CN218537114U - Unmanned aerial vehicle and load coupling mechanism - Google Patents
Unmanned aerial vehicle and load coupling mechanism Download PDFInfo
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- CN218537114U CN218537114U CN202222116744.2U CN202222116744U CN218537114U CN 218537114 U CN218537114 U CN 218537114U CN 202222116744 U CN202222116744 U CN 202222116744U CN 218537114 U CN218537114 U CN 218537114U
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Abstract
The utility model provides an unmanned aerial vehicle and a load connecting mechanism, wherein the unmanned aerial vehicle comprises a flying mechanism and a load mechanism, and the gravity center of the load mechanism and the gravity center of the unmanned aerial vehicle are positioned on the same vertical line; the load mechanism is symmetrical arrangement for first vertical face, and the load mechanism is symmetrical arrangement for the vertical face of second, first vertical face and the vertical face mutually perpendicular of second, and first vertical face and the vertical face of second are on a parallel with vertical direction respectively, and the load mechanism is located flight mechanism's below, and the focus of load mechanism and unmanned aerial vehicle's focus are located the vertical face of second. Consequently, load mechanism's focus and unmanned aerial vehicle's focus are located same vertical line, make unmanned aerial vehicle guarantee when the different task loads of adaptation that unmanned aerial vehicle's focus is located same vertical line with load mechanism's focus all the time from this, need not to carry out the counter weight again to the unmanned aerial vehicle after changing the load, is convenient for change the load.
Description
Technical Field
The utility model belongs to the technical field of the aircraft, concretely relates to unmanned aerial vehicle and load coupling mechanism.
Background
At present, along with the development of unmanned aerial vehicle technology, unmanned aerial vehicles can be used in the fields of police, military, city management, meteorology, logistics, emergency rescue, disaster relief and the like, and the unmanned aerial vehicles often carry different load cabins according to different tasks when executing the tasks.
When most unmanned aerial vehicle platforms appear the mounting task load requirement at present, need carry out special design to unmanned aerial vehicle according to the load requirement. The load compartment is arranged at the nose and the engine is arranged at the tail. Unmanned aerial vehicle can only install a load because restriction such as space restriction, weight focus restriction, pneumatic overall arrangement usually, does not change after the unmanned aerial vehicle platform accomplishes the load adaptation usually.
When unmanned aerial vehicle really needs to change load, then need change fuselage equipment arrangement according to fuselage space restriction, need readjust unmanned aerial vehicle's focus according to equipment change, need check the influence of load to the pneumatic appearance of unmanned aerial vehicle again according to the load appearance etc. from this causes to change the load inconvenience.
SUMMERY OF THE UTILITY MODEL
A first object of the utility model is to provide an unmanned aerial vehicle convenient to change load.
A second object of the present invention is to provide a load connecting mechanism which is convenient for replacing a load.
In order to achieve the first purpose, the utility model provides an unmanned aerial vehicle which comprises a flight mechanism and a load mechanism, wherein the load mechanism is detachably connected with the flight mechanism, and the gravity center of the load mechanism and the gravity center of the unmanned aerial vehicle are positioned on the same vertical line; the load mechanisms are symmetrically arranged relative to a first vertical surface, the load mechanisms are symmetrically arranged relative to a second vertical surface, the first vertical surface and the second vertical surface are mutually vertical, the first vertical surface and the second vertical surface are respectively parallel to the vertical direction, the load mechanisms are positioned below the flight mechanism, and the gravity center of the load mechanisms and the gravity center of the unmanned aerial vehicle are positioned on the second vertical surface; the flight mechanisms are symmetrically arranged relative to a third vertical plane, which coincides with the first vertical plane.
It is obvious by above-mentioned scheme, load mechanism's focus and unmanned aerial vehicle's focus are located same vertical line, make unmanned aerial vehicle guarantee when the different task loads of adaptation that unmanned aerial vehicle's focus is located same vertical line with load mechanism's focus all the time from this, need not to carry out the counter weight again to the unmanned aerial vehicle after changing the load, is convenient for change the load.
Preferably, the flight mechanism comprises a fuselage and a first connecting assembly which are fixedly connected with each other in a detachable mode, and the first connecting assemblies are symmetrically arranged with respect to the second vertical plane.
Furthermore, the first connecting assembly comprises a driving part, a limiting part, a driven part and a fixed plate, the driving part is detachably connected to the fixed plate, the limiting part is connected to an output shaft of the driving part, the driven part and the driven part are rotatably connected to the fixed plate, and the fixed plate is assembled on the machine body.
Further, the locating part includes even board and spacing post, and the connecting hole of even board is connected in the output shaft, and spacing post is located the tip of even board and is spacing in order to carry out the follower.
Further, the follower includes main part, first portion and second portion, and the main part is equipped with the driven shaft hole, and the main part is located between first portion and the second portion, and unmanned aerial vehicle's first locating component passes the driven shaft hole and connects in the fixed plate, and first portion is close to spacing post setting for second portion, and the second portion is protruding to the driven piece setting for first portion.
Further, the driven member further comprises a third portion, and the second portion is located between the main body and the third portion.
Furthermore, the driven part comprises a base body, an abutting part and a clamping part, the base body is provided with a driven shaft hole, a second positioning assembly of the unmanned aerial vehicle penetrates through the driven shaft hole and is connected to the fixing plate, the clamping part is arranged close to the driven shaft hole relative to the abutting part, the clamping part comprises a first arm and a second arm, a clamping opening of the clamping part is arranged between the first arm and the second arm, the first arm is arranged close to the main body relative to the second arm, and the length of the first arm is longer than that of the second arm; the first connecting assembly comprises a connecting plate, the first positioning assembly and the second positioning assembly penetrate through the connecting plate, the connecting plate comprises a first limiting protrusion and a second limiting protrusion, the first limiting protrusion is close to the first portion relative to the second limiting protrusion, and an adaptive area for loading and unloading the load mechanism is arranged between the first limiting protrusion and the second arm.
Furthermore, the load mechanism comprises a load cabin and a second connecting assembly which are fixedly connected with each other, and the second connecting assemblies are symmetrically arranged with respect to the second vertical surface.
Furthermore, the second connecting assembly comprises a positioning plate, a base plate and a connecting column, the positioning plate is connected to the upper end face of the load cabin, the base plate is arranged on the end face of the positioning plate, the connecting column is inserted into the base plate, and the connecting column is clamped in the clamping portion of the first connecting assembly; the bottom surface of the load cabin is a plane; the number of the first connecting assemblies and the number of the second connecting assemblies are two respectively.
In order to achieve the second object, the present invention provides a load connection mechanism, the load connection mechanism is located in the above-mentioned unmanned aerial vehicle, the load mechanism includes a first connection component and a second connection component, the first connection component is as above-mentioned, and the second connection component is as above-mentioned.
It is seen by above-mentioned scheme that the focus of load mechanism with unmanned aerial vehicle's focus is located same vertical line, makes unmanned aerial vehicle guarantee when the different task loads of adaptation that unmanned aerial vehicle's focus is located same vertical line with the focus of load mechanism all the time from this, need not to carry out the counter weight again to the unmanned aerial vehicle after changing the load, is convenient for change the load.
Drawings
The invention is further described with reference to the accompanying drawings, in which the embodiments do not constitute any limitation to the invention, and for a person skilled in the art, other figures may be derived from the following drawings without inventive step.
Figure 1 is a structure diagram of an unmanned aerial vehicle embodiment.
Fig. 2 is a local structure diagram of unmanned aerial vehicle embodiment.
Fig. 3 is an enlarged view of a portion of the structure shown in fig. 2.
Figure 4 is a local structure diagram of a first connection assembly of unmanned aerial vehicle embodiment.
Figure 5 is a local structure diagram of an unmanned aerial vehicle embodiment.
Fig. 6 is an enlarged view of a portion of the structure shown in fig. 5.
Fig. 7 is a partial structure exploded view of an embodiment of the unmanned aerial vehicle of the present invention.
Fig. 8 is an enlarged view of a portion of the structure shown in fig. 7.
Fig. 9 is a local structure diagram of the first connection assembly of the unmanned aerial vehicle embodiment when in the first state.
Fig. 10 is a partial structure diagram of the first connection assembly of the unmanned aerial vehicle of the present invention in the second state.
Fig. 11 is a local structure diagram of the first connection assembly of the unmanned aerial vehicle embodiment when being in the third state.
The reference numbers indicate: a drone 100; a flying mechanism 1; a load mechanism 2; a body 3; a first connection assembly 4; a driving member 6; a stopper 7; a driven member 8; a driven member 9; a fixing plate 10; a connecting plate 11; a lid 12; a connecting plate 13; a stopper post 14; a main body 15; a first portion 16; a second portion 17; a third portion 18; a base 19; an abutment 20; an engaging portion 21; a first arm 22; a second arm 23; a snap-fit opening 24; a first stopper protrusion 25; a second stopper protrusion 26; a compliant zone 27; a load compartment 28; a second connecting assembly 29; a positioning plate 30; a substrate 31; a connecting post 32; a stopper 33.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention.
Referring to fig. 1, the unmanned aerial vehicle 100 provided by this embodiment includes a flight mechanism 1 and a load mechanism 2, the load mechanism 2 is detachably connected to the flight mechanism 1, and the center of gravity of the load mechanism 2 and the center of gravity of the unmanned aerial vehicle 100 are located on the same vertical line. The center of gravity of the drone 100 is the overall center of gravity of the drone after the flight mechanism 1 and the loading mechanism 2 are connected to each other.
The load mechanisms 2 are symmetrically arranged relative to a first vertical plane A, the load mechanisms 2 are symmetrically arranged relative to a second vertical plane B, the first vertical plane A and the second vertical plane B are perpendicular to each other, the first vertical plane A and the second vertical plane B are respectively parallel to the vertical direction, the load mechanisms 2 are located below the flight mechanism 1, and the gravity centers of the load mechanisms 2 and the unmanned aerial vehicle 100 are located on the second vertical plane B; the flying machine 1 is arranged symmetrically with respect to a third vertical plane C, which coincides with the first vertical plane a.
Referring to fig. 2 and 3, the flying mechanism 1 includes a fuselage 3 and a first connecting assembly 4 fixedly connected to each other in a detachable manner, and a plurality of the first connecting assemblies 4 are symmetrically arranged with respect to the second vertical plane B. Fuselage 3 is equipped with holding tank 5, and holding tank 5 extends to the inboard of fuselage 3 from the bottom surface of fuselage 3, and at least one first connecting component 4 has been arranged to each holding tank 5. In this embodiment, the number of the first connecting elements 4 is two, the number of the accommodating grooves 5 is also two, and the number of the accommodating grooves 5 corresponds to the number of the first connecting elements 4 one by one.
Referring to fig. 2 to 4, the first connecting assembly 4 includes a driving member 6, a limiting member 7, a driven member 8, a driven member 9, a fixing plate 10, a connecting plate 11 and a cover 12, wherein the cover 12 covers the connecting plate 11, the cover 12 is screwed to the connecting plate 11, and the cover 12 is not shown in fig. 4. In the present embodiment, the fixing plate 10, the connecting plate 11 and the cover 12 are integrally formed.
The driving member 6 is detachably connected to the fixing plate 10 by a screw connection, the limiting member 7 is connected to an output shaft of the driving member 6, the driven member 9 and the driven member 8 are rotatably connected to the fixing plate 10, and the fixing plate 10 is detachably fixed to the body 3 by a screw connection.
The driving member 6 may preferably be an electrically controlled motor, and the limiting member 7 may be detachably and fixedly connected to the output shaft of the driving member 6 by a key connection or an interference fit.
The limiting part 7 comprises a connecting plate 13 and a limiting column 14, the connecting hole of the connecting plate 13 is connected to the output shaft, the limiting column 14 is located at the end part of the connecting plate 13 to limit the driven part 8, and the limiting column 14 can be located at the end part of the connecting plate 13 through threaded connection.
The driven member 8 further comprises a third portion 18, the second portion 17 being located between the main body 15 and the third portion 18, the third portion 18 projecting towards the driving member 6 relative to the second portion 17. In the present embodiment, the follower 8 is an integrally molded component.
The driven part 9 includes a base 19, an abutting portion 20, and an engaging portion 21, the base 19 is provided with a driven shaft hole, the second positioning assembly of the drone 100 passes through the driven shaft hole and is connected to the fixing plate 10, and the engaging portion 21 is disposed near the driven shaft hole relative to the abutting portion 20.
The engaging portion 21 includes a first arm 22 and a second arm 23, an engaging opening 24 of the engaging portion 21 is provided between the first arm 22 and the second arm 23, the engaging opening 24 is provided in a U-shape, the first arm 22 is provided close to the main body 15 relative to the second arm 23, and the length of the first arm 22 is longer than that of the second arm 23. In the present embodiment, the driven member 9 is an integrally molded member.
The first positioning assembly and the second positioning assembly respectively comprise a bolt and a nut, the first positioning assembly and the second positioning assembly penetrate through the connecting plate 11 and the fixing plate 10, the first positioning assembly is assembled on the fixing plate 10 and the connecting plate 11 through threaded connection so as to enable the driven piece 8 to rotate relative to the fixing plate 10 and the connecting plate 11, and the second positioning assembly is assembled on the fixing plate 10 and the connecting plate 11 through threaded connection so as to enable the driven piece 9 to rotate relative to the fixing plate 10 and the connecting plate 11.
The follower 8 pivots about the center of the follower shaft hole, and the follower 9 pivots about the center of the follower shaft hole located above the center of the follower shaft hole.
The connecting plate 11 comprises a first stop projection 25 and a second stop projection 26, the first stop projection 25 being located close to the first portion 16 with respect to the second stop projection 26, and an adapter 27 for mounting and dismounting the load mechanism 2 being provided between the first stop projection 25 and the second arm 23.
The connecting plate 11 is provided with a limiting body 33, the limiting body 33 is positioned on the first limiting protrusion 25 and the second limiting protrusion 26, and the limiting body 33 is close to the second limiting protrusion 26 and far away from the first limiting protrusion 25 along the horizontal direction.
Referring to fig. 5 to 8, the load mechanism 2 comprises a load compartment 28 and a second connecting assembly 29 fixedly connected to each other, and a plurality of the second connecting assemblies 29 are arranged symmetrically to each other with respect to the second vertical plane B.
The bottom surface of the load compartment 28 is a plane so as to support the body of the drone 100 with the load compartment 28, and the parking, taking off and landing of the drone 100 can all be supported through the bottom surface of the load compartment 28.
The second connecting assembly 29 comprises a positioning plate 30, a base plate 31 and a connecting column 32, the positioning plate 30 is connected to the upper end face of the load compartment 28, the base plate 31 is arranged on the end face of the positioning plate 30, the connecting column 32 is inserted into the base plate 31, and the connecting column 32 is clamped in the clamping portion 21. The positioning plate 29 can be connected to the upper end surface of the load compartment 28 through a connection structure such as a threaded connection, a clamping connection or a welding connection, the base plate 31 can be connected to the positioning plate 30 through a connection structure such as a threaded connection, a welding connection or an integral forming connection, and the connecting column 32 can be fixedly connected to the base plate 31 through a connection structure such as a clamping connection or an interference fit connection.
The number of the second connecting components 29 is two, each first connecting component 4 is connected with one second connecting component 29, and the number of the first connecting components 4 corresponds to the number of the second connecting components 29 one by one.
In the present embodiment, the number of the second connecting members 29 is two
The utility model provides a pair of load coupling mechanism is used for unmanned aerial vehicle 100, load coupling mechanism is located as above unmanned aerial vehicle 100 in, load mechanism 2 includes first connecting elements 4 and second coupling assembling 29, first connecting elements 4 be as above first connecting elements 4, second coupling assembling 29 be as above second coupling assembling 29.
Referring to fig. 1 to 9, the first connecting assembly 4 is in the first state, and the connecting column 32 is located in the engaging opening 24, and at this time, the second portion 17 and the abutting portion 20 are abutted against each other to locate the driven member 9 by the driven member 8, so that the driven member 9 is prevented from rotating under the action of gravity of the load mechanism 2, and the unmanned aerial vehicle 100 reliably carries the load.
Referring to fig. 1 to 8 and 10, when the unmanned aerial vehicle 100 needs to unload the load, the driving member 6 drives the driven member 8 to rotate clockwise in fig. 10, the second portion 17 acts on the abutting portion 20 to drive the driven member 9 to rotate counterclockwise in fig. 10, after the driven member 8 rotates to a predetermined angle, the limiting body 33 of the connecting plate 11 abuts against the third portion 18 to limit the rotation of the driven member 8, the second portion 17 is separated from the abutting portion 20, and at this time, the first connecting assembly 4 is in the second state.
Referring to fig. 1 to 9 and 11, the first connecting assembly 4 is in the third state, after the second portion 17 and the abutting portion 20 are separated from each other, the driven member 9 rotates clockwise in fig. 11 under the action of the gravity of the loading mechanism 2, after the driven member 9 rotates to a predetermined angle, the first arm 22 can abut against the second limiting protrusion 26, the second limiting protrusion 26 can limit the rotation of the driven member 9, and the connecting column 32 can automatically separate from the engaging opening 24 and separate from the first connecting assembly 4 after passing through the suitable area 27, so that the unloading of the loading compartment 28 is realized.
When the load compartment 28 needs to be mounted, the connecting rod 32 moves up into the engaging opening 24 after passing through the adaptive area 27, the connecting rod 32 applies force to the driven element 9, the driven element 9 rotates counterclockwise in fig. 11 under the upward acting force from the load mechanism 2, the driving element 6 drives the limiting element 7 to rotate counterclockwise in fig. 11, and the driven element 8 rotates counterclockwise in fig. 11 under the action of gravity because the first portion 16 is arranged close to the driven shaft hole relative to the second portion 17. Subsequently, the load mechanism 2 can no longer apply an upward urging force to the follower 9, the second portion 17 can apply an urging force to the follower 9, the follower 9 can rotate clockwise in fig. 11 under the action of the weight of the load mechanism 2 and the urging force of the second portion 17, and after the abutting portion 20 abuts against the second portion 17, the follower 8 and the follower 9 are no longer rotated, the first connecting unit 4 is in the first state shown in fig. 9, and the flying mechanism 1 is securely mounted on the load mechanism 2.
The focus of load mechanism 2 and unmanned aerial vehicle 100 are located same vertical line, make unmanned aerial vehicle 100 guarantee when the different task loads of adaptation from this that unmanned aerial vehicle 100's focus is located same vertical line with load mechanism 2's focus all the time, load evenly places in load cabin 28, need not to change unmanned aerial vehicle 100 after the load and carry out the counter weight again, is convenient for change load, more can prevent to produce harmful effects to unmanned aerial vehicle 100's overall aerodynamic characteristic.
Because the load cabin 28 is located below the flight mechanism 1 and below the aircraft body, the volume of the load cabin 28 is not limited by the structure of the aircraft body of the unmanned aircraft, the volume of the load cabin 28 can be increased, moreover, the task load can be prevented from being interfered by the aircraft body, the undercarriage and the propeller, the visual field range of the task load is increased, further, the visual field problem of the task load is not considered by the aircraft body, and the aircraft body can be streamlined, so that the appearance is neat, and the aerodynamic resistance is reduced.
The first connecting component 4 and the second connecting component 29 are used for connecting and detaching the flying mechanism 1 and the load mechanism 2, so that the load mechanism 2 can be quickly assembled and disassembled, and the unmanned aerial vehicle 100 can conveniently replace task loads to execute tasks such as reconnaissance, routing inspection and logistics transportation.
The unmanned aerial vehicle platform of flight mechanism 1 adopts the eight oar overall arrangement of four-axis that push back that draw in the front, and the wing at both sides respectively is connected with a tail boom, and a set of rotor wing screw (a set of rotor wing screw includes two rotors) is respectively arranged to the front and back end of each tail boom, and unmanned aerial vehicle takes off and descends and uses rotor wing screw to carry out the VTOL.
The empennage is installed to the tail boom, and the fuselage, the wings and the wing body are designed in a fused mode to reduce air resistance.
An engine is respectively arranged to the fuselage front and back end, and the engine of fuselage front end provides the pulling force, and the engine of fuselage rear end provides thrust, provides the power of cruising for unmanned aerial vehicle.
The terms "first", "second" are used for descriptive purposes only and are not to be understood as indicating or implying a 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 present invention, unless otherwise explicitly specified or limited, the terms "connected" and "positioned" are to be understood broadly, and may be, for example, fixedly connected, clamped and positioned, detachably connected, or integrated; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
Finally, it should be emphasized that the present invention is not limited to the above-described embodiments, which are merely preferred examples of the invention, and any modifications, equivalent replacements, improvements and the like made within the spirit and principle of the invention should be included in the protection scope of the invention.
Claims (10)
1. The utility model provides an unmanned aerial vehicle, includes flight mechanism and load mechanism, load mechanism detachably connect in flight mechanism, its characterized in that:
the load mechanism is positioned below the flight mechanism, and the gravity center of the load mechanism and the gravity center of the unmanned aerial vehicle are positioned on the same vertical line;
the load mechanisms are symmetrically arranged relative to a first vertical plane, the load mechanisms are symmetrically arranged relative to a second vertical plane, the first vertical plane and the second vertical plane are perpendicular to each other, the first vertical plane and the second vertical plane are respectively parallel to the vertical direction, and the gravity center of the load mechanisms and the gravity center of the unmanned aerial vehicle are located on the second vertical plane;
the flight mechanism is symmetrically arranged relative to a third vertical plane coincident with the first vertical plane.
2. A drone according to claim 1, characterised in that: the flight mechanism comprises a fuselage and a first connecting assembly which are mutually detachably and fixedly connected, and the first connecting assemblies are symmetrically arranged relative to the second vertical surface.
3. A drone according to claim 2, characterised in that: the first connecting assembly comprises a driving part, a limiting part, a driven part and a fixing plate, the driving part is detachably connected to the fixing plate, the limiting part is connected to an output shaft of the driving part, the driven part and the driven part are rotatably connected to the fixing plate, and the fixing plate is assembled on the machine body.
4. A drone according to claim 3, characterised in that: the locating part is including linking board and spacing post, link the connecting hole of board connect in the output shaft, spacing post is located link the tip of board with right the follower carries on spacingly.
5. A drone according to claim 4, characterised in that: the follower includes main part, first portion and second portion, the main part is equipped with driven shaft hole, the main part is located first portion with between the second portion, unmanned aerial vehicle's first positioning subassembly passes driven shaft hole and connect in the fixed plate, first portion for the second portion is close to spacing post setting, the second portion for the first portion is protruding to the driven piece setting.
6. A drone according to claim 5, characterised in that: the follower further includes a third portion, the second portion being located between the body and the third portion.
7. A drone according to claim 6, characterised in that: the driven part comprises a base body, an abutting part and a clamping part, the base body is provided with a driven shaft hole, a second positioning assembly of the unmanned aerial vehicle penetrates through the driven shaft hole and is connected to the fixing plate, the clamping part is arranged close to the driven shaft hole relative to the abutting part, the clamping part comprises a first arm and a second arm, a clamping opening of the clamping part is arranged between the first arm and the second arm, the first arm is arranged close to the main body relative to the second arm, and the length of the first arm is longer than that of the second arm; the first connecting assembly comprises a connecting plate, the first positioning assembly and the second positioning assembly penetrate through the connecting plate, the connecting plate comprises a first limiting protrusion and a second limiting protrusion, the first limiting protrusion is close to the first portion relative to the second limiting protrusion, and a motion adaptive area for loading and unloading the load mechanism is arranged between the first limiting protrusion and the second arm.
8. A drone according to any one of claims 2 to 7, characterised in that: the load mechanism comprises a load cabin and second connecting assemblies which are fixedly connected with each other, and the second connecting assemblies are symmetrically arranged relative to the second vertical surface.
9. A drone according to claim 8, characterised in that: the second connecting assembly comprises a positioning plate, a base plate and a connecting column, the positioning plate is connected to the upper end face of the load cabin, the base plate is arranged on the end face of the positioning plate, the connecting column is inserted into the base plate, and the connecting column is clamped in the clamping part of the first connecting assembly; the bottom surface of the load cabin is a plane; the number of the first connecting assembly and the second connecting assembly is two.
10. A load coupling mechanism located within an unmanned aerial vehicle according to any of claims 8 to 9, the load coupling mechanism comprising a first coupling assembly according to any of claims 8 to 9 and a second coupling assembly according to any of claims 8 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222116744.2U CN218537114U (en) | 2022-08-11 | 2022-08-11 | Unmanned aerial vehicle and load coupling mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222116744.2U CN218537114U (en) | 2022-08-11 | 2022-08-11 | Unmanned aerial vehicle and load coupling mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218537114U true CN218537114U (en) | 2023-02-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222116744.2U Active CN218537114U (en) | 2022-08-11 | 2022-08-11 | Unmanned aerial vehicle and load coupling mechanism |
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| Country | Link |
|---|---|
| CN (1) | CN218537114U (en) |
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2022
- 2022-08-11 CN CN202222116744.2U patent/CN218537114U/en active Active
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