CN218142089U

CN218142089U - Hinge assembly and flight equipment

Info

Publication number: CN218142089U
Application number: CN202221515807.5U
Authority: CN
Inventors: 吴旭民; 朱杰
Original assignee: Guangzhou Xaircraft Technology Co Ltd
Current assignee: Guangzhou Xaircraft Technology Co Ltd
Priority date: 2022-06-16
Filing date: 2022-06-16
Publication date: 2022-12-27
Anticipated expiration: 2032-06-16

Abstract

The application provides an articulated components and flight equipment, articulated components includes: the guide rod is arranged to be installed on a machine body of the flight equipment, and the guide rod is installed to be capable of moving relative to the machine body along the length direction; and a first connecting end of the universal joint is connected with one end, extending out of the fuselage, of the guide rod, and a second connecting end of the universal joint is connected with the folding wing of the flight equipment. The technical scheme that this application provided can solve among the prior art folding wing and exert great moment because of self weight to the junction and lead to the pin joint structure of junction to produce the problem damaged.

Description

Hinge assembly and flight equipment

Technical Field

The application relates to flight equipment, in particular to a hinge assembly for connecting folding wings and flight equipment.

Background

In the prior art, a folding wing on a flight device is generally configured to be folded through a rotating shaft, for example, an existing wing folded up and down is implemented through a hinge mechanism disposed on the wing near the upper or lower surface, and is locked through a latch. Wing structures that fold obliquely aft are typically provided with an oblique pivot axis in the wing and one or more latches at the leading and trailing edges of the wing.

However, the existing folding wings are usually folded in a hydraulic or electric manner, and for low-cost wings which are folded in a manual operation manner, if the folding wings are pivoted by using a rotating shaft, a user needs to lift the folding wings to maintain the folding wings and the fuselage at the same height when manually operating the folding wings, and when the user loses his hands and does not lift the wings, the wings exert a large moment on the connection due to the weight of the wings, so that the pivoting structures at the connection are damaged or broken.

SUMMERY OF THE UTILITY MODEL

In view of this, the present application provides a hinge assembly and a flight device to solve the problem that a pivot structure at a connection portion of a folding wing is easily broken or broken.

The present application provides a hinge assembly, the hinge assembly comprising:

the guide rod is arranged to be installed on a machine body of the flight equipment, and the guide rod is installed to be capable of moving relative to the machine body along the length direction;

and a first connecting end of the universal joint is connected with one end, extending out of the fuselage, of the guide rod, and a second connecting end of the universal joint is connected with the folding wing of the flight equipment.

Optionally, the hinge assembly further comprises a rotating portion for connecting with the folding wing, and the second connecting end of the universal joint is connected to the rotating portion.

Optionally, the gimbal is provided as a hollow structure through which wires can pass.

Optionally, an intermediate connection portion is disposed between the first connection end and the second connection end of the universal joint, and the first connection end and the second connection end are respectively hinged to the intermediate connection portion;

and a channel for passing through a wire is formed between the first connecting end and the middle connecting part and/or between the second connecting end and the middle connecting part respectively.

Optionally, the first connecting end includes two first connecting lugs extending towards the middle connecting portion, and the middle connecting portion includes two third connecting lugs extending towards the first connecting end; each first connecting lug corresponds to one third connecting lug respectively and is rotatably connected through a rotating shaft, and a first channel capable of passing through a wire is formed between the two first connecting lugs;

and/or the second connecting end comprises two second engaging lugs extending towards the intermediate connecting part, and the intermediate connecting part comprises two fourth engaging lugs extending towards the second connecting end; each second connecting lug corresponds to one fourth connecting lug respectively and is connected through the pivot rotation, forms the second passageway that can pass the wire rod between two the second connecting lug.

Optionally, the hinge assembly further includes a guide sleeve for being fixed to the body, the guide rod is configured to be axially movable along the guide sleeve, and the guide rod is configured to be rotatable in the guide sleeve.

According to another aspect of the present application, there is also provided a flying apparatus comprising a fuselage, a folding wing foldable relative to the fuselage, and a hinge assembly as described above;

the guide rod of the hinge assembly is connected to the fuselage, and the second connecting end of the universal joint is connected to the folding wing.

Optionally, the flight device further includes a locking assembly configured to connect and fix the foldable wing to the fuselage when the foldable wing is in an unfolded state during flight;

the locking assemblies are respectively arranged on two opposite sides of the hinge assembly, and each locking assembly comprises a first connecting portion connected to the fuselage, a second connecting portion connected to the folding wing and a locking component used for locking the first connecting portion and the second connecting portion together.

According to still another aspect of the present application, there is also provided a flying apparatus, including a fuselage, a folding wing foldable relative to the fuselage, and a hinge assembly for rotatably connecting the folding wing to the fuselage;

the hinge structure comprises a universal joint, a first connecting end of the universal joint is connected to the fuselage, a second connecting end of the universal joint is connected to the folding wing, and the folding wing can rotate relative to the fuselage through the universal joint in the folding process.

Optionally, an intermediate connection portion is disposed between the first connection end and the second connection end of the universal joint, and the first connection end and the second connection end are hinged to the intermediate connection portion respectively;

wherein a channel for passing through a wire is formed between the first connecting end and/or the second connecting end and the intermediate connecting part.

In the technical scheme that this application provided, folding wing adopts the mode of being connected through universal joint and fuselage are articulated, like this, after the fixed connection disconnection of folding wing and fuselage, even the user loses the hand and does not hold folding wing, folding wing can pass through the universal joint and rotate downwards to can not cause the damage to the component of junction. Therefore, the technical scheme that this application provided can solve among the prior art folding wing and exert great moment to the junction because of self weight and lead to the articulated structure of junction to produce the problem damaged.

Additional features and advantages of the present application will be described in detail in the detailed description which follows.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the application and, together with the description, serve to explain the application and are not intended to limit the application. In the drawings:

FIG. 1 is a schematic view of a hinge assembly according to one embodiment of the present application;

FIG. 2 is an enlarged view of FIG. 1 at A;

FIG. 3 is a schematic view of a guide rod and a guide sleeve in the hinge assembly according to one embodiment;

FIG. 4 is a schematic structural diagram of a flying apparatus according to one embodiment of the present application;

FIG. 5 is an enlarged view of FIG. 4 at B;

FIG. 6 is a schematic view of the structure of FIG. 5 after the fuselage and the folding wings are hidden;

fig. 7 is a top view of fig. 6.

Description of the reference numerals:

1-a hinge assembly; 11-a guide bar; 111-a spacing post; 112-shaft sleeve; 12-a rotating part; 13-a universal joint; 131-a first connection end; 1311 a first connection lug; 132-a second connection end; 1321-a second engaging ear; 133-intermediate connection; 1331-a third engaging lug; 1332-a fourth engaging tab; 14-a guide sleeve; 141-axial grooves; 142-a circumferential groove; 2-a first locking assembly; 3-a second locking assembly; 100-a fuselage; 101-a first rib; 102-a second rib; 200-folding wings; 201-third rib plate; 202-fourth rib.

Detailed Description

The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. In the present application, the embodiments and the features of the embodiments may be combined with each other without conflict.

In the description of the present application, it is to be understood that the terms "central," "longitudinal," "lateral," "upper," "lower," "left," "right," "vertical," "horizontal," "top," "bottom," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present application and to simplify the description, but are not intended to indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and are not to be construed as limiting the present application. Further, "inner and outer" refer to inner and outer relative to the contour of each member itself.

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 to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature.

The present application provides a hinge assembly 1 for hingedly connecting a folding wing to a fuselage, as shown in fig. 1, the hinge assembly 1 comprising:

a guide bar 11, the guide bar 11 being provided for mounting to a fuselage of the flight apparatus, and the guide bar 11 being mounted so as to be movable in a longitudinal direction relative to the fuselage;

the universal joint 13, a first connecting end 131 of the universal joint 13 is connected with one end of the guide rod 11 for extending out of the fuselage, and a second connecting end 132 is used for connecting with a folding wing of the flight equipment.

The fuselage described in the application includes a fuselage body, and may further include a fixed wing portion disposed on the fuselage body, and the folding wing may be connected to the fuselage body, or may be connected to the fixed wing portion.

The application provides a hinge assembly, when using, the guide bar 11 is movably installed in the fuselage, the second link 132 of universal joint 13 is connected in folding wing (can be directly connected or indirectly connected), when folding wing is folding, can at first make the fixed connection disconnection of folding wing and fuselage, then make folding wing move certain distance in the direction of keeping away from the fuselage, guide bar 11 moves to the direction of keeping away from the fuselage along length direction, the removal of guide bar 11 can lead folding wing along the removal of keeping away from the fuselage direction, then folding wing can rotate to folding through universal joint 13.

The folding direction of the folding wing is not limited in the present application, and in some embodiments, the folding wing can be rotated upward or downward through the universal joint 13 after moving a certain distance away from the fuselage, that is, folded upward or downward relative to the fuselage. In some embodiments, the guide rod 11 may be further configured to rotate in a circumferential direction, and after the foldable wing and the guide rod 11 are pulled to move a certain distance in a direction away from the fuselage, the foldable wing is rotated by a preset angle around the axis of the guide rod 11 (for example, the foldable wing rotates by 90 degrees from a horizontal state to a vertical state), and then is folded backwards relative to the fuselage through the universal joint 13.

In this application, folding wing adopts the articulated mode of being connected of universal joint 13 and fuselage, and after the fixed connection disconnection of folding wing and fuselage, even the user is lost the hand and does not lift folding wing, folding wing can be through universal joint 13 downwardly rotating to can not lead to the component of junction to cause the damage because of the weight of folding wing to the moment of force that applies the junction.

Therefore, the hinge assembly provided by the application can solve the problem that the hinge structure of the joint is damaged because the folding wing exerts large moment on the joint due to self weight in the prior art.

In one embodiment of the application, the articulation assembly further comprises a rotating part 12 for connection with a folding wing of a flying apparatus, the second connection end 132 of the universal joint 13 being connected to the rotating part 12. Of course, in another embodiment, the second connection end 132 of the universal joint 13 may be directly connected to the folding wing without providing the rotating portion 12.

The universal joint 13 may have various structural forms, and the present application is not limited thereto.

Alternatively, the gimbal 13 is provided as a hollow structure through which a wire can pass. This facilitates the arrangement of the wires of the flying apparatus.

Optionally, an intermediate connection portion 133 is disposed between the first connection end 131 and the second connection end 132 of the universal joint 13, and the first connection end 131 and the second connection end 132 are respectively hinged to the intermediate connection portion 133; wherein a channel for passing the wire is formed between the first connection end 131 and the intermediate connection portion 133 and/or between the second connection end 132 and the intermediate connection portion 133.

In one embodiment, the specific structure of the universal joint 13 is as shown in fig. 1 and 2, the first connection end 131 of the universal joint 13 includes two first connection lugs 1311 protruding toward the intermediate connection portion 133, and the intermediate connection portion 133 includes two third connection lugs 1331 protruding toward the first connection end 131; wherein, each first engaging lug 1311 is rotatably connected to one third engaging lug 1331 through a rotating shaft, and a first channel M capable of passing through a wire is formed between the two first engaging lugs 1311.

Alternatively, each first connection lug 1311 and the corresponding third connection lug 1331 are rotatably connected by an independent rotation shaft, so that the problem that the two first connection lugs 1311 are connected by a common rotation shaft to interfere with the wire passing through the first channel M can be avoided.

The second connection end 132 includes two second engaging lugs 1321 protruding toward the intermediate connection portion 133, and the intermediate connection portion 133 includes two fourth engaging lugs 1332 protruding toward the second connection end 132; each second engaging lug 1321 is rotatably connected to one fourth engaging lug 1332 through a rotating shaft, and a second passage N through which a wire can pass is formed between the two second engaging lugs 1321.

Optionally, each second engaging lug 1321 and the corresponding fourth engaging lug 1332 are rotatably connected through an independent rotating shaft, so that the problem that two second engaging lugs 1321 are connected through a common rotating shaft to easily cause interference with a wire passing through the second channel N can be avoided.

In this embodiment, the first connection end 131 of the universal joint 13 is provided with a projection (or flange) which projects in the radial direction and has a mounting hole, and the first connection end 131 can be connected to the projection (or flange) which projects in the radial direction on the guide bar 11 by a bolt passing through the projection. Similarly, the second connection end 132 of the universal joint 13 is provided with a protrusion (or flange) protruding in the radial direction and having a mounting hole, and the second connection end 132 is connected to the rotating part 12 or the folding wing by a bolt passing through the protrusion.

In one embodiment, as shown in fig. 1 and 3, the hinge assembly 1 further includes a guide sleeve 14 for fixing to the body, the guide rod 11 is disposed to be axially movable along the guide sleeve 14, and the guide rod 11 is disposed to be rotatable within the guide sleeve 14.

Optionally, a limiting structure is arranged between the guide sleeve 14 and the guide rod 11, and the limiting structure is configured to limit axial movement of the guide rod 11 and limit circumferential rotation of the guide rod 11 relative to the guide sleeve 14 when the guide rod 11 extends out from the fuselage to a preset length.

Specifically, as shown in fig. 1 and 3, the limiting structure includes a limiting groove disposed on the guide sleeve 14 and a limiting post 111 protruding from the outer surface of the guide rod 11, and the limiting post 111 is configured to move along the limiting groove. The limiting groove is an L-shaped groove and comprises an axial groove 141 extending axially and a circumferential groove 142 extending circumferentially, the circumferential groove 141 is arranged at one end, close to the universal joint 13, of the axial groove 141, the axial groove 141 limits the guide rod 11 axially, and the circumferential groove 142 limits the rotation of the guide rod 11 circumferentially.

When the folding wing is folded, the folding wing is pulled in the direction far away from the fuselage, in the process that the folding wing and the guide rod 11 move together, the limiting column 111 moves along the axial groove 141 until the limiting column 111 reaches the end part of the axial groove 141 close to the universal joint 13, then the folding wing and the guide rod 11 rotate together, the limiting column 111 enters the circumferential groove 142 from the axial groove 141 to move, the circumferential groove 142 circumferentially limits the rotation of the limiting column 111, and the folding wing is folded towards the rear of the fuselage through the universal joint 13 after rotating around the axis of the guide rod 11 by a preset angle.

When the folding wing is converted from the folding state to the unfolding state (namely, the folding wing is rotated from the folding position close to the fuselage to the outer side to the unfolding state), the folding wing is firstly rotated to the direction approximately consistent with the guide rod 11 through the universal joint 13 and then rotated together with the guide rod 11, the limiting column 111 enters the axial groove 141 along the circumferential groove 142 and then is pushed towards the fuselage, and the folding wing moves towards the fuselage together with the guide rod 11 until the limiting column 111 moves to the end part, far away from the universal joint 13, of the axial groove 141.

It is to be understood that the position limiting structure between the guide sleeve 14 and the guide bar 11 is not limited to the above, and for example, a position limiting post may be provided on the inner side of the position limiting groove 14, and a position limiting groove may be provided on the outer surface of the guide bar 11.

In addition, the above-described scheme is that the folding wings and the guide rods 11 are firstly pulled out away from the fuselage and then rotated by a certain angle, and it can be understood that the scheme of the application does not exclude that the folding wings and the guide rods 11 are firstly rotated by a certain angle and then axially moved in the direction away from the fuselage.

Alternatively, the stopper post 111 is provided away from the end of the guide bar 11 to which the universal joint 13 is connected. As shown in fig. 3, a shaft sleeve 112 is provided at an end of the guide rod 11 away from the universal joint 13, a stopper 111 is provided on the shaft sleeve 112, and the stopper 111 is provided on the guide rod 11 by facilitating the shaft sleeve 112.

According to another aspect of the present application, there is also provided a flying apparatus, as shown in fig. 4-7, comprising a fuselage 100, a folding wing 200 foldable with respect to the fuselage 100, and a hinge assembly 1 as described above.

Wherein the guide rod 11 of the hinge assembly 1 is connected to the fuselage 100, and the second connection end 132 of the universal joint 13 is connected to the folding wing 200.

In one embodiment, the hinge assembly further comprises a rotating part 12, the rotating part 12 being connected to the folding wing 200, and the second connection end 132 of the universal joint 13 being connected to the rotating part 12.

The flight device further comprises a locking assembly configured to couple and secure the folding wing 200 to the fuselage 100 when the folding wing is in the unfolded state during flight.

Wherein the locking assemblies, such as the first locking assembly 2 and the second locking assembly 3 shown in fig. 6 and 7, are respectively disposed at two opposite sides of the hinge assembly 1. Each locking assembly includes a first connection portion connected to the fuselage 200, a second connection portion connected to the folding wing 200, and a locking member for locking the first connection portion and the second connection portion together.

The specific structure of the locking assembly is not limited herein as long as the foldable wing 200 can be fixedly connected to the fuselage 100.

In some embodiments, a rib having a shape corresponding to a cross-sectional shape of a connection between the folding wing 200 and the fuselage 100 is further disposed between the folding wing and the fuselage, so as to function as a streamline for connecting the wing, and the hinge assembly 1, the first locking assembly 2, and the second locking assembly 3 may be connected to the rib.

Specifically, as shown in the embodiment of fig. 5 to 7, a first rib 101 and a second rib 102 are fixed relative to the body 100, and the portions of the hinge assembly 1, the first locking assembly 2, and the second locking assembly 3 fixed relative to the body 100 may be connected to the first rib 101 and the second rib 102. A third rib 201 and a fourth rib 202 are fixed relative to the folding wing 200, and the portions of the hinge assembly 1, the first locking assembly 2, and the second locking assembly 3 fixed relative to the folding wing 200 may be connected to the third rib 201 and the fourth rib 202.

The present application also provides a flying apparatus comprising a fuselage 100, a folding wing 200 foldable relative to the fuselage 100, and a hinge assembly for rotatably connecting the folding wing 200 to the fuselage 100.

Wherein the hinge assembly comprises a universal joint 13, the first connection end 131 of the universal joint 13 is connected to the fuselage 100, the second connection end 132 is connected to the folding wing 200, and the folding wing 200 rotates through the universal joint 13 during the conversion between the unfolded state and the folded state.

An intermediate connecting part 133 is arranged between the first connecting end 131 and the second connecting end 132 of the universal joint 13, and the first connecting end 131 and the second connecting end 132 are respectively hinged with the intermediate connecting part 133. Wherein a passage for passing the wire is formed between the first connection end 131 and/or the second connection end 132 and the intermediate connection portion 133.

In one embodiment, the universal joint 13 may adopt the structure shown in fig. 2, and may also adopt other structural forms, which are not limited herein.

In one embodiment, the folding wing 200 can be first moved a certain distance away from the fuselage 100, then rotated a certain angle around the axis of the guide rod 11, and then folded back by the universal joint 13, as described above. In other embodiments, the folding wings 200 can also be folded up or down directly by the universal joints 13.

According to the flight equipment provided by the application, the folding wings 200 are hinged to the fuselage 100 through the universal joints 13, when the folding wings 200 are folded, if the folding wings 200 are not lifted, the folding wings 200 can rotate downwards through the universal joints 200, and the problem that the joints are damaged due to the fact that the gravity of the folding wings 200 exerts large moment on the joints cannot occur.

The above description is only exemplary of the present application and should not be taken as limiting the present application, as any modifications, equivalents and the like that are within the spirit and principle of the present application should be included in the scope of the present application.

Claims

1. A hinge assembly, characterized in that it comprises:

2. The hinge assembly of claim 1, further comprising a rotating portion for connection with the folding wing, the second connection end of the universal joint being connected to the rotating portion.

3. The hinge assembly of claim 1, wherein the gimbal is provided as a hollow structure through which a wire can pass.

4. The hinge assembly according to claim 1, wherein an intermediate connecting portion is provided between the first connecting end and the second connecting end of the universal joint, and the first connecting end and the second connecting end are respectively hinged to the intermediate connecting portion;

5. The hinge assembly of claim 4, wherein the first connection end includes two first connection ears projecting toward the intermediate connection portion, the intermediate connection portion including two third connection ears projecting toward the first connection end; each first connecting lug corresponds to one third connecting lug respectively and is rotatably connected through a rotating shaft, and a first channel capable of passing through a wire is formed between the two first connecting lugs;

6. A hinge assembly according to any one of claims 1 to 5, further comprising a guide sleeve for securing to the body, the guide rod being arranged to be axially movable along the guide sleeve and to be rotatable within the guide sleeve.

7. A flying apparatus comprising a fuselage, a folding wing foldable relative to the fuselage and an articulation assembly according to any of claims 1-6;

8. The heeling apparatus of claim 7, further comprising a locking assembly configured to couple and secure the folding wing to the fuselage when the folding wing is in an extended position during heeling;

9. A flying apparatus comprising a fuselage, a folding wing foldable relative to the fuselage, and a hinge assembly for rotatably connecting the folding wing to the fuselage;

the hinge assembly comprises a universal joint, a first connecting end of the universal joint is connected to the fuselage, a second connecting end of the universal joint is connected to the folding wing, and the folding wing can rotate relative to the fuselage through the universal joint in the folding process.

10. The flying apparatus as claimed in claim 9, wherein an intermediate connection is provided between the first connection end and the second connection end of the gimbal, and the first connection end and the second connection end are respectively hinged with the intermediate connection;