CN211810192U - Mounting structure and aircraft - Google Patents

Abstract

The utility model discloses a carry structure and aircraft relates to storage logistics technical field. The mounting structure comprises a driving component, a linkage component, a side joint and a lock hook, wherein one end of the linkage component is connected to the driving component, and the other end of the linkage component is abutted against the middle upper part of the lock hook; the middle part of the lock hook is rotationally connected with the side joint, and the lower part of the lock hook is in a hook shape and used for hanging and carrying a cargo box; wherein the side fitting is connected to the inner wall of the aircraft; the driving component is used for driving the linkage component to move so as to control the rotation of the lock hook. This embodiment can accomplish cargo handling fast, can also load bigger goods or container.

Description

Mounting structure and aircraft

Technical Field

The utility model relates to a storage logistics technical field, concretely relates to carry structure and aircraft.

Background

At present, the logistics fixed wing unmanned aerial vehicle adopts modes such as a cargo cabin and a container plate, cargo containers and bulk cargos to load cargos, cargo doors are arranged at the head, the tail, the side edges and the like of the aircraft, and cargos are loaded and unloaded in a manual or mechanical auxiliary mode.

In order to improve the loading and unloading speed, a container which can fully plug all cargo space and a cabin door matched with the container are required to be designed for the aircraft at one time or only a few times, but according to the characteristics of the layout of the aircraft, the cabin door at the side is not too large, the force transmission of the aircraft structure is seriously influenced, the weight is increased, the cabin doors at the head and the tail are influenced by the arrangement of aircraft engines, avionics equipment and the like, a larger cabin door cannot be conveniently or even opened, the loading and unloading of larger goods or containers is influenced if the cabin door cannot be opened sufficiently, and the loading and unloading speed cannot be improved.

SUMMERY OF THE UTILITY MODEL

For solving among the prior art current cargo hold can't open enough big hatch door, influence the loading and unloading of great container, lead to the problem that can't improve handling speed, the utility model provides a load structure and aircraft can accomplish cargo handling fast, can also load great goods or container.

To achieve the above object, according to one aspect of the embodiments of the present invention, a mounting structure is provided.

The utility model discloses carry structure of embodiment includes: drive assembly, interlock subassembly, lateral part connect and latch hook, wherein:

one end of the linkage component is connected to the driving component, and the other end of the linkage component is abutted against the middle upper part of the lock hook;

the middle part of the lock hook is rotatably connected with the side joint, and the lower part of the lock hook is in a hook shape and used for hanging and carrying a cargo box; wherein the side fitting is connected to an interior wall of the aircraft;

the driving component is used for driving the linkage component to move so as to control the locking hook to rotate.

Optionally, the linkage assembly comprises a top sub, an unlocking lever and the rocker arm, wherein:

the top connector is connected to the inner wall of the aircraft;

one end of the unlocking rod is connected to the driving assembly, and the other end of the unlocking rod is rotatably connected with one end of the rocker arm;

the bent part of the rocker arm is rotatably connected with the top connector, when a container is mounted, the other end of the rocker arm is abutted against the upper part of the lock hook, and when the container is not mounted, the other end of the rocker arm is abutted against the middle part of the lock hook.

Optionally, the aircraft further comprises a resilient assembly connected between the rocker arm and an inner wall of the aircraft for applying a downward force to the rocker arm.

Optionally, the resilient assembly comprises a ram joint, a ram and a compression spring, wherein:

the ejector rod joint is connected to the inner wall of the aircraft;

the ejector rod is connected to the ejector rod joint;

the compression spring is sleeved outside the ejector rod, the upper end of the compression spring is connected to the ejector rod connector, and the lower end of the compression spring is propped against the rocker arm.

Optionally, the drive assembly comprises a drive motor and a speed reducer, wherein:

the driving motor is connected to the top of the inner wall of the aircraft;

the speed reducer is connected between the output end of the driving motor and the unlocking rod; the output end of the speed reducer is a worm wheel, and one end of the unlocking rod connected to the speed reducer is a worm.

Optionally, the speed reducer is connected with two unlocking rods located on two sides, and the speed reducer can drive the two unlocking rods to act simultaneously.

Optionally, the locking device further comprises a connecting shaft, and the unlocking rod is connected with the rocker arm, the rocker arm is connected with the top connector, and the latch hook is connected with the side connector through the connecting shaft.

Optionally, the lower portion of the latch hook is in the shape of two parallel straight or oblique curved hooks.

To achieve the above object, according to still another aspect of an embodiment of the present invention, an aircraft is provided.

The utility model discloses an aircraft, its characterized in that is provided with cargo hold, packing box and the utility model discloses a carry structure, wherein:

the cabin door of the cargo cabin is arranged at the belly of the aircraft, and the upper part of the inner wall of the cargo cabin is connected with the carrying structure;

and a hanging rod matched with the hanging structure is arranged at the top of the container.

An embodiment in the above-mentioned utility model has following advantage or beneficial effect:

1. the driving assembly drives the linkage assembly to move, the movement of the linkage assembly can control the lock hook to rotate around the side joint within a certain range, and the hook shape of the lock hook is matched with a cargo box in the rotating process, so that the cargo box is hung from the top;

2. the cargo loading and unloading can be completed rapidly through one or only a few operations, and larger cargos or containers can be loaded, so that the loading and unloading efficiency is high;

3. the elastic assembly can apply downward force to the rocker arm, so that the situation that when the driving assembly breaks down, the rocker arm rotates upwards to be separated from the latch hook, and the latch hook cannot effectively carry a cargo box is avoided;

4. the utility model discloses an aircraft can set up the hatch door at the aircraft belly, and according to the overall arrangement characteristics of aircraft, the abdominal hatch door of aircraft can not influence biography power and the increase weight of aircraft structure, also has no influence to arranging of engine, avionics equipment etc..

Drawings

Fig. 1 is a schematic view of a mounting structure provided in an embodiment of the present invention;

fig. 2 is a schematic view of an aircraft provided by an embodiment of the present invention;

fig. 3 is a schematic view illustrating a cargo compartment, a cargo box and a mounting structure of an aircraft according to an embodiment of the present invention;

fig. 4 is a schematic view of a cargo box of an aircraft according to an embodiment of the present invention.

In the figure, the position of the upper end of the main shaft,

1-a drive assembly; 11-a drive motor; 12-a speed reducer; 2-a linkage assembly; 21-top joint; 22-an unlocking lever; 23-a rocker arm; 3-a lateral joint; 4-a latch hook; 5-an elastic component; 51-ejector pin joint; 52-a top rod; 53-compression spring; 6-connecting shaft; 7-a cargo hold; 8-a cargo box; 81-hanging rod.

Detailed Description

Exemplary embodiments of the invention are described below with reference to the accompanying drawings, in which various details of embodiments of the invention are included to assist understanding, and which are to be considered exemplary only. Accordingly, those of ordinary skill in the art will recognize that various changes and modifications of the embodiments described herein can be made without departing from the scope and spirit of the invention. Also, descriptions of well-known functions and constructions are omitted in the following description for clarity and conciseness.

Fig. 1 is a schematic view of a mounting structure provided in an embodiment of the present invention.

As shown in fig. 1, an embodiment of the present invention provides a mounting structure, which mainly includes: drive assembly 1, interlock subassembly 2, side joint 3 and latch hook 4.

The embodiment of the utility model provides an in, connect drive assembly 1 and lateral part joint 3 in the inner wall of aircraft, the one end of interlock subassembly 2 is connected in drive assembly 1, and the other end of interlock subassembly 2 supports in the well upper portion of latch hook 4, and the middle part of latch hook 4 is rotated and is connected in lateral part joint 3, and the lower part of latch hook 4 is the hook-shaped. Latch hook 4 can rotate around lateral part joint 3, drives interlock subassembly 2 through drive assembly 1 and moves, and interlock subassembly 2's motion can control latch hook 4 at the certain limit internal rotation, and the cooperation of pivoted in-process latch hook 4's hook-shaped completion and packing box realizes carrying packing box 8 from the top, the utility model discloses a carry structure can make aircraft such as fixed wing unmanned aerial vehicle set up the hatch door at aircraft belly, according to the overall arrangement characteristics of aircraft, aircraft belly hatch door can not influence the biography power and the increase weight of aircraft structure, also has no influence to arranging of engine, avionics equipment etc. to just can accomplish cargo handling fast through once or only a few operations, can also load great goods or container, handling efficiency is high.

In the embodiment of the present invention, the linkage assembly 2 may include a top joint 21, an unlocking lever 22 and an L-shaped rocker arm 23.

One end of the unlocking rod 22 is connected to the driving assembly 1, the other end of the unlocking rod 22 is rotatably connected with one end of the rocker arm 23, the top connector 21 is connected to the inner wall of the aircraft, the bent portion of the rocker arm 23 is rotatably connected to the top connector 21, when the cargo box 8 is mounted, the other end of the rocker arm 23 abuts against the upper portion of the latch hook 4, and when the cargo box 8 is not mounted, the other end of the rocker arm 23 abuts against the middle portion of the latch hook 4. The unlocking rod 22 and the L-shaped rocker arm 23 and other parts are supported through the top connector 21, the unlocking rod 22 can move transversely under the driving of the driving assembly 1, so that the rocker arm 23 is driven to rotate around the top connector 21, the contact position of a latch hook 4 of the rocker arm 23 changes along with the rotation, and the latch hook 4 is controlled to rotate within a certain range. When the rocker arm 23 abuts against the upper portion of the latch hook 4, the hook-shaped opening of the latch hook 4 faces the driving assembly 1, and is in a locking state at this time, and when the rocker arm 23 abuts against the middle portion of the latch hook 4, the hook-shaped opening of the latch hook 4 faces obliquely downward, and is in an unlocking state at this time.

The utility model discloses a carry structure can also include elastic component 5. Elastic component 5 is connected between rocker 23 and the inner wall of aircraft, and elastic component 5 is used for exerting decurrent power to rocker 23, avoids when drive assembly 1 breaks down, and rocker 23 upwards rotates and separates with latch hook 4, leads to latch hook 4 can't effectively carry packing box 8.

Specifically, the elastic assembly 5 may include a jack connector 51, a jack 52, and a compression spring 53. Wherein, ejector pin joint 51 is connected in the aircraft inner wall, ejector pin joint 51 is used for supporting ejector pin 52 and compression spring 53, and ejector pin 52 connects in ejector pin joint 51, and compression spring 53 overlaps the outside of locating ejector pin 52, and compression spring 53's upper end connects in ejector pin joint 51. The ejector rod 52 can enable the compression spring 53 to only vertically stretch out and draw back, and meanwhile, the maximum upward rotating angle of the rocker arm 23 can be controlled, the lower end of the compression spring 53 is elastically abutted to the rocker arm 23, the rocker arm 23 can be guaranteed to be in contact with the latch hook 4 through the ejector rod 52 and the compression spring 53, accordingly, the mounting reliability is guaranteed, and the transportation safety is improved. The elastic means is the elastic force and corresponding force action applied by the elastic device in the compressed state to the static connecting piece.

In the embodiment of the present invention, the driving assembly 1 may include a driving motor 11 and a speed reducer 12. Wherein, driving motor 11 is connected in the inner wall top of aircraft, and the output of driving motor 11 passes through speed reducer 12 with unblock pole 22 and is connected. The output end of the speed reducer 12 is a worm wheel, one end of the unlocking rod 22 connected to the speed reducer 12 is a worm, the worm wheel of the speed reducer 12 is matched with the unlocking rod 22, the worm wheel of the speed reducer 12 starts to rotate under the driving of the driving motor 11, and the unlocking rod 22 is driven to transversely move by the matching of the worm wheel and the worm. In addition, the output end of the speed reducer 12 can be two worm gears which act simultaneously, or the worm gears of the speed reducer 12 can be matched with the two unlocking levers 22, so that one driving assembly 1 can drive the two unlocking levers 22.

With continued reference to fig. 1, as a preferred implementation, a mounting structure of an embodiment of the present invention includes: the device comprises a driving motor 11, a speed reducer 12, a top connector 21, an unlocking rod 22, a rocker arm 23, a side connector 3, a latch hook 4, a push rod connector 51, a push rod 52, a compression spring 53 and a connecting shaft 6. The top connector 21, the unlocking rod 22, the rocker arm 23, the side connector 3, the latch hook 4, the ejector rod connector 51, the ejector rod 52, the compression spring 53 and other parts are all two parts and are respectively positioned on two sides of the driving motor 11; the top joint 21 and the side joint 3 may be hinged seats, i.e. the rocker arm 23 and the top joint 21 and the shackle 4 and the side joint 3 are in hinged form. The driving motor 11 and the mandril joint 51 are connected to the top of the inner wall of the aircraft, and the side joint 3 is connected to the upper side part of the inner wall of the aircraft.

Specifically, the components on each side take the following form of connection: one end of the unlocking rod 22 is connected with the output end of the driving motor 11 through the speed reducer 12, the other end of the unlocking rod 22 is connected with one end of the rocker arm 23 through the connecting shaft 6, the unlocking rod 22 and the rocker arm 23 can rotate relatively, the other end of the rocker arm 23 abuts against the upper portion of the locking hook 4, the bent portion of the rocker arm 23 is connected with the top connector 21 through the connecting shaft 6, the rocker arm 23 can rotate around the top connector 21, the middle portion of the locking hook 4 is connected with the side connector 3 through the connecting shaft 6, the locking hook 4 can rotate around the side connector 3, the middle lower portion of the locking hook 4 is in the shape of two straight bent hooks or oblique bent hooks, and the cross section of the locking hook 4 is similar to an inverted. In addition, the connecting shafts 6 used at different positions can be selected to have different sizes according to requirements.

When the cargo box 8 is hung, the driving motor 11 outputs power to the speed reducer 12, the worm wheel at the output end of the speed reducer 12 rotates in the locking direction, the unlocking rod 22 is driven to move transversely to the locking hook 4 through the cooperation of the worm wheel and the worm, the locking hook 4 is pushed to rotate upwards, and the hanging rod 81 of the cargo box 8 is hung between two straight hook shapes or inclined hook shapes of the locking hook 4 to finish hanging.

When the cargo box 8 is unloaded, the driving motor 11 outputs power to the speed reducer 12, the worm wheel at the output end of the speed reducer 12 rotates in the unlocking direction (opposite to the locking direction), the unlocking rod 22 is driven to transversely move towards the speed reducer 12 through the matching of the worm wheel and the worm, the locking hook 4 is pushed to downwards rotate, the hanging rod 81 of the cargo box 8 is separated from the two straight hook shapes or the inclined hook shapes of the locking hook 4, and the unloading is completed.

Fig. 2 is a schematic view of an aircraft provided by an embodiment of the present invention; fig. 3 is a schematic view illustrating a cargo compartment, a cargo box and a mounting structure of an aircraft according to an embodiment of the present invention; fig. 4 is a schematic view of a cargo box of an aircraft according to an embodiment of the present invention.

As shown in fig. 2 to 4, an aircraft provided with a cargo compartment 7, a cargo box 8 and a mounting structure according to an embodiment of the present invention is provided.

The cabin door of the cargo hold 7 is arranged at the belly of the aircraft, and the upper part of the inner wall of the cargo hold 7 is connected with a mounting structure; the top of the cargo box 8 is provided with a hanging rod 81 which is matched with the hanging structure.

The utility model discloses an aircraft can set up the hatch door at the aircraft belly, according to the overall arrangement characteristics of aircraft, the abdominal hatch door of aircraft can not influence biography power and the increase weight of aircraft structure, also has no influence to arranging of engine, avionics equipment etc to just can accomplish cargo handling fast through once or only a few operations, can also load great goods or container, handling efficiency is high.

As a preferred embodiment, multiple sets of mounting structures and multiple containers 8 may be provided within an aircraft setting, with at least two sets of mounting structures being used to mount each container 8. If it is more convenient to hang the cargo box 8 in the cargo compartment 7, the aircraft landing gear can be raised, and a special loading platform, i.e. a pit is dug on the ground, corresponding mechanical equipment is loaded, and the cargo is loaded into the cargo compartment 7, for example, the aircraft landing gear can cooperate with mechanical equipment such as an Automatic Guided Vehicle (AGV) and the like, so that the fully-mechanized operation can be realized.

As can be seen from the above description, the mounting structure and the aircraft of the embodiments of the present invention have at least the following advantages or beneficial effects:

1. the driving assembly 1 drives the linkage assembly 2 to move, the movement of the linkage assembly 2 can control the lock hook 4 to rotate around the side joint 3 within a certain range, and the hook shape of the lock hook 4 is matched with a cargo box in the rotating process, so that the cargo box is hung from the top;

2. the cargo loading and unloading can be completed rapidly through one or only a few operations, and larger cargos or containers can be loaded, so that the loading and unloading efficiency is high;

3. the elastic assembly 5 can apply a downward force to the rocker arm 23, so that the situation that when the driving assembly 1 fails, the rocker arm 23 rotates upwards to be separated from the latch hook 4, and the latch hook 4 cannot effectively mount a cargo box is avoided;

4. the utility model discloses an aircraft can set up the hatch door at the aircraft belly, and according to the overall arrangement characteristics of aircraft, the abdominal hatch door of aircraft can not influence biography power and the increase weight of aircraft structure, also has no influence to arranging of engine, avionics equipment etc..

The above is only a preferred embodiment of the present invention, and should not be limited to the present invention, and any modifications, equivalent replacements, simple improvements and the like made in the spirit of the present invention should be included in the protection scope of the present invention.

Claims (9)

1. The utility model provides a carry structure, its characterized in that includes drive assembly (1), interlock subassembly (2), lateral part joint (3) and latch hook (4), wherein:

one end of the linkage component (2) is connected to the driving component (1), and the other end of the linkage component (2) is abutted against the middle upper part of the locking hook (4);

the middle part of the locking hook (4) is rotatably connected with the side joint (3), and the lower part of the locking hook (4) is hook-shaped and is used for hanging a cargo box (8); wherein the side fitting (3) is connected to an inner wall of the aircraft;

the driving component (1) is used for driving the linkage component (2) to move so as to control the locking hook (4) to rotate.

2. The mounting structure according to claim 1, wherein the linkage assembly (2) comprises a top joint (21), an unlocking lever (22) and an L-shaped rocker arm (23), wherein:

the top joint (21) is connected to the inner wall of the aircraft;

one end of the unlocking rod (22) is connected to the driving assembly (1), and the other end of the unlocking rod (22) is rotatably connected with one end of the rocker arm (23);

the bent part of the rocker arm (23) is rotatably connected to the top connector (21), when the cargo box (8) is mounted, the other end of the rocker arm (23) abuts against the upper part of the latch hook (4), and when the cargo box (8) is not mounted, the other end of the rocker arm (23) abuts against the middle part of the latch hook (4).

3. The mounting structure according to claim 2, further comprising a resilient assembly (5), the resilient assembly (5) being connected between the rocker arm (23) and an inner wall of the aircraft for applying a downward force to the rocker arm (23).

4. Mounting structure according to claim 3, characterized in that the elastic assembly (5) comprises a ram joint (51), a ram (52) and a compression spring (53), wherein:

the ejector rod joint (51) is connected to the inner wall of the aircraft;

the ejector rod (52) is connected to the ejector rod joint (51);

the compression spring (53) is sleeved outside the ejector rod (52), the upper end of the compression spring (53) is connected to the ejector rod joint (51), and the lower end of the compression spring (53) elastically abuts against the rocker arm (23).

5. Mounting structure according to claim 2, characterized in that the drive assembly (1) comprises a drive motor (11) and a speed reducer (12), wherein:

the driving motor (11) is connected to the top of the inner wall of the aircraft;

the speed reducer (12) is connected between the output end of the driving motor (11) and the unlocking rod (22); the output end of the speed reducer (12) is a worm wheel, and one end of the unlocking rod (22) connected to the speed reducer (12) is a worm.

6. The mounting structure according to claim 5, wherein the speed reducer (12) is connected to two unlocking levers (22) on two sides, and the speed reducer (12) can drive the two unlocking levers (22) to act simultaneously.

7. The mounting structure according to claim 2, further comprising a connecting shaft (6), wherein the unlocking lever (22) and the rocker arm (23), the rocker arm (23) and the top joint (21), and the latch hook (4) and the side joint (3) are connected through the connecting shaft (6).

8. Mounting structure according to claim 2, characterized in that the middle and lower part of the locking hook (4) is in the shape of two straight or oblique hooks.

9. An aircraft, characterized in that a cargo hold (7), a cargo box (8) and a mounting structure according to any one of claims 1-8 are provided, wherein:

the cabin door of the cargo cabin (7) is arranged at the belly of the aircraft, and the upper part of the inner wall of the cargo cabin (7) is connected with the mounting structure;

and a hanging rod (81) matched with the hanging structure is arranged at the top of the container (8).

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