CN114735197A - Fixed locking mechanism for foldable wings - Google Patents

Abstract

The present disclosure provides a fixing locking mechanism for a foldable wing, which is used for locking or unlocking the foldable wing of an aircraft. The aircraft includes a fuselage, and the middle part of the fuselage is sequentially connected with a first wing and a second wing from the inside to the outside. Two wings, the second wing is equivalent to the foldable movement of the first wing. The mechanism includes a first group of hollow beams and a second group of hollow beams, which are respectively opened on the first wing and the second wing. The first group The hollow beam and the second group of hollow beams are aligned with each other; the linear actuator is arranged on the first wing; a group of movable spar is slidably arranged in a section of the first group of hollow beams close to the second wing, and the movable spar abuts Linear actuator; wherein, driven by the linear actuator, the movable spar slides along the first group of hollow beams until a part of the movable spar is fixed in the first group of hollow beams, and the other part of the movable spar is fixed in the Inside the second group of hollow beams. The present disclosure is simple in structure, realizes wing locking, has high reliability and wide application range.

Description

Fixed locking mechanism for foldable wings

technical field

The present disclosure relates to the technical field of aircraft, and in particular, to a fixed locking mechanism for a foldable wing.

Background technique

The wing is the most important part of the aircraft. The structure of the wing needs to bear the lift, resistance and various bending and torsion moments of the aircraft during flight, and also takes into account the installation requirements of the landing gear, engine, external suspension and aerodynamic rudder surface. The load-bearing components include spar/web arranged in the spanwise direction of the wing, rib arranged perpendicular to the direction of the spar, and the skin covering the outside of the wing, etc.

Foldable wings were first used in military carrier aircraft. The wings can be folded inward when the aircraft is parked on the aircraft carrier deck and hangar, thereby greatly reducing the wingspan and footprint, which is conducive to the deployment of aircraft carriers. With the development of variant technology, the foldable wing has also gradually developed, expanding its scope of application, and various new types of folding wings have gradually appeared. Many variant aircraft can perform wing folding and deformation during flight. Change the wing shape in the flight environment to complete specific flight tasks.

For a foldable wing, the spanwise established structures such as spars and webs are completely broken at the folded part of the wing, and the fixed locking mechanism of the folded wing needs to connect the broken position and make it structurally stronger and stronger. When the stiffness reaches the requirements before breaking, it needs to withstand large forces and moments, and at the same time ensure sufficient reliability.

Among the existing foldable wings and fixed locking mechanisms for folding wings, the most common is the wing folding mechanism used by carrier-based aircraft. This folding mechanism is mainly used in large-scale carrier-based aircraft. Often the chord is relatively small, the thickness of the wing is low, and the single-block or multi-web wing structure is mostly used. For example, the wings of existing carrier-based fighter jets use a large number of fixing pins to pass through the locking holes of two adjacent fins, so that the two end faces of the folded wing are fixed together, thereby completing the locking. However, the fixed locking method of this folding wing mainly has the following deficiencies: (1) It mainly relies on the force transmission of the wing ribs on the two end faces, which is suitable for multi-web or single-piece wings, and is not suitable for large-scale wings. Chord ratio multi-spar wing. (2) The fixing mechanism is more complicated and requires a larger actuator, which is not suitable for small unmanned aircraft. (3) It is mainly suitable for folding the aircraft in the ground stop state, not suitable for deformation and folding in the air.

SUMMARY OF THE INVENTION

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

The present disclosure provides a foldable wing fixing and locking mechanism for locking or unlocking a foldable wing of an aircraft, and for locking or unlocking the foldable wing of an aircraft. The aircraft includes a fuselage, The middle part of the fuselage is sequentially connected with a first wing and a second wing from the inside to the outside, and the second wing is equivalent to the foldable movement of the first wing. The mechanism includes: a first group of hollow beams and a second group of hollow beams, They are respectively installed 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; a group of movable spar is slidably arranged on In a section of the first group of hollow beams close to the second wing, the movable spar abuts the linear actuator; wherein, driven by the linear actuator, the movable spar slides along the first group of hollow beams until the movable spar A part of the movable spar is fixed in the first group of hollow beams, and the other part of the movable spar is fixed in the second group of hollow beams.

Further, the first wing is fixedly connected to the fuselage, and the first wing is rotatably connected to the second wing.

Further, the first airfoil and the second airfoil are connected by connecting rods or hinges.

Further, each of the first group of hollow beams and the second group of hollow beams includes a plurality of hollow beams, and the respective hollow beams in the connecting surface of the first airfoil and the second airfoil are aligned with each other.

Further, limiters are respectively provided in the first group of hollow beams and the second group of hollow beams to limit the fixed position of the movable spar.

Further, there are one or more movable spars.

Further, the end of the movable spar is an inclined surface or a curved surface, which is used 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 a deployed position and a folded position, wherein in the deployed position, the second wing is flush with the outer end surface of the first wing.

Compared with the prior art, the fixing and locking mechanism of the foldable wing provided by the present disclosure has at least the following beneficial effects: the present disclosure has a simple structure, realizes wing locking for the foldable wing, has high reliability, and has a wide application range .

Description of drawings

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

FIG. 1 schematically shows a structural diagram of a fixed locking mechanism of a foldable wing according to an embodiment of the present disclosure;

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

[Description of reference numerals]

1-fuselage; 2-first wing; 3-second wing; 4-first group of hollow beams; 41-hollow beams; 5-second group of hollow beams; 6-linear actuator; 7-movement Spars.

Detailed ways

In order to make the objectives, technical solutions and advantages of the present disclosure clearer, the present disclosure will be further described in detail below with reference to the specific embodiments and the accompanying drawings. Obviously, the described embodiments are some, but not all, embodiments of the present disclosure. Based on the embodiments in the present disclosure, all other embodiments obtained by those of ordinary skill in the art without creative efforts 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 limit the present disclosure. The terms "comprising", "comprising" and the like as used herein indicate 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 specified and limited, the terms "installation", "connection", "connection", "fixation" and other terms should be interpreted in a broad sense, for example, it may be a fixed connection or a detachable connection, It can be a mechanical connection or an electrical connection or can communicate with each other; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal communication between the two elements or the interaction relationship between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present disclosure can be understood according to specific situations.

All terms (including technical and scientific terms) used herein have the meaning as commonly understood by one of ordinary skill in the art, unless otherwise defined. It should be noted that terms used herein should be construed to have meanings consistent with the context of the present specification and should not be construed in an idealized or overly rigid manner.

FIG. 1 schematically shows a structural diagram of a fixed locking mechanism of a foldable wing according to an embodiment of the present disclosure.

As shown in FIG. 1 , an embodiment of the present disclosure provides a foldable wing fixing and locking mechanism for locking or unlocking the foldable wing of an aircraft. The aircraft includes a fuselage 1 . The middle part is sequentially connected with a first wing 2 and a second wing 3 from the inside to the outside, and the second wing 3 is equivalent to the first wing 2 being foldable and movable. The fixed locking mechanism includes a first group of hollow beams 4 , a second group of hollow beams 5 , a linear actuator 6 and a movable spar 7 .

It should be noted that the fixing and locking mechanism of the foldable wing in the embodiment of the present disclosure can be applied between the first wing 2 and the second wing 3 located on the same side of the fuselage 1 , so as to prevent the first wing 2 Lock or unlock with the second wing 3 . That is to say, on the fuselage 1 of the entire aircraft, two sets of the fixed locking mechanisms arranged symmetrically can be arranged to lock or unlock the foldable wings on the left and right sides of the fuselage 1 . It can be understood that each set of fixed locking mechanisms includes a first group of hollow beams 4 , a second group 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 opened 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 . The movable spar 7 is slidably arranged in a section of the first group of hollow beams 4 close to the second wing 3 , and the movable spar 7 abuts against the linear actuator 6 .

Wherein, driven by the linear actuator 6, the movable spar 7 slides along the first group of hollow beams 4 until a part of the movable spar 7 is fixed in the first group of hollow beams 4, and the other part of the movable spar 7 is fixed in the second group of hollow beams 5 .

As a result, a slidable movable spar 7 is fitted in the hollow spar, which is driven by the 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 spar 7 to slide, and a part of the movable spar 7 enters the second group of hollow beams 5 from the first group of hollow beams 4 , the first group of hollow beams 4 and the second group of hollow beams 5 are connected together through the movable spar 7 to form a whole beam, so that the first wing 2 and the second wing 3 form a complete wing structure. The fixed locking of the aircraft wing is completed.

In the embodiment of the present disclosure, the first wing 2 is fixedly connected to the fuselage 1 to serve as a fixed wing; the second wing 3 is rotatably connected to the first wing 2 to serve as a movable wing. Specifically, the first airfoil 2 and the second airfoil 3 may be connected, for example, by connecting rods or hinges.

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

As shown in FIGS. 2( a ) to 2 ( c ), the first group of hollow beams 4 and the second group of hollow beams 5 each include a plurality of hollow beams 41 . The respective hollow beams 41 are aligned with each other. Thus, both wings of the aircraft are of a beam-type layout, each comprising a plurality of hollow beams, which are aligned in sequence.

In the embodiment of the present disclosure, the first group of hollow beams 4 and the second group of hollow beams 5 are respectively provided with limiters (not shown in the figure) to limit the fixed position of the movable spar 7 . Thus, the stopper can further ensure that a part of the movable spar 7 remains inside the first wing 2 and the other part remains inside the second wing 3 when the wing locking is completed.

In the embodiment of the present disclosure, there are one or more movable spars 7 .

Continuing as shown in Figures 2(b) to 2(c), the end of the movable spar 7 is an inclined surface or a curved surface, which is used for guiding.

In the embodiment of the present disclosure, the linear actuator 6 includes an electric actuator or a hydraulic actuator.

The above is only an exemplary description, and this embodiment is not limited thereto. For example, the second wing 3 is equivalent to the foldable movement of the first wing 2, and the wings on both sides can have different connection methods according to the requirements of the folding and deformation of the wing. For example, the second wing 3 can wrap around the first wing 2. Rotated or otherwise folded, the end faces of the two wings can be aligned when restored from the folded state.

For another example, in other embodiments, the linear actuator 6 may also be disposed on the second wing 3 . Correspondingly, the movable spar 7 can be slidably arranged in a section of the second group of hollow beams 5 close to the first wing 2 , and the movable spar 7 abuts against the linear actuator 6 . In this fixed locking mechanism, driven by the linear actuator 6, the movable wing spar 7 can slide along the second group of hollow beams 5 until a part of the movable wing spar 7 is fixed in the second group of hollow beams 5, and the movable wing Another part of the beam 7 is fixed in the first group of hollow beams 4 .

Based on the above disclosure, the specific working principle of the fixing and locking mechanism of the foldable wing in this embodiment is as follows: the two sections of the foldable wing are connected by hinges or connecting rods, and the structure of the inner and outer sections of the wing is There are several hollow beams in each of them, and one side of the hollow beam is arranged with movable spar. The movable spar is driven by a linear actuator, and the end of the movable spar is a slope or curved surface with guiding function. When the two sections of wings are restored from the folded state and the end faces are aligned, the linear actuator drives the movable spar from one side. The hollow spar of the wing slides out inside and is inserted into the hollow spar of the other wing, so that part of the movable spar remains in the hollow spar of one wing and a part is inserted into the hollow spar of the other wing, The hollow beams of the wings on both sides are connected to a whole beam structure through the movable wing spar located in the middle, so as to realize the wing locking.

To sum up, the fixing and locking mechanism of the foldable wing provided by the embodiment of the present disclosure includes the first group of hollow beams, the second group of hollow beams, the linear actuator and the movable wing spar, and has a simple structure, which is suitable for the foldable wing. To achieve wing locking, high reliability and wide application range.

In the description of the present disclosure, it should be understood that the orientations or positional relationships indicated by the terms "upper", "lower", "front", "rear", "left", "right", etc. are based on those shown in the accompanying drawings The orientation or positional relationship is only for the convenience of describing the present disclosure and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present disclosure. Throughout the drawings, the same elements are denoted by the same or similar reference numbers. Conventional structures or constructions will be omitted when it may obscure the understanding of the present disclosure. And the shape, size and positional relationship of each component in the figure do not reflect the actual size, proportion and actual positional relationship.

Similarly, in the above description of exemplary embodiments of the disclosure, various features of the disclosure are sometimes grouped together into a single embodiment, figure or in the description. Description with reference to the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc. means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example includes in at least one embodiment or example of the present disclosure. In this specification, schematic representations of the above terms 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.

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

The specific embodiments described above further describe the purpose, technical solutions and beneficial effects of the present disclosure in detail. It should be understood that the above-mentioned specific embodiments are only specific embodiments of the present disclosure, and are not intended to limit the present disclosure. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present disclosure should be included within the protection scope of the present disclosure.

Claims (9)

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.

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