Arresting system, wings and aircraft

Abstract

This invention relates to arresting systems, wings, and aircraft. The wing includes a fixed wing and a foldable wingtip mounted to the fixed wing. The object of this invention is to provide an arresting device that allows the foldable wingtip to be arrested relative to the fixed wing in a very precise position. The arresting system includes a first hook mounted to the foldable wingtip and a second hook mounted to the fixed wing, wherein the first and second hooks are configured to move relative to each other between an arresting position and a release position. In the arresting position, the first and second hooks engage and prevent relative movement between a first and a second aircraft component. In the release position, the first and second hooks disengage and allow relative movement between the first and second aircraft components. The first and second hooks are formed and arranged such that they can move to the arresting position when the foldable wingtip is in an extended position.

Description

Technical Field

[0001] This invention relates to an arresting system, particularly a latching system, for arresting a first aircraft component relative to a second aircraft component. The first and second aircraft components can be, for example, a foldable wingtip portion and a fixed wing of an aircraft wing. Alternatively, the first and second aircraft components can also be a cargo door and an associated fuselage structure to which the cargo door is movably mounted. Another aspect of the invention relates to a wing for an aircraft including such an arresting system, particularly a foldable wing comprising a fixed wing and a foldable wingtip portion. Yet another aspect of the invention relates to an aircraft including such an arresting system and / or such a wing. Background Technology

[0002] This wing includes: a fixed wing for mounting to the fuselage; and a foldable wingtip portion mounted to the fixed wing via one or more foldable wingtip hinges rotatable about a wingtip hinge axis between an extended and a folded position. In the extended position, the foldable wingtip extends as a continuous extension of the fixed wing, preferably in the same plane as the fixed wing. In the folded position, the foldable wingtip extends upward or backward to reduce the overall span of the aircraft compared to the extended position. Specifically, when the foldable wingtip can be folded upward, the hinge axis extends in a horizontal plane and / or parallel to the chord line and / or parallel to the wing surface and / or along the direction of flight of the aircraft. Alternatively, when the foldable wingtip can be folded backward, the hinge axis extends vertically and / or along the wing thickness direction and / or in a direction transverse to or perpendicular to the wing surface.

[0003] Preferably, the wing further includes an actuation unit for actuating the foldable wingtip portion to move relative to the fixed wing about the wingtip hinge axis, i.e., between an extended position and a folded position. The actuation unit can be formed in various ways, for example, as a rack and pinion drive, and can be mounted near the wingtip hinge axis between the fixed wing and the foldable wingtip portion.

[0004] Foldable wings were developed to reduce the space requirements of the aircraft during maneuvering and parking. Once the aircraft lands, the foldable tips of the wings fold upwards or backwards, thereby reducing the overall span of the aircraft.

[0005] In the extended position, the foldable wing tip is typically secured by a separate locking device. Various designs of such locking devices have been proposed in the art, such as latching devices including a locking pin that engages with a corresponding hole. Summary of the Invention

[0006] The object of the present invention is to provide an arresting device that enables the foldable wingtip portion to be stopped relative to the fixed wing in a very precise position and can be engaged in a simple and quick manner.

[0007] This objective is achieved by an arresting system for blocking a first aircraft component relative to a second aircraft component, the arresting system comprising a first aircraft component, a second aircraft component, a first hook, and a second hook.

[0008] The first aircraft component is movable relative to the second aircraft component between a first position and a second position, wherein the first position may be the position where it is stopped by the arresting system. The first hook is C-shaped or U-shaped and has a first leg, an opposing second leg, and a first recess located between the first leg and the second leg. The first leg is pivotally mounted to the first aircraft component via a first hinge having a first hinge axis.

[0009] Similar to the first hook, the second hook is C-shaped or U-shaped and has a third leg, an opposing fourth leg, and a second recess located between the third and fourth legs. The third leg is pivotally mounted to the second aircraft component via a second hinge, which has a second hinge axis preferably parallel to the axis of the first hinge.

[0010] The first and second hooks are configured to move relative to each other, specifically pivoting, between an arresting position and a release position. In the arresting position, the first and second hooks engage and prohibit relative movement between the first and second aircraft components, while in the release position, the first and second hooks disengage and allow relative movement between the first and second aircraft components. Preferably, the first and second hooks have curved outer surfaces such that, when viewed in a cross-section through the first hinge axis and / or the second hinge axis, the engaged first and second hooks have a circular or elliptical profile.

[0011] In the blocking position, the first hook and the second hook engage in one of two ways: the first leg is received in a form-fitting manner in the second recess, while the third leg is received in a form-fitting manner in the first recess; or the second leg is received in a form-fitting manner in the second recess, while the fourth leg is received in a form-fitting manner in the first recess. In both cases, the engagement is such that the surface of the first hook abuts against the surface of the second hook along a continuous contact surface. The form-fitting manner in this connection is preferably understood as a complete form-fit between the surfaces of the first and second hooks without any gaps or disengagement of intermediate sections. Specifically, not only the concave surfaces of the first and second hooks, but also the convex surfaces of the first and second hooks are at least partially in contact with the corresponding other of the first and second hooks.

[0012] This arresting system can arrest the foldable wingtip relative to the fixed wing in a very precise position and can be engaged in a simple and quick manner.

[0013] According to a preferred embodiment, when viewed in a cross-section passing through the first hinge axis and / or the second hinge axis, the contact surface has an S-shaped form with a continuous tangential path. Preferably, this S-shaped form has only one central inflection point. This allows for a maximum contact surface with maximum friction and smooth engagement.

[0014] According to another preferred embodiment, the first hook portion has a first inner surface that guides to and defines the first recess, wherein the second hook portion has a second inner surface that guides to and defines the second recess, and wherein, when viewed from the inside of the engaged first and second hook portions outward, the contact surface extends along 50% to 100% of the first and / or second inner surfaces, preferably between 75% and 100%, more preferably between 90% and 100%, and most preferably along the entire first and / or second inner surfaces. That is, the contact surface extends from a central inflection point along the first and / or second inner surfaces until another inflection point appears at the first or second inner surface, causing the first and second inner surfaces to disengage and thus terminating the contact surface. This results in the formation of a maximum contact surface with maximum friction and smooth engagement.

[0015] According to another preferred embodiment, when viewed in a cross-section passing through the first hinge axis and / or the second hinge axis, the first leg is wider than the second leg and / or the third leg is wider than the fourth leg. This facilitates stable engagement of the hook and easy movement.

[0016] According to yet another preferred embodiment, the first hook and the second hook are formed and arranged such that when the first hook and the second hook move from the release position to the blocking position, the first hook and the second hook not only pivot relative to each other about the respective first hinge and / or second hinge, but also translate when viewed in a cross-section passing through the axis of the first hinge and / or the axis of the second hinge. This translational movement may be necessary or advantageous for the rapid and complete engagement of the first hook and the second hook.

[0017] According to another preferred embodiment, the tip of the first leg, preferably the center of the tip region of the first leg, and / or the tip of the third leg, preferably the center of the tip region of the third leg, protrudes beyond the straight connecting line that directly connects the first hinge and the second hinge, preferably directly connecting the axes of the first hinge and the second hinge. In this way, the first hook and the second hook surround each other at a large angle, thereby achieving a tight engagement.

[0018] According to another preferred embodiment, in the blocking position, the first hook engages with the second hook, such that the first leg is received in a form-fitting manner in the second recess, while the third leg is received in a form-fitting manner in the first recess. This engagement option allows the first hinge and the second hinge to come close to each other during engagement.

[0019] Specifically, preferably, a first guiding structure is mounted to a first aircraft component, and a second guiding structure is mounted to a second aircraft component, wherein, in the arrested position, a fourth leg engages between the first leg and the first guiding structure, and a second leg engages between the third leg and the second guiding structure. Preferably, the first and second guiding structures have concave surfaces adapted to the outer surfaces of the first and second hooks. The first and second guiding structures secure the engaged hooks in the arrested position because when a tensile load is applied between the first and second aircraft components and thus between the engaged first and second hooks, once the tensile load causes slight elastic deformation of the second and fourth legs, the second leg is clamped between the third leg and the second guiding structure, and the fourth leg is clamped between the first leg and the first guiding structure. This clamping of the second and fourth legs prevents the engaged hooks from disengaging under load, resulting in a very strong and rigid connection.

[0020] According to another preferred embodiment, in the blocking position, the first hook and the second hook engage such that the second leg is received in a form-fitting manner in the second recess, while the fourth leg is received in a form-fitting manner in the first recess. This engagement option allows the first hinge and the second hinge to be further apart from each other during engagement.

[0021] Specifically, preferably, in the arresting position, the second and fourth legs engage with each other such that they surround each other at an angle greater than 90° relative to the main load direction of the main external load applied to the arresting system. It is also preferred that the first and second hooks are formed and arranged such that they must pivot more than 90° to move from the release position to the arresting position. Through this deep-surround engagement, the engaged hooks are secured in the arresting position because when a tensile load is applied between the first and second aircraft components and thus between the engaged first and second hooks, once the tensile load causes slight elastic deformation of the second and fourth legs, the second leg is clamped between the third and fourth legs, and the fourth leg is clamped between the first and second legs. This clamping of the second and fourth legs prevents the engaged hooks from disengaging under load, resulting in a very strong and rigid connection.

[0022] According to another preferred embodiment, the blocking system further includes a locking device for locking the first hook and the second hook in a blocking position. The locking device preferably includes a first hole in the first hook and a second hole in the second hook. Preferably, the first hole and the second hole extend along a direction passing through the first hinge axis and / or the second hinge axis, and preferably perpendicular to the first hinge axis and / or the second hinge axis. When the first hook and the second hook are in the blocking position, the first hole and the second hole are aligned. The locking device also includes a locking pin configured to insert into the aligned first hole and the second hole to prevent disengagement of the first hook and the second hook. This locking device prevents accidental release of the blocking system.

[0023] Another aspect of the invention relates to a wing for an aircraft. The wing includes a fixed wing and a foldable wingtip portion mounted to the fixed wing via a foldable wingtip hinge rotatable between an extended position and a folded position about a wingtip hinge axis. The wing also includes an arresting system according to any of the foregoing embodiments, wherein a first aircraft component is the foldable wingtip portion, a second aircraft component is the fixed wing, a first position is an extended position, and a second position is a folded position. A first hook and a second hook are formed and arranged such that they can move into the arresting position when the foldable wingtip portion is in the extended position. Preferably, the first hinge axis and the second hinge axis extend parallel to the wingtip hinge axis. The features and effects associated with the arresting system described above are applicable to aircraft.

[0024] According to a preferred embodiment, the arresting system is arranged spaced apart from the tip hinge axis in the wing thickness direction of the fixed wing. Preferably, the arresting system is arranged below the tip hinge axis relative to the normal position of the aircraft on the ground. In this way, when aerodynamic forces act on the wingtip, a tensile load is applied to the arresting system, wherein the tensile load is minimized when the distance between the arresting system and the tip hinge axis is maximized.

[0025] Another aspect of the invention relates to an aircraft comprising an arresting system according to any of the foregoing embodiments and / or a wing according to any of the foregoing embodiments. The features and effects described above related to the arresting system and the wing are applicable to the aircraft in relation to the same purpose. Attached Figure Description

[0026] Preferred embodiments of the invention will be described in more detail below with the aid of the accompanying drawings. In the drawings:

[0027] Figure 1 A perspective view of an aircraft according to an embodiment of the present invention is shown.

[0028] Figure 2 Show Figure 1The side view of the wing shown focuses on the tip hinge and arresting system.

[0029] Figure 3 Show Figure 2 A cross-sectional view of a first embodiment of the arresting system used in the wing shown, and

[0030] Figure 4a and Figure 4b Show Figure 2 A cross-sectional view of a second embodiment of the arresting system used in the wing shown. Detailed Implementation

[0031] Figure 1 An exemplary aircraft 1 according to an embodiment of the present invention is shown. The aircraft 1 includes a foldable wing 3, which includes a fixed wing 5 mounted to a fuselage 7 and a foldable wingtip portion 9 movably mounted to the fixed wing 5.

[0032] Figure 2 A more detailed illustration is provided. Figure 1 The wing 3 of the aircraft 1 shown in the figure. The foldable wingtip 9 is in the extended position 15 via a hinge axis 13 around the tip (see figure). Figure 2 A foldable wing tip hinge 11, which rotates between the folded position (not shown), is mounted to the fixed wing 5. In the extended position 15, the foldable wing tip 9 extends into a continuous extension of the fixed wing 5, which lies in the same plane as the fixed wing 5. In the folded position, the foldable wing tip 9 extends upward to reduce the overall span of the aircraft 1. The hinge axis 13 is parallel to the wing chord and extends along the flight direction of the aircraft 1.

[0033] The wing also includes an arresting system 17 for arresting the first aircraft component 19, namely the foldable wingtip portion 9, relative to the second aircraft component 21, namely the fixed wing 5. In addition to the foldable wingtip portion 9 and the fixed wing 5, the arresting system 17 also includes a first hook portion 23 and a second hook portion 25. The arresting system 17 is arranged spaced apart from the wingtip hinge axis 13 in the wing thickness direction 26 of the fixed wing 5.

[0034] The first hook portion 23 is C-shaped and has a first leg 27, an opposing second leg 29, and a first recess 31 located between the first leg 27 and the second leg 29. The first leg 27 is pivotally mounted to the foldable wing tip portion 9 via a first hinge 33 having a first hinge axis 35. The second hook portion 25 is C-shaped and has a third leg 37, an opposing fourth leg 39, and a second recess 41 located between the third leg 37 and the fourth leg 39. The third leg 37 is pivotally mounted to the fixed wing 5 via a second hinge 43 having a second hinge axis 45 parallel to the first hinge axis 35. The first hinge axis 35 and the second hinge axis 45 are parallel to the tip hinge axis 13.

[0035] The first hook 23 and the second hook 25 are configured to move relative to each other between a blocking position 47 and a releasing position 49. In the blocking position 47, the first hook 23 and the second hook 25 are engaged and prevent movement of the foldable wing tip 9 relative to the fixed wing 5, while in the releasing position 49, the first hook 23 and the second hook 25 are disengaged and allow movement of the foldable wing tip 9 relative to the fixed wing 5. The first hook 23 and the second hook 25 are formed and arranged such that when the foldable wing tip 9 is in the extended position 15, they can move to the blocking position 47.

[0036] In the blocking position 47, the first hook 23 and the second hook 25 are based on Figure 3 and Figure 4a and Figure 4b One of the two embodiments shown is combined. In Figure 3 In the illustrated embodiment, the first leg 27 is received in the second recess 41 in a form-fitting manner, while the third leg 37 is received in the first recess 31 in a form-fitting manner. Conversely, in Figure 4a and Figure 4b In the illustrated embodiment, the second leg 29 is received in the second recess 41 in a form-fitting manner, while the fourth leg 39 is received in the first recess 31 in a form-fitting manner. In both cases, the engagement causes the surface of the first hook 23 to abut against the surface of the second hook 25 along a continuous contact surface 51.

[0037] exist Figure 3 In the illustrated embodiment, the arresting system 17 further includes a first guide structure 53 mounted to the foldable wing tip 9 and a second guide structure 55 mounted to the fixed wing 5. In the arresting position 47, a fourth leg 39 engages between the first leg 27 and the first guide structure 53, and a second leg 29 engages between the third leg 37 and the second guide structure 55. The first guide structure 53 and the second guide structure 55 have concave surfaces 57 adapted to the outer surfaces 59 of the first hook 23 and the second hook 25.

[0038] exist Figure 3 In the illustrated embodiment, in the blocking position 47, the second leg 29 and the fourth leg 39 engage with each other such that they surround each other at an angle greater than 90° relative to the main load direction 61 of the main external load applied to the blocking system 17. Furthermore, the first hook 23 and the second hook 25 are formed and arranged such that they must pivot more than 90° to move from the release position 49 to the blocking position 47.

[0039] exist Figure 3 and Figure 4a and Figure 4b In both embodiments shown, when viewed in a cross-section passing through the first hinge axis 35 and the second hinge axis 45, the contact surface 51 has an S-shaped form with a continuous tangential path. This S-shaped form has only one central inflection point 63. The first hook portion 23 has a first inner surface 65 that guides to and defines the first recess 31, while the second hook portion 25 has a second inner surface 67 that guides to and defines the second recess 41, and wherein the contact surface 51 extends along the entire first inner surface 65 and the second inner surface 67. That is, the contact surface 51 extends from the central inflection point 63 along the first inner surface 65 and the second inner surface 67 until another inflection point appears at the first inner surface 65 or the second inner surface 67, causing the first inner surface 65 to disengage from the second inner surface 67, and thus terminating the contact surface 51.

[0040] Furthermore, in both embodiments, when viewed in a cross-section passing through the first hinge axis 35 and the second hinge axis 45, the first leg 27 is wider than the second leg 29, and the third leg 37 is wider than the fourth leg 39.

[0041] This is true for both implementations, but especially for Figure 4a and Figure 4b In the illustrated embodiment, the first hook portion 23 and the second hook portion 25 are formed and arranged such that when the first hook portion 23 and the second hook portion 25 move from the release position 49 to the blocking position 47, the first hook portion 23 and the second hook portion 25 not only pivot relative to each other about the corresponding first hinge 33 and second hinge 43, but also translate when viewed in a cross-section passing through the first hinge axis 35 and the second hinge axis 45. Furthermore, the tips of the first leg portion 27 and the third leg portion 37 protrude beyond the connecting line connecting the first hinge 33 and the second hinge 43.

[0042] Figure 3 The illustrated implementation and Figure 4a and Figure 4bThe blocking system 17 in the illustrated embodiment further includes a locking device 69 for locking the first hook 23 and the second hook 25 in the blocking position 47. The locking device 69 includes a first hole 71 in the first hook 23 and a second hole 73 in the second hook 25. The first hole 71 and the second hole 73 extend in a direction perpendicular to the first hinge axis 35 and the second hinge axis 45. When the first hook 23 and the second hook 25 are in the blocking position 47, the first hole 71 and the second hole 73 are aligned. The locking device 69 also includes a locking pin 75 configured to insert into the aligned first hole 71 and second hole 73 to prevent the first hook 23 from disengaging from the second hook 25.

Claims

1. An arresting system (17) for arresting a first aircraft component (19) relative to a second aircraft component (21), the arresting system (17) comprising: A first aircraft component (19) and a second aircraft component (21), wherein the first aircraft component (19) is movable relative to the second aircraft component (21) between a first position and a second position. A first hook (23) in the shape of a C-shape has a first leg (27), an opposing second leg (29), and a first recess (31) located between the first leg (27) and the second leg (29), wherein the first leg (27) is pivotally mounted to the first aircraft component (19) via a first hinge (33). The second hook (25) is C-shaped and has a third leg (37), an opposing fourth leg (39), and a second recess (41) located between the third leg (37) and the fourth leg (39), wherein the third leg (37) is pivotally mounted to the second aircraft component (21) via a second hinge (43). The first hook (23) and the second hook (25) are configured to move relative to each other between a blocking position (47) and a release position (49). In the blocking position (47), the first hook (23) and the second hook (25) are engaged, preventing relative movement between the first aircraft component (19) and the second aircraft component (21). In the release position (49), the first hook (23) and the second hook (25) are disengaged, allowing relative movement between the first aircraft component (19) and the second aircraft component (21). In the blocking position (47), the first hook (23) engages with the second hook (25), such that the first leg (27) is received in the second recess (41) in a form-fitting manner, while the third leg (37) is received in the first recess (31) in a form-fitting manner, such that the surface of the first hook (23) abuts against the surface of the second hook (25) along a continuous contact surface (51). The first guidance structure (53) is installed to the first aircraft component (19), and the second guidance structure (55) is installed to the second aircraft component (21). In the arresting position (47), the fourth leg (39) is engaged between the first leg (27) and the first guidance structure (53), and the second leg (29) is engaged between the third leg (37) and the second guidance structure (55).

2. The barrier system according to claim 1, wherein, The contact surface (51) has an S-shaped shape with a continuous tangential path.

3. The barrier system according to claim 1 or 2, wherein, The first hook (23) has a first inner surface (65) that leads to and defines the first recess (31), wherein the second hook (25) has a second inner surface (67) that leads to and defines the second recess (41), and wherein the contact surface (51) extends between 50% and 100% of the first inner surface (65) and / or the second inner surface (67).

4. The barrier system according to claim 1 or 2, wherein, The first leg (27) is wider than the second leg (29) and / or the third leg (37) is wider than the fourth leg (39).

5. The barrier system according to claim 1 or 2, wherein, The first hook (23) and the second hook (25) are formed and arranged such that when the first hook (23) and the second hook (25) move from the release position (49) to the blocking position (47), the first hook (23) and the second hook (25) not only pivot relative to each other about the corresponding first hinge (33) and / or second hinge (43), but also translate.

6. The barrier system according to claim 1 or 2, wherein, The tip of the first leg (27) and / or the tip of the third leg (37) protrudes beyond the line connecting the first hinge (33) and the second hinge (43).

7. The blocking system according to claim 1 or 2 further includes a locking device (69) for locking the first hook (23) and the second hook (25) in the blocking position (47), wherein, The locking device (69) includes a first hole (71) in the first hook (23) and a second hole (73) in the second hook (25), wherein the first hole (71) and the second hole (73) are aligned when the first hook (23) and the second hook (25) are in the blocking position (47), wherein the locking device (69) further includes a locking pin (75) configured to be inserted into the aligned first hole (71) and second hole (73) to prevent the first hook (23) from disengaging from the second hook (25).

8. The barrier system according to claim 3, wherein, The contact surface (51) extends between 75% and 100% of the first inner surface (65) and / or the second inner surface (67).

9. The barrier system according to claim 3, wherein, The contact surface (51) extends between 90% and 100% of the first inner surface (65) and / or the second inner surface (67).

10. The barrier system according to claim 3, wherein, The contact surface (51) extends along the entire first inner surface (65) and / or the second inner surface (67).

11. The barrier system according to claim 6, wherein, The connecting line is straight and directly connects the first hinge axis and the second hinge axis.

12. A wing (3) for use in an aircraft (1), the wing (3) comprising: Fixed-wing (5), and A foldable wing tip portion (9) is attached to the fixed wing (5) via a wing tip hinge (11) that is rotatable about the wing tip hinge axis (13) between an extended position (15) and a folded position. Its features are, The wing (3) includes an arresting system (17) according to any one of claims 1 to 11, wherein the first aircraft component (19) is the foldable wingtip portion (9), the second aircraft component (21) is the fixed wing (5), the first position is the extended position (15), the second position is the folded position, and The first hook (23) and the second hook (25) are formed and arranged such that when the foldable wing tip (9) is in the extended position (15), the first hook (23) and the second hook (25) can move to the blocking position (47).

13. The wing according to claim 12, wherein, The arresting system (17) is arranged to be spaced apart from the axis of the tip hinge (13) in the wing thickness direction (26) of the fixed wing (5).

14. An aircraft (1) comprising an arresting system (17) according to any one of claims 1 to 11 and / or comprising a wing (3) according to claim 12 or 13.

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