lift of the related aircraft can be increased, in particular to allow approach and landing with lower speed and on shorter runways. High lift assemblies with a drooping, downward rotating high lift body that is sealed to the leading edge portion of the upper skin panel, such as droop nose assemblies, related to simple and effective high lift devices. However, some known devices cause a pressure peak in the area of the transition between the trailing edge of the high lift body and the leading edge portion of the upper skin panel.

Therefore, the object of the present invention is to provide a wing causing a smooth pressure profile along its upper skin panel.

This object is achieved in that the leading edge portion of the upper skin panel is configured to be elastically deformed, in particular bent towards the lower skin panel, when the high lift body is moved from the stowed position to the deployed position. In such a way, a smooth transition from the trailing edge of the high lift body to the upper skin panel can be achieved avoiding small and discontinuous curvature radii. This results in a smooth pressure profile along the upper skin panel without undesired pressure peaks.

According to a preferred embodiment, the leading edge portion of the upper skin panel is configured to be elastically deformed, when the high lift body is moved from the stowed position to the deployed position, by at least one link element that is mounted, preferably rotatably mounted, preferably at one end, to the rotation element and that is, preferably at the other end, mounted to, preferably rotatably mounted to, the leading edge portion of the upper skin panel. When the rotation element rotates downwards to move the high lift body into the deployed position, the link element mounted to the rotation element pulls the leading edge portion of the upper skin panel downwards, too. When the rotation element rotates upwards to move the high lift body back into the stowed position, the link element pushes the leading edge portion of the upper skin panel back upwards into the undeformed state. By such a link element the curvature of the leading edge portion of the upper skin panel can be precisely adapted to form the desired pressure profile.

Additionally or alternatively, it is preferred that the leading edge portion of the upper skin panel is configured to be elastically deformed, when the high lift body is moved from the stowed position to the deployed position, by at least one rope element that is attached, preferably at one end, to the rotation element and that is, preferably at the other end, attached to the leading edge portion of the upper skin panel. When the rotation element rotates downwards to move the high lift body into the deployed position, the rope element attached to the rotation element pulls the leading edge portion of the upper skin panel downwards, too. When the rotation element rotates upwards to move the high lift body back into the stowed position, the elastic properties of the upper skin panel move the leading edge portion of the upper skin panel back upwards into the undeformed state. By such a rope element the curvature of the leading edge portion of the upper skin panel can be precisely adapted to form the desired pressure profile.

Additionally or alternatively, it is preferred that the leading edge portion of the upper skin panel is configured to be elastically deformed by the trailing edge of the high lift body moving along and contacting, preferably sliding over and continuously contacting, preferably pressing onto, an outer surface of the leading edge portion of the upper skin panel, when the high lift body is moved from the stowed position to the deployed position. When the rotation element rotates downwards to move the high lift body into the deployed position, the trailing edge of the high lift body mounted in a fixed or defined position relative to the rotation element pushes the leading edge portion of the upper skin panel downwards, too. When the rotation element rotates upwards to move the high lift body back into the stowed position, the elastic properties of the upper skin panel move the leading edge portion of the upper skin panel back upwards into the undeformed state. The trailing edge of the high lift body preferably has a defined stiffness to achieve the desired deformation of the leading edge portion of the upper skin panel. By the trailing edge of the high lift body deforming the leading edge portion of the upper skin panel the curvature of the leading edge portion of the upper skin panel can be precisely adapted to form the desired pressure profile in a very simple manner.

According to the present invention, the wing comprises a rotating actuator for driving the rotation element about the axis of rotation. Such a rotating actuator is a simple and effective way to drive the high lift body.

In examples not according to the present invention, the rotary actuator is mounted, preferably fixedly mounted, to the main wing and has a rotating drive arm linked to the rotation element by a drive link that is, preferably at one end, rotatably mounted to the drive arm and that is, preferably at the other end, rotatably mounted to the rotation element. This results in a simple and effective actuator.

According to the present invention, however, the rotary actuator comprises a first rotating arm and a second rotating arm rotating in opposite directions about a common axis. The first rotating arm is rotatably mounted to the main wing, and the second rotating arm is rotatably mounted to the rotation element or to the high lift body. In such a way, the common axis is displaced when the actuator is actuated. This results in a simple and effective actuator.

According to a preferred embodiment, at least one stiffener is provided at the leading edge portion of the upper skin panel. The stiffener extends in a span direction, preferably in parallel to the axis of rotation and/or in parallel to the trailing edge of the high lift body. By such a spanwise stiffener deflection of the leading edge portion of the upper skin panel in the span direction can be reduced, in particular between different rotation elements or different connection assemblies in the span direction, if present.

In particular, it is preferred that the stiffener is formed separately from the upper skin panel and is attached to an inner surface of the leading edge portion of the upper skin panel. Preferably, the stiffener has an angled profile including a flange element resting against the inner surface of the leading edge portion of the upper skin panel, and a web element extending angled to the flange element and away from the inner surface of the leading edge portion of the upper skin panel. Such an angled profile might be an L-, C-, T-, Z-, or I-profile. Such a stiffener is lightweight, simple to install, and provides an effective stiffening.

Alternatively, it is preferred that the stiffener is formed integral with the leading edge portion of the upper skin panel. For example, the stiffener might be formed by bending a part of the leading edge portion of the upper skin panel made of a metal material, or might be moulded as part of the leading edge portion of the upper skin panel made of a fiber reinforced plastic material. Such an integral stiffener provides a simple form and requires no extra parts.

It is also preferred that the link element and/or the rope element is attached to the leading edge portion of the upper skin panel via the stiffener or in the area of the stiffener. By the attachment to the stiffener with a defined stiffness a defined contact or gap between the trailing edge of the high lift body and the outer surface of the leading edge portion of the upper skin panel can be precisely adjusted as desired. Alternatively, the link element might also be attached to the link element and/or the rope element in a position spaced from the attachment or from the area of the stiffener.

It is further preferred that the extension of the stiffener normal to the leading edge portion of the upper skin panel varies in the span direction. In such a way, the stiffness of the stiffener can be adapted as required in the span direction.

In particular, it is preferred that the extension of the stiffener normal to the leading edge portion of the upper skin panel varies in the span direction in such a way that a maximum extension is in the area of the attachment of the link element and/or the rope element, while the extension is decreasing, preferably linearly decreasing, in the span direction with increasing distance from the area of the attachment of the link element and/or the rope element. Likewise, a minimum extension is located between, preferably centrally between, the link elements or rope elements of each two spanwise neighboring connection assemblies or rotation elements. In such a way, the stiffness of the stiffeners is distributed in the span direction such that the highest stiffness is present in the attachment area of the link element or rope element.

According to a further preferred embodiment, the leading edge portion of the upper skin panel has a thickness varying in a chord direction, to adapt the curvature of the leading edge portion of the upper skin panel when in the deformed state. In such a way, the thickness of the leading edge portion of the upper skin panel can be used to tailor the curvature of the upper skin panel in the deformed state, i.e. when the high lift body is in the deployed position. Preferably, the thickness of the leading edge portion of the upper skin panel varies analogue to the bending moment resulting from elastic deformation of the leading edge portion of the upper skin panel, preferably in such a way that the varying bending stiffness along the chord direction of the leading edge portion of the upper skin panel, resulting from the varying thickness, compensates the bending moment.

In particular, it is preferred that the thickness of the leading edge portion of the upper skin panel increases linearly or essentially linearly in the chord direction downstream, preferably from the leading edge downstream. In such a way, the bending stiffness of the leading edge portion of the upper skin panel in the chord direction can be adapted to compensate the bending moment resulting from elastic deformation of the leading edge portion of the upper skin panel.

Additionally or alternatively, it is preferred that the leading edge portion of the upper skin panel is made of a fiber reinforced plastic having a varying laminate lay-up in the chord direction, to adapt the curvature of the leading edge portion of the upper skin panel when in the deformed state. In such a way, the laminate lay-up of the leading edge portion of the upper skin panel can be used to tailor the curvature of the upper skin panel in the deformed state, i.e. when the high lift body is in the deployed position. Preferably, the laminate lay-up of the leading edge portion of the upper skin panel varies analogue to the bending moment resulting from elastic deformation of the leading edge portion of the upper skin panel, preferably in such a way that the varying bending stiffness along the chord direction of the leading edge portion of the upper skin panel, resulting from the varying laminate lay-up, compensates the bending moment. Preferably, the laminate lay-up of the leading edge portion of the upper skin panel increases linearly in the chord direction downstream, preferably from the leading edge downstream.

Additionally or alternatively, it is preferred that the leading edge portion of the upper skin panel is provided with at least one reinforcement element, preferably attached to the inner surface of the upper skin panel, extending in the chord direction to vary the bending stiffness of the leading edge portion of the upper skin panel along the chord direction, to adapt the curvature of the leading edge portion of the upper skin panel when in the deformed state. The reinforcement element might itself have a bending stiffness constant or varying in the chord direction. In such a way, the reinforcement element can be used to tailor the curvature of the upper skin panel in the deformed state, i.e. when the high lift body is in the deployed position. Preferably, the reinforcement element is configured such that the bending stiffness of the leading edge portion of the upper skin panel varies in the chord direction analogue to the bending moment resulting from elastic deformation of the leading edge portion of the upper skin panel, in order to compensate the bending moment. Preferably, the reinforcement element is configured such that the bending stiffness of the leading edge portion of the upper skin panel increases linearly in the chord direction downstream, preferably from the leading edge downstream.

According to a further preferred embodiment, the leading edge high lift assembly comprises a further connection assembly spaced from the connection assembly in the span direction and preferably formed as the connection assembly. Preferably at least two spaced connection assemblies are provided to carry each high lift body. Each connection assembly might also comprise more than one rotation element. In such a way, a stable hold and movement of the high lift body is achieved.

A further aspect of the invention relates to an aircraft according to appended claim <NUM>, which comprises the wing according to any of the afore-described embodiments. Features and effects described above in connection with the wing apply vis-a-vis also to the aircraft.

Preferred embodiments of the present invention are explained hereinafter in more detail by means of a drawing. The drawing shows in.

In Fig. an example of an aircraft <NUM> which may be constructed according to the present invention is illustrated. The aircraft <NUM> comprises a fuselage <NUM>, wings <NUM>, a vertical tail plane <NUM> and a horizontal tail plane <NUM>. <FIG> show in more detail several examples of the wings <NUM>.

<FIG> shows a first example of the wing <NUM> not according to the invention, but which may be useful for understanding aspects thereof. The wing <NUM> comprises a main wing <NUM> and a leading edge high lift assembly <NUM> movable relative to the main wing <NUM> to increase lift of the wing <NUM>. The leading edge high lift assembly <NUM> comprises a high lift body <NUM> and a connection assembly <NUM>. The high lift body <NUM> is a droop high lift body also referred to as droop nose, droop leading edge, droop flap or slat, in particular sealed slat. The connection assembly <NUM> is configured for connecting the high lift body <NUM> to the leading edge of the main wing <NUM> in such a way that the high lift body <NUM> is movable relative to the main wing <NUM> between a stowed position and a deployed position. The stowed position relates to a position where the wing profile has a lower curvature, while the deployed position relates to a position where the wing profile has a higher curvature.

The connection assembly <NUM> comprises at least one rotation element <NUM> that is mounted to the high lift body <NUM> and that is mounted to the main wing <NUM> rotatably about an axis of rotation <NUM>. The rotation element <NUM> is mounted to the high lift body <NUM> in a fixed, non-rotatable manner by a hinge <NUM> arranged between the end of the rotation element <NUM> and the high lift body <NUM>, and additionally by a fixing link <NUM> that is hinged to the rotation element <NUM> and that is hinged to the high lift body <NUM> spaced apart from the rotation element <NUM>, so that a relative rotation of the high lift body <NUM> and the rotation element <NUM> is prevented. The axis of rotation <NUM> is arranged at a lower part of the main wing <NUM> near or at a lower skin and preferably extends in parallel to a span direction <NUM> and in parallel to the extension of leading edge along the wing <NUM>, so that the high lift body <NUM> is rotated about the axis of rotation <NUM> when moved between the stowed position and the deployed position.

The main wing <NUM> comprises an upper skin panel <NUM> for contact with an ambient flow on an upper side of the main wing <NUM>, and a lower skin panel <NUM> for contact with an ambient flow on a lower side of the main wing <NUM>. The upper skin panel <NUM> has a leading edge portion <NUM> in the area of a leading edge of the main wing <NUM> and facing the high lift body <NUM>. The upper skin panel <NUM> and the lower skin panel <NUM> have an open end <NUM> at the leading edge of the main wing <NUM>, where they are connected or supported against each other via a front spar <NUM>.

The high lift body <NUM> extends between a leading edge <NUM> and a trailing edge <NUM>, the trailing <NUM> edge in parallel to the axis of rotation <NUM>. The trailing edge <NUM> of the high lift body <NUM> moves in a sliding manner along the outer surface of the leading edge portion <NUM> of the upper skin panel <NUM> of the main wing <NUM> in contact with the outer surface of the leading edge portion <NUM> of the upper skin panel <NUM>, when the high lift body <NUM> is moved between the stowed position and the deployed position. The contact generally seals the high lift body <NUM> to the upper skin panel <NUM> for essential flow, but a certain leakage flow might be permitted.

The leading edge portion <NUM> of the upper skin panel <NUM> is configured to be elastically deformed in such a way that it is bent towards the lower skin panel <NUM>, when the high lift body <NUM> is moved from the stowed position to the deployed position. The elastic deformation can be done in different ways according to the invention, as described hereinafter.

In the example shown in <FIG>, the leading edge portion <NUM> of the upper skin panel <NUM> is configured to be elastically deformed, when the high lift body <NUM> is moved from the stowed position to the deployed position, by a link element <NUM> that is rotatably mounted at one end to the rotation element <NUM> and that is at the other end rotatably mounted to the leading edge portion <NUM> of the upper skin panel <NUM>. When the rotation element <NUM> rotates downwards to move the high lift body <NUM> into the deployed position, the link element <NUM> mounted to the rotation element <NUM> pulls the leading edge portion <NUM> of the upper skin panel <NUM> downwards, too. When the rotation element <NUM> rotates upwards to move the high lift body <NUM> back into the stowed position, the link element <NUM> pushes the leading edge portion <NUM> of the upper skin panel <NUM> back upwards into the undeformed state. As an alternative to the link element <NUM>, a rope element (not shown) can be used to deform the leading edge portion <NUM> of the upper skin element <NUM>. Additional to the deformation caused by the link element <NUM>, in the embodiment of <FIG> the leading edge portion <NUM> of the upper skin panel <NUM> is configured to be elastically deformed by the trailing edge <NUM> of the high lift body <NUM> moving along in a sliding manner and continuously contacting and pressing onto an outer surface of the leading edge portion <NUM> of the upper skin panel <NUM>, when the high lift body <NUM> is moved from the stowed position to the deployed position. When the rotation element <NUM> rotates downwards to move the high lift body <NUM> into the deployed position, the trailing edge <NUM> of the high lift body <NUM> mounted in a fixed or defined position relative to the rotation element <NUM> pushes the leading edge portion <NUM> of the upper skin panel <NUM> downwards, too. When the rotation element <NUM> rotates upwards to move the high lift body <NUM> back into the stowed position, the elastic properties of the upper skin panel <NUM> assist to move the leading edge portion <NUM> of the upper skin panel <NUM> back upwards into the undeformed state. In such a way, by the link element <NUM> together with the trailing edge <NUM> of the high lift body <NUM> the curvature of the leading edge portion <NUM> of the upper skin panel <NUM> can be precisely adapted to form the desired pressure profile.

The examples shown in <FIG> and <FIG> differ from the example shown in <FIG> by the wing <NUM> comprising a rotating actuator <NUM> for driving the rotation element <NUM> about the axis of rotation <NUM>. In the example not forming part of the presently claimed invention shown in <FIG>, the rotary actuator <NUM> is fixedly mounted to the main wing <NUM> and has a rotating drive arm <NUM> linked to the rotation element <NUM> by a drive link <NUM> that is at one end rotatably mounted to the drive arm <NUM> and that is at the other end rotatably mounted to the rotation element <NUM>. <FIG> shows the high lift body <NUM> in the stowed position, while <FIG> shows the high lift body <NUM> in the deployed position.

In embodiments according to the present invention, as shown in <FIG>, the rotary actuator <NUM> comprises a first rotating arm <NUM> and a second rotating arm <NUM> rotating in opposite directions about a common axis <NUM>. The first rotating arm <NUM> is rotatably mounted to the main wing <NUM>, and the second rotating arm <NUM> is rotatably mounted to the rotation element <NUM> or to the high lift body <NUM>, so that the common axis <NUM> is displaced when the actuator <NUM> is actuated.

The examples not according to the invention, but which may be useful for understanding aspects thereof, embodiments shown in <FIG> differ from the embodiment shown in <FIG> by a stiffener <NUM> being provided at the leading edge portion <NUM> of the upper skin panel <NUM>. The stiffener <NUM> extends in a span direction <NUM> in parallel to the axis of rotation <NUM> and in parallel to the trailing edge <NUM> of the high lift body <NUM>.

In the examples shown in <FIG> and <FIG>, the stiffener <NUM> is formed separately from the upper skin panel <NUM> and is attached to an inner surface of the leading edge portion <NUM> of the upper skin panel <NUM>. The stiffener <NUM> has an angled profile including a flange element <NUM> resting against the inner surface of the leading edge portion <NUM> of the upper skin panel <NUM>, and a web element <NUM> extending angled to the flange element <NUM> and away from the inner surface of the leading edge portion <NUM> of the upper skin panel <NUM>. The angles profile in the present embodiment is an L-profile.

In the alternative example shown in <FIG>, the stiffener <NUM> is formed integral with the leading edge portion <NUM> of the upper skin panel <NUM>. In case of the upper skin panel <NUM> being made of a metal material the stiffener <NUM> is formed by bending a part of the leading edge portion <NUM> of the upper skin panel <NUM>. In case of the upper skin panel <NUM> being made of a fiber reinforced plastic material the stiffener <NUM> is moulded as part of the leading edge portion <NUM> of the upper skin panel <NUM>.

In the example shown in <FIG>, the link element <NUM> is attached to the leading edge portion <NUM> of the upper skin panel <NUM> via the stiffener <NUM>. As shown in <FIG>, the extension of the stiffener <NUM> normal to the leading edge portion <NUM> of the upper skin panel <NUM> varies in the span direction <NUM> in such a way that a maximum extension is in the area of the attachment of the link element <NUM>, while the extension is linearly decreasing in the span direction <NUM> with increasing distance from the area of the attachment of the link element <NUM>. Likewise, a minimum extension is located centrally between the link elements <NUM> of each two spanwise neighboring connection assemblies <NUM>.

The example not according to the invention, but which may be useful for understanding aspects thereof, shown in <FIG> differs from the embodiment shown in <FIG> by the leading edge portion <NUM> of the upper skin panel <NUM> having a thickness varying in a chord direction <NUM>, to adjust the curvature of the leading edge portion <NUM> of the upper skin panel <NUM> when in the deformed state. This allows the thickness of the leading edge portion <NUM> of the upper skin panel <NUM> to be used to tailor the curvature of the upper skin panel <NUM> in the deformed state, i.e. when the high lift body <NUM> is in the deployed position. The thickness of the leading edge portion <NUM> of the upper skin panel <NUM> varies analogue to the bending moment resulting from elastic deformation of the leading edge portion <NUM> of the upper skin panel <NUM>, in such a way that the varying bending stiffness along the chord direction <NUM> of the leading edge portion <NUM> of the upper skin panel <NUM>, resulting from the varying thickness, compensates the bending moment. This means in the present example, the thickness of the leading edge portion <NUM> of the upper skin panel <NUM> increases linearly or essentially linearly in the chord direction <NUM> downstream, so that a maximum thickness is reached at the downstream end <NUM> of the leading edge portion <NUM> of the upper skin panel <NUM>.

In case that the leading edge portion <NUM> of the upper skin panel <NUM> being made of a fiber reinforced plastic, the linear thickness increase of the upper skin panel <NUM> might be implemented or assisted by the leading edge portion <NUM> of the upper skin panel <NUM> having a linearly increasing, e.g. ply-ramped, laminate lay-up (not shown) in the chord direction <NUM>.

Also, one or more reinforcement elements (not shown) attached to the leading edge portion <NUM> of the upper skin panel <NUM> might be used to implement or assist an increasing bending stiffness of the leading edge portion <NUM> of the upper skin panel <NUM> in the chord direction to compensate an increasing bending moment.

As shown in <FIG>, the leading edge high lift assembly <NUM> comprises a further connection assembly <NUM>' spaced from the connection assembly <NUM> in the span direction <NUM> and preferably formed as the connection assembly <NUM>. At least two spaced connection assemblies <NUM>, <NUM>' are provided to carry each high lift body <NUM>. Each connection assembly <NUM>, <NUM>' might also comprise more than one rotation element <NUM>.

Claim 1:
A wing (<NUM>) for an aircraft (<NUM>), comprising
a main wing (<NUM>), and
a leading edge high lift assembly (<NUM>) comprising
a high lift body (<NUM>), and
a connection assembly (<NUM>) connecting the high lift body (<NUM>) to the main wing (<NUM>) in such a way that the high lift body (<NUM>) is movable relative to the main wing (<NUM>) between a stowed position and a deployed position,
wherein the connection assembly (<NUM>) comprises at least one rotation element (<NUM>) that is mounted to the high lift body (<NUM>) and that is mounted to the main wing (<NUM>) rotatably about an axis of rotation (<NUM>),
wherein the main wing (<NUM>) comprises an upper skin panel (<NUM>) and a lower skin panel (<NUM>), wherein the upper skin panel (<NUM>) has a leading edge portion (<NUM>),
wherein the high lift body (<NUM>) extends between a leading edge (<NUM>) and a trailing edge (<NUM>), wherein the trailing edge (<NUM>) of the high lift body (<NUM>) is configured to move along the leading edge portion (<NUM>) of the upper skin panel (<NUM>) of the main wing (<NUM>), when the high lift body (<NUM>) is moved between the stowed position and the deployed position,
wherein the leading edge portion (<NUM>) of the upper skin panel (<NUM>) is configured to be elastically deformed, when the high lift body (<NUM>) is moved from the stowed position to the deployed position,
characterized in that
the wing (<NUM>) comprises a rotating actuator (<NUM>) for driving the rotation element (<NUM>) about the axis of rotation (<NUM>),
the rotating actuator (<NUM>) comprises a first rotating arm (<NUM>) and a second rotating arm (<NUM>) rotating in opposite directions about a common axis (<NUM>),
the first rotating arm (<NUM>) is rotatably mounted to the main wing (<NUM>), and
the second rotating arm (<NUM>) is rotatably mounted to the rotation element (<NUM>) or to the high lift body (<NUM>).