CN114735197A

CN114735197A - Fixing and locking mechanism of foldable wing

Info

Publication number: CN114735197A
Application number: CN202210412981.5A
Authority: CN
Inventors: 陈海昕; 郭廷宇; 朱晨华; 冯良韬
Original assignee: Tsinghua University
Current assignee: Tsinghua University
Priority date: 2022-04-19
Filing date: 2022-04-19
Publication date: 2022-07-12

Abstract

The fixed locking mechanism comprises a first group of hollow beams and a second group of hollow beams, wherein the first group of hollow beams and the second group of hollow beams are respectively arranged on the first wing and the second wing and are aligned with each other; the linear actuator is arranged on the first wing; the group of movable wing beams are arranged in the first group of hollow beams in a sliding manner and close to one section of the second wing, and the movable wing beams are abutted against the linear actuator; the movable wing beam slides along the first group of hollow beams under the driving of the linear actuator until one part of the movable wing beam is fixed in the first group of hollow beams and the other part of the movable wing beam is fixed in the second group of hollow beams. The wing locking device is simple in structure, high in reliability and wide in application range, and wing locking is achieved.

Description

Fixing and locking mechanism of foldable wing

Technical Field

The present disclosure relates to aircraft technology, and more particularly to a fixed locking mechanism for foldable wings.

Background

The wing is the most important component of the airplane, the structure of the wing needs to bear the lift force, the resistance and various bending torque moments of the airplane in the flying process, and simultaneously, the installation requirements of the undercarriage, the engine, the plug-in part and the pneumatic control surface are considered, and the main force bearing parts of the wing comprise wing spars/webs arranged in the wingspan direction of the calendar, wing ribs arranged in the direction perpendicular to the wing spars, skin covering outside the wing and the like.

The foldable wing is used for military carrier-based aircraft at first, and the wing can be folded inwards when the aircraft is parked on an aircraft carrier deck and an aircraft garage, so that the wingspan and the occupied area are greatly reduced, and the aircraft carrier deployment is facilitated. With the development of variant technologies, foldable wings are gradually developed, the application range of the foldable wings is expanded, various novel foldable wings gradually appear, and many variant aircrafts can fold and deform the wings in the flight process, and change the shapes of the wings under different flight environments to complete specific flight tasks.

For a foldable wing, the unfolding-direction establishment structures of a wing spar, a web plate and the like are completely broken at the folding part of the wing, a fixing and locking mechanism of the foldable wing needs to connect the broken positions and enable the structural strength and rigidity of the wing to meet the requirements before breaking, and the wing needs to bear larger force and moment and ensure enough reliability.

In the existing fixed locking mechanisms of the foldable wings and the foldable wings, the wing folding mechanism used for the ship-based aircraft is the most common, the folding mechanism is mainly applied to the ship-based large aircraft, the wings of the aircraft are usually smaller in aspect ratio and lower in wing thickness, and a single-block type or multi-web type wing structure form is mostly adopted. For example, the wings of the existing carrier-based fighter plane use a large number of fixing pins to penetrate through the locking holes of two adjacent fins, so that two end surfaces of the folding wings are fixed together, and the locking is completed. However, the fixed locking manner of the folding wing mainly has the following defects: (1) the wing ribs on two end faces are mainly used for transferring force, and the wing is suitable for multi-web or single-piece wings and is not suitable for multi-beam wings with large aspect ratio. (2) The fixing mechanism is complex, needs a large actuator and is not suitable for small unmanned planes. (3) The folding device is mainly suitable for folding the airplane in a ground shutdown state and is not suitable for being deformed and folded in the air.

Disclosure of Invention

In view of this, the present disclosure provides a fixing and locking mechanism for a foldable wing, which has a simple structure and a wide application range.

The utility model provides a fixed locking mechanical system of collapsible wing for the collapsible wing to the aircraft locks or removes the locking, is used for locking or removing the locking to the collapsible wing of aircraft, and the aircraft includes the fuselage, and the middle part of fuselage has connected gradually first wing and second wing from inside to outside, and the second wing is equivalent to the collapsible activity of first wing, and this mechanism includes: the first group of hollow beams and the second group of hollow beams are respectively arranged on the first wing and the second wing, and the first group of hollow beams and the second group of hollow beams are aligned with each other; the linear actuator is arranged on the first wing; the movable wing beams are arranged in the first group of hollow beams in a sliding mode and close to one section of the second wing, and the movable wing beams are abutted to the linear actuator; the movable wing beam slides along the first group of hollow beams under the driving of the linear actuator until one part of the movable wing beam is fixed in the first group of hollow beams and the other part of the movable wing beam is fixed in the second group of hollow beams.

Furthermore, the first wing is fixedly connected with the fuselage, and the first wing is rotatably connected with the second wing.

Further, the first wing and the second wing are connected through a connecting rod or a hinge.

Further, the first and second sets of hollow spars each comprise a plurality of hollow spars, each hollow spar in the connecting face of the first airfoil and the second airfoil being aligned with one another.

Further, a stopper is arranged in each of the first set of hollow beams and the second set of hollow beams for limiting the fixing position of the movable spar.

Further, the movable spars are one or more.

Furthermore, the end of the movable wing beam is an inclined plane or a curved surface for guiding.

Further, the linear actuator includes an electric actuator or a hydraulic actuator.

Further, the second wing moves relative to the first wing between an extended position in which the second wing is flush-butted against an outer end face of the first wing and a folded position.

Compared with the prior art, the fixing and locking mechanism of the foldable wing provided by the disclosure has at least the following beneficial effects: the wing locking device is simple in structure, higher in reliability and wider in application range, and wing locking is realized for the foldable wings.

Drawings

The above and other objects, features and advantages of the present disclosure will become more apparent from the following description of the embodiments of the present disclosure with reference to the accompanying drawings, in which:

FIG. 1 schematically illustrates a block diagram of a fixed locking mechanism of a foldable wing according to an embodiment of the disclosure;

fig. 2(a) -2 (c) schematically illustrate installation views of a first set of hollow beams and a second set of hollow beams according to an embodiment of the present disclosure.

[ description of reference ]

1-a fuselage; 2-a first airfoil; 3-a second airfoil; 4-a first set of hollow beams; 41-hollow beam; 5-a second set of hollow beams; 6-a linear actuator; 7-movable spar.

Detailed Description

For the purpose of promoting a better understanding of the objects, aspects and advantages of the present disclosure, reference is made to the following detailed description taken in conjunction with the accompanying drawings. It is to be understood that the described embodiments are only a few, and not all, of the disclosed embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.

In the present disclosure, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integral; can be mechanically connected, electrically connected or can communicate with each other; they may be directly connected or indirectly connected through intervening media, or may be in communication within two elements or in interactive relationship between two elements. The specific meaning of the above terms in the present disclosure can be understood by those of ordinary skill in the art as appropriate.

All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.

FIG. 1 schematically illustrates a block diagram of a fixed locking mechanism of a foldable wing according to an embodiment of the disclosure.

As shown in fig. 1, an embodiment of the present disclosure provides a fixed locking mechanism for a foldable wing, which is used for locking or unlocking the foldable wing of an aircraft, where the aircraft includes a fuselage 1, a first wing 2 and a second wing 3 are sequentially connected to a middle portion of the fuselage 1 from inside to outside, and the second wing 3 is equivalent to the first wing 2 and is foldable and movable. The fixed locking mechanism comprises a first set of hollow beams 4, a second set of hollow beams 5, a linear actuator 6 and a movable spar 7.

It should be noted that the fixed locking mechanism of the foldable wing according to the embodiment of the present disclosure may be applied between the first wing 2 and the second wing 3 located on the same side of the fuselage 1 to lock or unlock the first wing 2 and the second wing 3. That is, two sets of the fixed locking mechanisms symmetrically arranged may be arranged on the fuselage 1 of the whole aircraft to lock or unlock the foldable wings on the left and right sides of the fuselage 1. It will be appreciated that each set of fixed locking mechanisms comprises a first set of hollow beams 4, a second set of hollow beams 5, a linear actuator 6 and a movable spar 7.

The first group of hollow beams 4 and the second group of hollow beams 5 are respectively arranged on the first wing 2 and the second wing 3, and the first group of hollow beams 4 and the second group of hollow beams 5 are aligned with each other. The linear actuator 6 is arranged on the first wing 2. A movable spar 7 is slidably arranged in a section of the first set of hollow beams 4 close to the second wing 3, the movable spar 7 abutting against the linear actuator 6.

Wherein the movable spar 7 slides along the first set of hollow beams 4 under the drive of the linear actuator 6 until a part of the movable spar 7 is fixed in the first set of hollow beams 4 and another part of the movable spar 7 is fixed in the second set of hollow beams 5.

The hollow beam is thus fitted with a slidable movable spar 7, which movable spar 7 is driven by a linear actuator 6. After the first group of hollow beams 4 and the second group of hollow beams 5 are aligned with each other, the linear actuator 6 drives the movable wing beam 7 to slide, a part of the movable wing beam 7 enters the second group of hollow beams 5 from the first group of hollow beams 4, so that the first group of hollow beams 4 and the second group of hollow beams 5 are connected together through the movable wing beam 7 to form a whole beam, and therefore the first wing 2 and the second wing 3 form a complete wing structure, and the fixed locking of the whole aircraft wing is completed.

In the embodiment of the disclosure, the first wing 2 is fixedly connected with the fuselage 1 as a fixed wing; the second wing 3 is rotatably connected to the first wing 2 as a movable wing. In particular, the first wing 2 and the second wing 3 may be connected by a connecting rod or a hinge, for example.

As shown in fig. 2(a) -2 (c), the first set of hollow spars 4 and the second set of hollow spars 5 each comprise a plurality of hollow spars 41, and the respective hollow spars 41 in the connecting surfaces of the first airfoil 2 and the second airfoil 3 are aligned with each other. Thus, both wings of the aircraft are of a beam-type layout, each containing a plurality of hollow beams, which are aligned in sequence.

In the disclosed embodiment, each of the first set of hollow beams 4 and the second set of hollow beams 5 is provided with a stop (not shown) therein for limiting the fixed position of the movable spar 7. The stop thus further ensures that a part of the movable spar 7 remains inside the first wing 2 and another part inside the second wing 3 when the wing locking is completed.

In the disclosed embodiment, the number of movable spars 7 is one or more.

As further shown in fig. 2(b) -2 (c), the end of the movable spar 7 is beveled or curved for guiding.

In the disclosed embodiment, the linear actuator 6 includes an electric actuator or a hydraulic actuator.

The above is merely an exemplary description, and the present embodiment is not limited thereto. For example, for the second wing 3 corresponding to the first wing 2 to be foldable, the two wings may have different connection modes according to the requirement of wing folding deformation, for example, the second wing 3 may rotate around the first wing 2 or be folded in other ways, and when recovering from the folding state, the end surfaces of the two wings may be aligned.

For another example, in other embodiments, the linear actuator 6 may also be provided on the second wing 3. Correspondingly, a movable spar 7 may be slidably arranged in a section of the second set of hollow beams 5 close to the first wing 2, the movable spar 7 abutting the linear actuator 6. In this fixed locking mechanism, the movable spar 7 can slide along the second set of hollow beams 5 under the drive of the linear actuator 6 until one part of the movable spar 7 is fixed inside the second set of hollow beams 5 and the other part of the movable spar 7 is fixed inside the first set of hollow beams 4.

Based on the above disclosure, the fixed locking mechanism of the foldable wing of the embodiment specifically works on the following principle: two sections of wings of the foldable wing are connected through hinges or connecting rods, the structures of the inner section of wing and the outer section of wing both comprise a plurality of hollow beams, and a movable wing beam is arranged inside the hollow beam on one side. The movable wing beam is driven by the linear actuator, the end part of the movable wing beam is an inclined plane or a curved surface with a guiding function, when the two sections of wings are recovered from the folded state and the end surfaces of the two sections of wings are aligned, the linear actuator drives the movable wing beam to slide out of the hollow beam of the wing on one side and insert into the hollow beam of the wing on the other side, finally, one part of the movable wing beam is left in the hollow beam of the wing on one side and the other part of the movable wing beam is inserted into the hollow beam of the wing on the other side, and the hollow beams of the wings on the two sides are connected into a whole beam structure through the movable wing beams positioned in the middle, so that wing locking is realized.

To sum up, the fixed locking mechanism of the foldable wing provided by the embodiment of the disclosure comprises a first group of hollow beams, a second group of hollow beams, a linear actuator and a movable wing beam, has a simple structure, realizes wing locking for the foldable wing, and has high reliability and wide application range.

In the description of the present disclosure, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", and the like indicate orientations or positional relationships based on orientations or positional relationships shown in the drawings, which are merely for convenience of description and simplification of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed in a particular orientation, and operate, and thus, should not be construed as limiting the present disclosure. Throughout the drawings, like elements are represented by like or similar reference numerals. Conventional structures or constructions will be omitted when they may obscure the understanding of the present disclosure. And the shapes, sizes and positional relationships of the components in the drawings do not reflect the actual sizes, proportions and actual positional relationships.

Similarly, in the above description of exemplary embodiments of the disclosure, various features of the disclosure are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various disclosed aspects. Reference to the description of the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the disclosure. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present disclosure, "a plurality" means at least two, e.g., two, three, etc., unless explicitly specifically limited otherwise. Furthermore, the word "a" or "an" preceding an element does not exclude the presence of a plurality of such elements.

The above-mentioned embodiments, objects, technical solutions and advantages of the present disclosure are further described in detail, it should be understood that the above-mentioned embodiments are only examples of the present disclosure, and should not be construed as limiting the present disclosure, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present disclosure should be included in the protection scope of the present disclosure.

Claims

1. The utility model provides a fixed locking mechanical system of collapsible wing for the collapsible wing to the aircraft locks or removes the locking, the aircraft includes the fuselage, the middle part of fuselage has connected gradually first wing and second wing from inside to outside, the second wing is equivalent to the collapsible activity of first wing, its characterized in that, the mechanism includes:

the first group of hollow beams and the second group of hollow beams are respectively arranged on the first wing and the second wing, and are aligned with each other;

the linear actuator is arranged on the first wing;

a set of movable spars slidably disposed within a section of the first set of hollow beams adjacent the second wing, the movable spars abutting the linear actuator;

wherein the movable wing beam slides along the first group of hollow beams under the driving of the linear actuator until one part of the movable wing beam is fixed in the first group of hollow beams and the other part of the movable wing beam is fixed in the second group of hollow beams.

2. A fixed locking mechanism for a foldable wing according to claim 1, wherein the first wing is fixedly connected to the fuselage and the first wing is pivotally connected to the second wing.

3. A securing and locking mechanism for a foldable wing according to claim 2, characterised in that the first wing and the second wing are connected by a connecting rod or a hinge.

4. A securing lock mechanism for a foldable wing according to claim 1, wherein the first and second sets of hollow spars each comprise a plurality of hollow spars, each hollow spar in the connecting face of the first and second wings being aligned with each other.

5. A securing and locking mechanism for a foldable wing according to claim 1, characterised in that each of the hollow beams of the first and second set is provided with a stop for limiting the securing position of the movable spar.

6. A fixed locking mechanism for a foldable wing according to claim 1, wherein the movable spar is one or more.

7. A securing and locking mechanism for a foldable wing according to claim 1, wherein the end of the movable spar is beveled or curved for guiding.

8. A securing lock mechanism for a foldable wing according to claim 1, characterised in that the linear actuator comprises an electric actuator or a hydraulic actuator.

9. A fixed locking mechanism for a foldable wing according to claim 1, wherein the second wing moves relative to the first wing between an extended position in which the second wing interfaces flush with an outer end face of the first wing and a folded position.