Patent Description:
The wing 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 a 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/or shorter chord extension 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/or longer chord extension and might also be referred to as drooped position, landing position or extended position.

The connection assembly comprises a first connection element that is mounted to the high lift body and that is movably mounted to the main wing. The connection assembly further comprises a second connection element that is mounted to the high lift body in a position spaced apart from the first connection element in a span direction, and that is movably mounted to the main wing.

In case that the high lift body is formed as a droop nose, the first and second connection elements might be formed as rotation elements, such as hinge arms, rotation rods or a parts of the high lift body structure, that are mounted to the high lift body and that are mounted to the main wing rotatably about an axis of rotation. The rotation element might be 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.

However, in case that the high lift body is formed as a slat, the first and second connection elements might be formed as slat tracks guided at the main wing for movement along a predetermined path that might be straight or curved around a centre that lies far outside the wing profile, or might be formed as a linkage rotatably mounted to the main wing and rotatably mounted to the high lift body.

Similar wings are known in the art (see e.g. documents <CIT> and <CIT>). At the known wings it may happen, in particular when the first and second connection elements are arranged with a greater distance from another, that the portion of the high lift body between the two connection elements bends under air loads, so that in the stowed position of the high lift body there might be no smooth transition in this area between the trailing edge of the high lift body and the leading edge of the main wing, which however is advantageous for aerodynamic reasons. Also, the high lift bodies of some known wings are spanwise supported only by side struts rotatably linked at the main wing and rotatably linked at the high lift body and extending at least partly in span direction, which add weight and complexity to the wing.

Therefore, the object of the present invention is to provide a wing comprising a simple, lightweight and aerodynamically optimized leading edge high lift assembly.

This object is achieved by means of a leading edge high lift assembly as per claim <NUM> and a wing according to claims <NUM>-<NUM>, wherein the connection assembly comprises an additional support device arranged spaced apart from the first and second connection elements and configured to support the high lift body at the main wing against movement or deformation of the high lift body, i.e. to restrict movement or deformation of the high lift body, in particular in a wing thickness direction, i.e. at least with a share in the wing thickness direction, and/or in a span direction, i.e. at least with a share in the span direction, relative to the main wing. There might also be more than one additional support devices provided per high lift body. By such an additional support, bending of the high lift body between the first and second connection elements under air loads and/or spanwise movement of the high lift body can be reliably restricted, so that the leading edge high lift assembly is particularly simple, lightweight and aerodynamically advantageous.

According to a preferred embodiment, the additional support device is arranged, preferably centrally, between the first connection element and the second connection element. In such a way, bending of the high lift body between the first and second connection elements under air loads and/or spanwise movement of the high lift body can be most efficiently restricted without introducing additional bending moments into the high lift body. However, it is also possible that the additional support device is arranged outboard or inboard of the first or second connection element.

According to the invention, the additional support device comprises a hold down device configured to support the high lift body at the main wing against upwards movement of the high lift body relative to the main wing, i.e. to restrict upwards movement of the high lift body relative to the main wing, when the high lift body is in the stowed position. The term "upwards" is with respect to a normal position of the associated aircraft on the ground. The upwards movement might also be interpreted as a movement in the wing thickness direction towards the upper wing surface. By such a hold down device bending of the high lift body between the first and second connection elements under air loads can be restricted in a simple and efficient way.

In particular, it is preferred that the hold down device comprises a first stop element mounted, preferably fixedly mounted, to the high lift body and a second stop element mounted, preferably fixedly mounted, to the main wing. The first and second stop elements are configured to rest against one another when the high lift body is in the stowed position to support the high lift body at the main wing against upwards movement of the high lift body relative to the main wing. Preferably, the first stop element and/or the second stop element might be adjustable in the contact direction, e.g. might include an adjustable screw, wherein contact is preferably established by the screw head. By such first and second stop elements a simple and reliable hold down device can be realized.

It is further preferred that the first and second stop elements are configured to rest against one another within a contact plane. The contact plane extends in a plane spanned by the span direction and a chord direction, or at least has a share in a plane spanned by the span direction and the chord direction. This means a contact force transferred between the first and second stop elements, which results from an upwards movement of the high lift body being restricted by the hold down device, extends normal to the contact plane or at least has a share normal to the contact plane, so that an efficient load transfer between the first and second stop elements is enabled.

According to the invention, the additional support device comprises a lateral support device configured to support the high lift body at the main wing against spanwise movement of the high lift body relative to the main wing, i.e. to restrict spanwise movement of the high lift body relative to the main wing, when the high lift body is moved between the stowed position and the deployed position, including when the high lift body is in the stowed position and in the deployed position. By such a lateral support spanwise movement of the high lift body can be restricted at all times in a simple and efficient way.

If only the additional support device is used to transfer the lateral loads of the high lift body, the additional support device is preferably formed in a fail-safe manner for lateral loads. This means preferably, the load path is fails-safe, e.g. by additional rollers or slide pads, contact plates, or back-to-back blades, or multiple load paths are provided, e.g. by providing another additional support device spaced from the first additional support device by a lateral gap and transferring lateral loads when the first additional support device fails.

In particular, it is preferred that the lateral support device comprises a roller or slide bearing including at least one roller or slide pad mounted to one of the high lift body and the main wing, and engaging a corresponding guide surface at the other one of the high lift body and the main wing, so that the roller rolls or the slide pad slides along the guide surface when the high lift body is moved between the stowed position and the deployed position, thereby providing a load support in the span direction. By such a roller or slide bearing a simple, reliable and efficient lateral support is realized.

It is further preferred that the guide surface and/or a rotation axis of the roller extend in a chord plane spanned by the chord direction and the wing thickness direction. In such a way, a load support in the lateral direction is enabled.

It is also preferred that the lateral support device comprises a first blade preferably extending in the chord plane, mounted to the high lift body and having a first guide surface at a first side and a second guide surface at an opposite second side. The lateral support device preferably further comprises a pair of rollers or slide pads mounted to the main wing, preferably to a rib of the main wing, and engaging the first and/or second guide surfaces from opposite sides. In such a way, a simple and efficient lateral support device is realized wherein only one blade is required mounted to the high lift body.

Alternatively, it is preferred that the lateral support device comprises a first blade and a second blade both mounted to the high lift body preferably in parallel to one another and having a first guide surface and a second guide surface facing towards each other and preferably extending in the chord plane. The lateral support device preferably further comprises a roller or slide pad mounted to the main wing, preferably to a rib of the main wing, and guided between the first and second blades in engagement with the first guide surface and/or the second guide surface. In such a way, a simple and efficient lateral support device is realized wherein only one roller or slide pad is required mounted to the main wing.

Alternatively, it is preferred that the lateral support device comprises a first blade preferably extending in the chord plane, mounted to the main wing, preferably to a rib of the main wing, and having a first guide surface at a first side and a second guide surface at an opposite second side. The lateral support device preferably further comprises a pair of rollers or slide pads mounted to the high lift body and engaging the first and/or second guide surfaces from opposite sides. In such a way, a simple and efficient lateral support device is realized wherein only one blade is required mounted to the main wing.

Alternatively, it is preferred that the lateral support device comprises a first blade and a second blade both mounted to the main wing, preferably to a rib of the main wing, preferably in parallel to one another and having a first guide surface and a second guide surface facing towards each other and preferably extending in the chord plane. The lateral support device preferably further comprises a roller or slide pad mounted to the high lift body and guided between the first and second blades in engagement with the first guide surface and/or the second guide surface. In such a way, a simple and efficient lateral support device is realized wherein only one roller or slide pad is required mounted to the high lift body.

According to a preferred embodiment, the first blade and/or the second blade have a profile, preferably a T-, L- or C-shaped profile, including a blade portion preferably having the guide surfaces, and a flange portion mounted to the high lift body or to the main wing, e.g. by bolts. Preferably, the flange portion is mounted to the lower and/or rearward panel of high lift body. In such a way, a simple and reliable structure is formed.

In particular, it is preferred that the first blade and/or the second blade is formed as or integrally formed with a rib of the main wing, preferably extending in a chord direction. In such a way, a simple and reliable structure is formed.

According to a preferred embodiment, at least one contact plate preferably formed of a hard material, such as steel, titanium, or ceramic, is mounted to the first and/or second blades and includes the first and/or second guiding surfaces to reinforce the first and/or second guiding surfaces, in particular in cases where the first and/or second blades are formed of a softer material, such as aluminium. In such a way, reliable and durable guide surfaces are formed.

According to a preferred embodiment, the first stop element is mounted to or formed integrally with the first and/or second blade. Additionally or alternatively, the second stop element is mounted to or formed integrally with a rib of the main wing. In such a way, a simple and reliable hold down device is formed.

In particular, it is preferred that the first stop element includes a first stop flange preferably formed at the lower or front end of the first and/or second blade and extending in the span direction. Additionally or alternatively, the second stop element includes a second stop flange formed at a rib of the main wing and extending in the span direction. In such a way, a simple and reliable hold down device is formed.

Alternatively, it is preferred that the first stop element is formed as a chordwise extension of the first and/or second blade and is preferably formed at the lower or front end of the first and/or second blade. Additionally or alternatively, the second stop element is formed as a chordwise extending projection at a rib of the main wing. In such a way, another simple and reliable hold down device is formed.

Alternatively, it is preferred that the first stop element is formed at the upper or rear end of the first and/or second blade, preferably at the head end of the first and/or second blade. Additionally or alternatively, the second stop element is formed as a chordwise and/or spanwise extending projection at a rib of the main wing. In such a way, another simple and reliable hold down device is formed.

According to a preferred embodiment, the additional support device comprises a deployment stop limiting deployment movement of the high lift body and thereby defining the deployed position of the high lift body. In such a way, the deployment stop can be easily integrated into the wing and reliable limit deployment of the high lift body.

In particular, it is preferred that the deployment stop comprises at least one lateral projection extending from the first and/or second guide surface of the first and/or second blade in the span direction and running against, i.e. stopping at, at least one roller or slide pad when the high lift body is in the deployed position. In such a way, a simple and reliable deployment stop is formed.

According to a preferred embodiment, the high lift body might be in the form of a droop nose, wherein the first connection element is in the form of a first rotation element, such as a hinge arm, preferably fixedly mounted to the high lift body and mounted to the main wing rotatably about a first rotation axis, and wherein the second connection element is in the form of a second rotation element, such as a hinge arm, preferably fixedly mounted to the high lift body and mounted to the main wing rotatably about a second rotation axis preferably parallel or coaxial to the first rotation axis. Preferably, the first and second rotation axes are arranged within or at the profile of the main wing. In such a way, the high lift body is moved on a circular path around the first and second rotation axes. Preferably, the wing comprises a rotating actuator for driving the rotation element about the axis of rotation. The additional support device according to the invention is particularly advantageous for a high lift body in the form of a droop nose.

Alternatively, it is preferred that the high lift body is in the form of a slat, wherein the first and second connection elements are formed as slat tracks movably guided at the main wing along a predetermined straight or curved path, or are formed as linkages rotatably mounted to the main wing and mounted to the slat. The additional support device according to the invention is also advantageous for a high lift body in the form of a slat.

A further aspect of the invention relates to an aircraft comprising the wing according to any of the afore-described embodiments and/or comprising the leading edge high lift assembly according to any of the afore described embodiments. Features and effects described above in connection with the wing and in connection with the leading edge high lift assembly 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 embodiment of an aircraft <NUM> 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 embodiments of the wings <NUM>.

<FIG> show a first embodiment of the wing <NUM> according to the invention. 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. 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, as indicated in <FIG>. 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 a first connection element <NUM> that is mounted to the high lift body <NUM> and that is movably mounted to the main wing <NUM>. The connection assembly <NUM> further comprises a second connection element <NUM> that is mounted to the high lift body <NUM> in a position spaced apart from the first connection element <NUM> in a span direction <NUM>, and that is movably mounted to the main wing <NUM>.

As shown in <FIG>, the first and second connection elements <NUM>, <NUM> are formed as rotation elements <NUM> in the form of hinge arms that are mounted to the high lift body <NUM> and that are mounted to the main wing <NUM> rotatably about an axis of rotation <NUM>. Each 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 a lower skin and extends in parallel to the span direction <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 wing <NUM> further comprises a rotating actuator <NUM> for driving the rotation element <NUM> about the axis of rotation <NUM>.

As indicated in <FIG>, the connection assembly <NUM> further comprises an additional support device <NUM> arranged centrally between and spaced apart from the first and second connection elements <NUM>, <NUM> and configured to support the high lift body <NUM> at the main wing <NUM> against movement or deformation of the high lift body <NUM> in a wing thickness direction <NUM> and/or in a span direction <NUM> relative to the main wing <NUM>. Different embodiments of the additional support device are shown in <FIG>.

In the embodiment shown in <FIG>, the additional support device <NUM> comprises a hold down device <NUM> configured to support the high lift body <NUM> at the main wing <NUM> against upwards movement of the high lift body <NUM> relative to the main wing <NUM>, when the high lift body <NUM> is in the stowed position. The hold down device <NUM> comprises a first stop element <NUM> fixedly mounted to the high lift body <NUM> and a second stop element <NUM> fixedly mounted to the main wing <NUM>. The first and second stop elements <NUM>, <NUM> are configured to rest against one another when the high lift body <NUM> is in the stowed position to support the high lift body <NUM> at the main wing <NUM> against upwards movement of the high lift body <NUM> relative to the main wing <NUM>. The first stop element <NUM> and the second stop element <NUM> are adjustable in the contact direction by including an adjustable screw <NUM>, wherein contact is established by the screw head <NUM>.

The first and second stop elements <NUM>, <NUM> are configured to rest against one another within a contact plane <NUM>. The contact plane <NUM> extends in a plane spanned by the span direction <NUM> and a chord direction <NUM>, or at least has a share in said plane spanned by the span direction <NUM> and the chord direction <NUM>. This means a contact force transferred between the first and second stop elements <NUM>, <NUM>, which results from an upwards movement of the high lift body <NUM> being restricted by the hold down device <NUM>, extends normal to the contact plane <NUM> or at least has a share normal to the contact plane <NUM>, so that an efficient load transfer between the first and second stop elements <NUM>, <NUM> is enabled.

In the embodiments shown in <FIG>, the additional support device <NUM> comprises a lateral support device <NUM> configured to support the high lift body <NUM> at the main wing <NUM> against spanwise movement of the high lift body <NUM> relative to the main wing <NUM>, when the high lift body <NUM> is moved between the stowed position and the deployed position, including when the high lift body <NUM> is in the stowed position and in the deployed position. The lateral support device <NUM> comprises a roller or slide bearing <NUM> including at least one roller <NUM> mounted to one of the high lift body <NUM> and the main wing <NUM>, and engaging a corresponding guide surface <NUM> at the other one of the high lift body <NUM> and the main wing <NUM>, so that the roller <NUM> rolls along the guide surface <NUM> when the high lift body <NUM> is moved between the stowed position and the deployed position, thereby providing a load support in the span direction <NUM>. The guide surface <NUM> and a rotation axis <NUM> of the roller <NUM> extend in a chord plane spanned by the chord direction <NUM> and the wing thickness direction <NUM>.

<FIG> show an embodiment, wherein the lateral support device <NUM> comprises a first blade <NUM> extending in the chord plane, mounted to the high lift body <NUM> and having a first guide surface <NUM> at a first side <NUM> and a second guide surface <NUM> at an opposite second side <NUM>. The lateral support device <NUM> further comprises a pair of rollers <NUM> mounted a rib <NUM> of the main wing <NUM> and engaging the first and second guide surfaces <NUM>, <NUM> from opposite sides. As shown e.g. in <FIG>, the first blade <NUM> has a T-shaped profile including a blade portion <NUM> having the guide surfaces <NUM>, <NUM>, and a flange portion <NUM> mounted to the high lift body <NUM>, specifically to the lower and/or rearward panel <NUM> of high lift body <NUM>, e.g. by bolts <NUM>.

<FIG> show an alternative embodiment, wherein the lateral support device <NUM> comprises a first blade <NUM> extending in the chord plane, mounted to a rib of <NUM> the main wing <NUM>, and having a first guide surface <NUM> at a first side <NUM> and a second guide surface <NUM> at an opposite second side <NUM>. The lateral support device <NUM> further comprises a pair of rollers <NUM> mounted to the high lift body <NUM> and engaging the first and second guide surfaces <NUM>, <NUM> from opposite sides. The first blade <NUM> is formed as or integrally formed with a rib of the main wing <NUM> extending in a chord direction <NUM>.

<FIG> shows an alternative embodiment slightly different to that of <FIG>, wherein the lateral support device <NUM> comprises a first blade <NUM> and a second blade <NUM> both mounted to a rib <NUM> of the main wing <NUM> in parallel to one another and having a first guide surface <NUM> and a second guide surface <NUM> facing towards each other and extending in the chord plane. The lateral support device <NUM> further comprises a roller <NUM> mounted to the high lift body <NUM> and guided between the first and second blades <NUM>, <NUM> in engagement with the first guide surface <NUM> and/or the second guide surface <NUM>. The first blade <NUM> and the second blade <NUM> are formed as or integrally formed with a rib of the main wing <NUM> extending in a chord direction <NUM>.

In the embodiments shown in <FIG>, a contact plate <NUM> formed of a hard material, such as steel, titanium, or ceramic, is mounted to the first and second blades <NUM>, <NUM> and includes the first and second guiding surfaces <NUM>, <NUM> to reinforce the first and second guiding surfaces <NUM><NUM> as in the present embodiments the first and second blades <NUM>, <NUM> are formed of a softer material, namely aluminium.

<FIG> show further embodiments, where a first stop element <NUM> is mounted to or formed integrally with the first and/or second blade <NUM>, <NUM>. Additionally, a second stop element <NUM> is mounted to or formed integrally with a rib <NUM> of the main wing <NUM>.

In the embodiment shown in <FIG>, the first stop element <NUM> is formed at the upper or rear end of the first blade <NUM> at the head end of the first blade <NUM>. Additionally, the second stop element <NUM> is formed as a chordwise and/or spanwise extending projection at a rib <NUM> of the main wing <NUM>.

In the embodiment shown in <FIG>, the first stop element <NUM> is formed as a chordwise extension <NUM> of the first blade <NUM> and is formed at the lower or front end of the first blade <NUM>. Additionally, the second stop element <NUM> is formed as a chordwise extending projection <NUM> at a rib <NUM> of the main wing <NUM>.

In the embodiment shown in <FIG>, the first stop element <NUM> includes a first stop flange <NUM> formed at the lower or front end of the first blade <NUM> and extending in the span direction. Additionally, the second stop element <NUM> includes a second stop flange <NUM> formed at a rib <NUM> of the main wing <NUM> and extending in the span direction <NUM>.

<FIG> show a further embodiment, where the additional support device <NUM> comprises a deployment stop <NUM> limiting deployment movement of the high lift body <NUM> and thereby defining the deployed position of the high lift body <NUM>. The deployment stop <NUM> comprises two opposite lateral projections <NUM> extending from the first and second guide surface <NUM>, <NUM> of the first blade <NUM> in the span direction <NUM> and running against rollers <NUM> when the high lift body <NUM> is in the deployed position.

Claim 1:
leading edge high lift assembly (<NUM>) for a wing (<NUM>) comprising a main wing (<NUM>) of an aircraft, comprising
a high lift body (<NUM>), and
a connection assembly (<NUM>) configured for 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 a first connection element (<NUM>) that is mounted to the high lift body (<NUM>) and that is configured to be movably mounted to the main wing (<NUM>),
wherein the connection assembly (<NUM>) comprises a second connection element (<NUM>) that is mounted to the high lift body (<NUM>) in a position spaced apart from the first connection element (<NUM>) in a span direction (<NUM>), and that is configured to be movably mounted to the main wing (<NUM>),
wherein the connection assembly (<NUM>) comprises an additional support device (<NUM>) arranged spaced apart from the first and second connection elements (<NUM>, <NUM>) and configured to support the high lift body (<NUM>) at the main wing (<NUM>) against movement or deformation of the high lift body (<NUM>) relative to the main wing (<NUM>),
wherein
the additional support device (<NUM>) comprises a hold down device (<NUM>) configured to support the high lift body (<NUM>) at the main wing (<NUM>) against upwards movement of the high lift body (<NUM>) relative to the main wing (<NUM>) when the high lift body (<NUM>) is in the stowed position,
the hold down device (<NUM>) comprises a first stop element (<NUM>) mounted to the high lift body (<NUM>) and a second stop element (<NUM>) configured to be mounted to the main wing (<NUM>),
the first and second stop elements (<NUM>, <NUM>) are configured to rest against one another when the high lift body (<NUM>) is in the stowed position, and characterized in that
the additional support device (<NUM>) comprises a lateral support device (<NUM>) configured to support the high lift body (<NUM>) at the main wing (<NUM>) against spanwise movement of the high lift body (<NUM>) relative to the main wing (<NUM>) when the high lift body (<NUM>) is moved between the stowed position and the deployed position.