A drone fuselage connecting mechanism and a drone

Abstract

The application discloses a fuselage connecting mechanism of a UAV and the UAV. The fuselage connecting mechanism comprises a middle wing butt joint assembly, a first base and a first latch. The first latch is connected to the first side of the first base, and a first plug hole is arranged on the second side of the first latch. The central wing butt joint assembly comprises a second base. A second plug hole is arranged on the third side of the second base. The first latch is plugged into the second plug hole, so that the middle wing butt joint assembly is detachably connected to the central wing butt joint assembly. The fuselage connecting mechanism can conveniently realize the detachable connection between different components of the UAV, and conveniently unlock and lock the different components.

Description

TECHNICAL FIELD

[0001] The present application relates to the unmanned aerial vehicle technical field, especially relates to a fuselage connecting mechanism of unmanned aerial vehicle and unmanned aerial vehicle. BACKGROUND

[0002] Nowadays, the unmanned aerial vehicle is generally mainly composed of body, wing, landing gear, tail wing, rotor and propeller and the like functional components, and develops towards the modularization.

[0003] However, the existing unmanned aerial vehicle is generally assembled by using the mode such as high-strength glue, rivet, screw, welding and the like which can realize the fixed connection between modules, so that it is generally difficult, even impossible to disassemble, separate or needs to be unlocked and locked between modules by means of tools. SUMMARY

[0004] The fuselage connecting mechanism of unmanned aerial vehicle and unmanned aerial vehicle provided by the present application can solve the problem that the functional components in the prior art unmanned aerial vehicle are difficult, even impossible to disassemble and separate.

[0005] To solve the above technical problems, one technical scheme adopted by the present application is to provide a fuselage connecting mechanism of unmanned aerial vehicle, wherein the fuselage connecting mechanism comprises: a middle wing butt joint assembly comprising a first base and a first bolt, the first bolt being connected on a first side of the first base, and a first insertion hole being arranged on a second side of the first bolt; a central wing butt joint assembly comprising a second base, a second insertion hole being arranged on a third side of the second base, and the first bolt being inserted into the second insertion hole to detachably connect the middle wing butt joint assembly and the rotor arm butt joint assembly to the central wing butt joint assembly.

[0006] The fuselage connecting mechanism further comprises: a rotor arm butt joint assembly comprising a third base and a second bolt, the second bolt being connected on a fourth side of the third base, the second bolt being inserted into the first insertion hole and being inserted into the second insertion hole by the first bolt, so as to detachably connect the rotor arm butt joint assembly to the middle wing butt joint assembly and the central wing butt joint assembly.

[0007] The fifth side of the third base is further provided with a pull buckle lock hook, and the sixth side of the second base is further provided with a pull buckle lock, the pull buckle lock being buckled with the pull buckle lock hook; the fifth side of the third base is adjacent to the fourth side thereof, and the sixth side of the second base is adjacent to the third side thereof.

[0008] The sixth side of the second base is further provided with a mounting piece, one side of the mounting piece is further provided with a first mounting hole, the fifth side of the third base is further provided with a second mounting hole corresponding to the first mounting hole, a quick pin is further arranged in the second mounting hole, and part of the quick pin is further inserted into the first mounting hole, so that the rotor arm docking assembly is connected with the central wing docking assembly.

[0009] The end of the quick pin away from the mounting piece is further provided with a pull ring in a ring shape.

[0010] The number of the first pins is two, and the two first pins are arranged on the first side of the third base at intervals; the number of the second pins is two, and the two second pins are arranged on the fourth side of the third base at intervals and are respectively inserted into the first insertion holes of the first pins.

[0011] The edge of the third side of the second base is provided with a ring-shaped groove, and the first side of the first base is further provided with a protruding part corresponding to the ring-shaped groove, and the protruding part is embedded in the ring-shaped groove.

[0012] To solve the above technical problems, another technical solution adopted by the present application is to provide an unmanned aerial vehicle, wherein the unmanned aerial vehicle comprises: a middle wing mechanism, a rotor arm, a central wing mechanism and a fuselage connecting mechanism, the fuselage connecting mechanism comprises a middle wing docking assembly, a rotor arm docking assembly and a central wing docking assembly; wherein the middle wing docking assembly comprises a first base and a first pin, the first pin is connected to the first side of the first base, and a first insertion hole is arranged on the second side of the first pin; the rotor arm docking assembly comprises a third base and a second pin, the second pin is connected to the fourth side of the third base, the second pin is inserted into the first insertion hole, so that the rotor arm docking assembly is detachably connected to the middle wing docking assembly, so that the rotor arm and the middle wing mechanism are connected; the central wing docking assembly comprises a second base, a second insertion hole is arranged on the third side of the second base, and the first pin is inserted into the second insertion hole, so that the middle wing docking assembly and the rotor arm docking assembly are detachably connected to the central wing docking assembly, so that the middle wing mechanism and the rotor arm are connected with the central wing mechanism.

[0013] The unmanned aerial vehicle further comprises a fuselage mechanism, and the fuselage mechanism is connected to the central wing mechanism.

[0014] The fifth side of the third base is further provided with a pull buckle lock hook, and the sixth side of the second base is further provided with a pull buckle lock, the pull buckle lock is buckled with the pull buckle lock hook; wherein the fifth side of the third base is adjacent to the fourth side thereof, and the sixth side of the second base is adjacent to the third side thereof.

[0015] The beneficial effects of the present application are: different from the prior art, the intermediate wing docking assembly in the fuselage connecting mechanism provided by the present application comprises a first base and a first latch connected on the first side of the first base, and a first insertion hole is arranged on the second side of the first latch, and a second insertion hole is further arranged on the third side of the second base of the central wing docking assembly, and the first latch can be inserted into the second insertion hole to detachably connect the intermediate wing docking assembly to the central wing docking assembly, so that the mutual cooperation and docking between the intermediate wing docking assembly and the central wing docking assembly can be realized in the way of latch insertion, the latch insertion is quick and convenient, there is no external resistance source exposed at the docking position between the components, so that the endurance performance of the corresponding unmanned aerial vehicle can be effectively improved, and the connection and cooperation realized is stable and reliable, and the appearance is beautiful. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 is an exploded schematic view of an embodiment of the fuselage connecting mechanism of the unmanned aerial vehicle of the present application;

[0017] Figure 2 is Figure 1 is an assembly schematic view of the fuselage connecting mechanism;

[0018] Figure 3 is Figure 1 is an assembly schematic view of the fuselage connecting mechanism in the pull buckle lock hook and the pull buckle lock;

[0019] Figure 4 is Figure 1 is an assembly schematic view of the fuselage connecting mechanism in the mounting member and the quick latch;

[0020] Figure 5 is a structural schematic view of an embodiment of the unmanned aerial vehicle of the present application. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0022] The terms "first", "second", "third", "etc." are used only for descriptive purposes and do not connote or imply a relative importance or an ordering between the indicated technical features. Thus, a feature defined with "first", "second", "third", etc. can include at least one of the features explicitly or implicitly. In the description of the present application, the meaning of "a plurality of" is at least two, such as two, three, etc., unless otherwise explicitly specified. All directional references, such as up, down, left, right, front, back, etc., used in the description of the present application are only used for convenience and do not imply or require that the device be constructed or operated in any specific orientation. Terms such as "include", "have", and "comprise" and their conjugates, as used in the description of the present application, are intended to encompass the presence of the stated feature, but do not preclude the presence or addition of one or more other features, unless otherwise explicitly stated or limited.

[0023] Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of the application. The appearances of the phrase "in an embodiment" in various places in the specification are not necessarily all referring to the same embodiment, nor are they necessarily mutually exclusive of one another. It is expressly understood that any of the embodiments described herein can be combined with any of the other embodiments unless explicitly stated otherwise.

[0024] The present application will be described in detail below with reference to the accompanying drawings and embodiments.

[0025] Please refer to Figure 1 and Figure 2 , wherein, Figure 1 is an exploded schematic view of an embodiment of the fuselage connecting mechanism of the unmanned aerial vehicle of the present application, Figure 2 is Figure 1 an assembly schematic view of the fuselage connecting mechanism in . In the present embodiment, the fuselage connecting mechanism 1 comprises: a middle wing docking assembly 10, a rotor arm docking assembly 20, and a central wing docking assembly 30.

[0026] Among them, the fuselage connecting mechanism 1 provided in the present application can be specifically used for detachable connection between different functional components in the unmanned aerial vehicle, such as the middle wing mechanism, the rotor arm, and the central wing mechanism. Of course, in other embodiments, the fuselage connecting mechanism 1 can also be specifically used for connection between different components in a mechanical toy, or a smart robot, or any other reasonable mechanical device, and the present embodiment does not limit this.

[0027] Specifically, the intermediate wing docking assembly 10 in the fuselage connecting mechanism 1 further comprises a first base 11 and a first plug 12, and the first plug 12 is connected on the first side of the first base 11, and a first plug hole (not marked in the figure) is further arranged on the second side of the first plug 12.

[0028] The central wing docking assembly 30 further comprises a second base 31, and a second plug hole 32 is arranged on the third side of the second base 31, so that the first plug 12 in the intermediate wing docking assembly 10 can be correspondingly plugged into the second plug hole 32.

[0029] The rotary-wing aircraft arm docking assembly 20 further comprises a third base 21 and a second plug 22, and the second plug 22 is connected on the fourth side of the third base 21. The second plug 22 can be correspondingly plugged into the first plug hole, and the first plug 12 is inserted into the second plug hole 32, so as to further detachably connect the rotary-wing aircraft arm docking assembly 20 with the intermediate wing docking assembly 10 and the central wing docking assembly 30.

[0030] The first plug hole of the first plug 12 correspondingly plugs in the second plug 22 of the rotary-wing aircraft arm docking assembly 20, so as to further detachably connect the connected intermediate wing docking assembly 10 and rotary-wing aircraft arm docking assembly 20 with the central wing docking assembly 30.

[0031] In other embodiments, when the rotor is not needed, the rotary-wing aircraft arm docking assembly 20 can be omitted, and only the intermediate wing docking assembly 10 and the central wing docking assembly 30 are retained.

[0032] The above scheme realizes the mutual cooperation and docking between the intermediate wing docking assembly 10, the rotary-wing aircraft arm docking assembly 20 and the central wing docking assembly 30 by sequentially plugging in the two pairs of plugs, which can avoid using tools to unlock and lock each assembly. The plugging-in mode is more rapid and convenient, and each connecting assembly is embedded in the fuselage, so that there is no external resistance source at the docking position between the connecting assemblies, thereby effectively improving the flight aerodynamic performance and endurance performance of the unmanned aerial vehicle, and realizing stable and reliable connection and cooperation, and the appearance is beautiful.

[0033] In an embodiment, the first side of the first base 11 in the intermediate wing docking assembly 10 can be perpendicular to the second side of the first plug 12, so that the opening direction of the first plug hole on the second side of the first plug 12 is perpendicular to the first side of the first base 11.

[0034] And the fourth side of the third base 21 in the rotorcraft arm docking assembly 20 corresponds to the second side of the first pin 12, and the second pin 22 is vertically connected to the fourth side of the third base 21, so as to be arranged to extend in a direction opposite to the opening direction of the first insertion hole in the first pin 12, and then the second pin 22 can be stably inserted into the first insertion hole, so that the rotorcraft arm docking assembly 20 is stably and detachably connected to the middle wing docking assembly 10.

[0035] The first insertion hole in the first pin 12 can be a through hole or a blind hole, that is, the depth thereof can be less than or equal to the length of the first pin 12 in the direction perpendicular to the second side thereof, which can be determined by the actual connection scene, and the present application does not limit this.

[0036] In another embodiment, the first side of the first base 11 can also be arranged at a specific obtuse angle or acute angle with the second side of the first pin 12, which can be determined by the shape contour of the corresponding docking assembly and the actual connection scene, and the present application does not limit this.

[0037] Please continue to refer to Figure 3 , Figure 3 is Figure 1 the assembly diagram of the buckle lock hook and the buckle lock in the fuselage connecting mechanism.

[0038] In an embodiment, the fifth side of the third base 21 in the rotorcraft arm docking assembly 20 is also provided with a buckle lock hook 23, and the sixth side of the second base 31 in the central wing docking assembly 30 is also provided with a buckle lock 33 corresponding to the buckle lock hook 23, so that the buckle lock 33 and the buckle lock hook 23 are buckled, and the central wing docking assembly 30 and the rotorcraft arm docking assembly 20 are more stably connected.

[0039] The fifth side of the third base 21 and the fourth side thereof are adjacent two sides, and the sixth side of the second base 31 and the third side thereof are adjacent two sides, and the sixth side can be perpendicular to the third side.

[0040] It can be understood that the buckle lock 33 of the mature product is used to realize the connection between the central wing docking assembly 30 and the rotorcraft arm docking assembly 20, which is more convenient and fast to operate and has lower implementation cost.

[0041] Please continue to refer to Figure 4 , Figure 4 is Figure 1 the assembly diagram of the mounting piece and the quick pin in the fuselage connecting mechanism.

[0042] In an embodiment, the sixth side of the second base 31 of the central wing docking assembly 30 is further provided with a mounting member 34, and one side of the mounting member 34 is further provided with a first mounting hole (not shown in the figure), and the fifth side of the third base 21 of the rotorcraft arm docking assembly 20 is further provided with a second mounting hole corresponding to the first mounting hole.

[0043] In an embodiment, the sixth side of the second base 31 of the central wing docking assembly 30 is further provided with a mounting member 34, and one side of the mounting member 34 is further provided with a first mounting hole (not shown in the figure), and the fifth side of the third base 21 of the rotorcraft arm docking assembly 20 is further provided with a second mounting hole corresponding to the first mounting hole.

[0044] It can be understood that the quick release pin 24 is further provided with an elastic mechanism (not shown in the figure) inside, so as to conveniently realize the docking or separation between the third base 21 of the rotorcraft arm docking assembly 20 and the mounting member 34 by means of the elastic mechanism.

[0045] Further, in an embodiment, the end of the quick release pin 24 away from the mounting member 34 is further provided with a ring-shaped pull ring 241, and the user can insert his fingers into the pull ring 241 to insert or separate the quick release pin 24 into or from the first mounting hole of the mounting member 34, so as to connect or separate the third base 21 of the rotorcraft arm docking assembly 20 and the mounting member 34.

[0046] In an embodiment, the number of the first pins 12 in the intermediate wing docking assembly 10 is specifically two, and the two first pins 12 are arranged at intervals on the first side of the third base 21. The number of the second pins 22 in the rotorcraft arm docking assembly 20 is also correspondingly two, and the two second pins 22 are also arranged at intervals on the fourth side of the third base 21, so as to respectively correspondingly insert each second pin 22 into the first insertion hole of the corresponding first pin 12, thereby more stably connecting the rotorcraft arm docking assembly 20 and the intermediate wing docking assembly 10.

[0047] In an embodiment, the edge position of the third side of the second base 31 of the central wing docking assembly 30 is provided with a ring-shaped groove (not shown in the figure), and the first side of the first base 11 of the intermediate wing docking assembly 10 is further provided with a protruding part (not shown in the figure) corresponding to the ring-shaped groove, so as to embed the protruding part in the ring-shaped groove, thereby more stably connecting the rotorcraft arm docking assembly 20 and the intermediate wing docking assembly 10.

[0048] Alternatively, the first pin 12 and the second pin 22 can specifically have any reasonable shape such as a square body shape, a trapezoidal body shape, or a cylindrical body shape, and the present application does not limit this.

[0049] It can be understood that the central wing docking assembly 30 is inserted into the middle wing docking assembly 10, and the rotorcraft arm docking assembly 20, the central wing docking assembly 30 and the middle wing docking assembly 10 are inserted into each other, and then the rotorcraft arm docking assembly 20 and the central wing docking assembly 30 are locked by the pull buckle 33, the quick insertion pin 24 and the like, so that the connected overall structure is more stable and reliable, the corresponding connecting mechanisms are embedded in the fuselage, the overall structure has no external resistance source, the flight aerodynamic performance of the unmanned aerial vehicle is improved, and the unmanned aerial vehicle is beautiful and simple in appearance.

[0050] The application also provides an unmanned aerial vehicle, please refer to Figure 5 , Figure 5 is an explosion schematic view of an embodiment of the unmanned aerial vehicle of the application. In the embodiment, the unmanned aerial vehicle 40 comprises a middle wing mechanism 41, a rotorcraft arm 42, a central wing mechanism 43 and a fuselage connecting mechanism 44.

[0051] Specifically, the fuselage connecting mechanism 44 further comprises a middle wing docking assembly 441, a rotorcraft arm docking assembly 442 and a central wing docking assembly 443.

[0052] The middle wing docking assembly 441 in the fuselage connecting mechanism 44 further comprises a first base (not shown in the figure) and a first insertion pin (not shown in the figure), and the first insertion pin is connected to the first side of the first base, and a first insertion hole is further provided on the second side of the first insertion pin.

[0053] The rotorcraft arm docking assembly 442 further comprises a third base (not shown in the figure) and a second insertion pin (not shown in the figure), and the second insertion pin is connected to the fourth side of the third base, and the second insertion pin can be inserted into the first insertion hole to detachably connect the rotorcraft arm docking assembly 442 and the middle wing docking assembly 441, so as to connect the rotorcraft arm 42 and the middle wing mechanism 41.

[0054] The central wing docking assembly 443 further comprises a second base (not shown in the figure), and a second insertion hole is further provided on the third side of the second base, so that the first insertion pin in the middle wing docking assembly 441 can be inserted into the second insertion hole.

[0055] The first insertion hole of the first insertion pin further inserts the second insertion pin in the rotorcraft arm docking assembly 442, so as to further detachably connect the connected middle wing docking assembly 441 and rotorcraft arm docking assembly 442 and the central wing docking assembly 443, and connect the middle wing mechanism 41 and the rotorcraft arm 42 to the central wing mechanism 43.

[0056] In an embodiment, the UAV 40 further comprises a fuselage mechanism 45, and the central wing mechanism 43 is correspondingly connected to the fuselage mechanism 45.

[0057] It can be understood that the UAV 40 can further comprise any other reasonable functional components such as landing gear, tail, propeller, etc., which will not be described here.

[0058] In an embodiment, the fifth side of the third base of the rotorcraft arm docking assembly 442 is further provided with a carabiner (not shown in the figure), and the sixth side of the second base of the central wing docking assembly 443 is further provided with a carabiner corresponding to the carabiner, so that the carabiner can be buckled with the carabiner, thereby realizing more stable connection between the central wing docking assembly 443 and the rotorcraft arm docking assembly 442.

[0059] Among them, the fifth side and the fourth side of the third base are two adjacent sides, and the sixth side and the third side of the second base are two adjacent sides, and specifically can be perpendicular to the third side.

[0060] It can be understood that the carabiner of the mature product is used to realize the connection between the central wing docking assembly 443 and the rotorcraft arm docking assembly 442, which is more convenient and fast to operate, and the implementation cost is also lower.

[0061] Among them, the fuselage connecting mechanism 44 can be the fuselage connecting mechanism 1 as described in any of the above, please refer to Figures 1-4 and related text content, which will not be described here.

[0062] The beneficial effects of the present application are: different from the prior art, the intermediate wing docking assembly in the fuselage connecting mechanism provided by the present application comprises a first base and a first bolt, the first bolt is connected to the first side of the first base, and a first insertion hole is provided on the second side of the first bolt, the second bolt of the rotorcraft arm docking assembly is connected to the fourth side of the third base, and the second bolt can be inserted into the first insertion hole to detachably connect the rotorcraft arm docking assembly to the intermediate wing docking assembly, and the third side of the second base of the central wing docking assembly is further provided with a second insertion hole, and the first bolt can be inserted into the second insertion hole to detachably connect the intermediate wing docking assembly and the rotorcraft arm docking assembly to the central wing docking assembly, so that the mutual cooperation and docking between the intermediate wing docking assembly, the rotorcraft arm docking assembly and the central wing docking assembly can be realized by the way of inserting the two pairs of bolts in turn, and the way of inserting is more quick and convenient, and there is no external resistance source at the docking place between the components, so as to effectively improve the endurance performance of the corresponding UAV, and the realized connection and cooperation are stable and reliable, and the appearance is beautiful.

[0063] The above merely describes the embodiments of the present application, and does not limit the patent scope of the present application. Any equivalent structure or equivalent process transformation, or direct or indirect application in other related technical fields, which is made by using the content of the present application specification and drawings, is also included in the patent protection scope of the present application.

Claims

1. A body connecting mechanism of a drone, characterized by, The fuselage connecting mechanism comprises: The intermediate wing docking assembly comprises a first base and a first plug, the first plug being connected to a first side of the first base and having a first plug hole on a second side of the first plug; The central wing docking assembly comprises a second base, the second base having a second plug hole on a third side of the second base, the first plug being plugged into the second plug hole to detachably connect the intermediate wing docking assembly to the central wing docking assembly; The rotorcraft arm docking assembly comprises a third base and a second plug, the second plug being connected to a fourth side of the third base, the second plug being plugged into the first plug hole and being inserted into the second plug hole by the first plug to detachably connect the rotorcraft arm docking assembly to the intermediate wing docking assembly and the central wing docking assembly; The sixth side of the second base further comprises a mounting, one side of the mounting further comprising a first mounting hole, the fifth side of the third base further comprising a second mounting hole corresponding to the first mounting hole, a quick plug being further inserted into the second mounting hole and a part of the quick plug being further plugged into the first mounting hole to connect the rotorcraft arm docking assembly to the central wing docking assembly, the quick plug further comprising an elastic mechanism inside.

2. The fuselage connecting mechanism according to claim 1, wherein The fifth side of the third base further comprises a pull buckle lock hook, the sixth side of the second base further comprising a pull buckle lock, the pull buckle lock being buckled with the pull buckle lock hook; wherein the fifth side of the third base is adjacent to the fourth side of the third base, and the sixth side of the second base is adjacent to the third side of the second base.

3. The fuselage connecting mechanism according to claim 1, wherein The end of the quick plug away from the mounting further comprises a ring-shaped pull ring.

4. The fuselage connecting mechanism according to claim 1, wherein The number of the first plugs is two, the two first plugs being arranged on the first side of the third base at intervals; The number of the second plugs is two, the two second plugs being arranged on the fourth side of the third base at intervals and being respectively plugged into the first plug hole of each first plug.

5. The fuselage connecting mechanism according to claim 1, wherein The edge of the third side of the second base comprises a ring-shaped groove, the first side of the first base further comprising a protruding part corresponding to the ring-shaped groove, the protruding part being embedded in the ring-shaped groove.

6. A drone, characterized in that, The unmanned aerial vehicle comprises an intermediate wing mechanism, a rotorcraft arm, a central wing mechanism and a fuselage connecting mechanism, the fuselage connecting mechanism comprising an intermediate wing docking assembly, a rotorcraft arm docking assembly and a central wing docking assembly; The intermediate wing docking assembly comprises a first base and a first plug, the first plug being connected to a first side of the first base and having a first plug hole on a second side of the first plug; The rotorcraft arm docking assembly comprises a third base and a second plug-in pin connected on the fourth side of the third base, which is plugged into the first plug-in hole to detachably connect the rotorcraft arm docking assembly to the middle wing docking assembly, so as to connect the rotorcraft arm to the middle wing mechanism. The central wing docking assembly comprises a second base, the third side of which is provided with a second plug-in hole, and the first plug-in pin is plugged into the second plug-in hole to detachably connect the middle wing docking assembly and the rotorcraft arm docking assembly to the central wing docking assembly, so as to connect the middle wing mechanism and the rotorcraft arm to the central wing mechanism. The sixth side of the second base is further provided with a mounting member, one side of the mounting member is further provided with a first mounting hole, the fifth side of the third base is further provided with a second mounting hole corresponding to the first mounting hole, a quick plug-in pin is further arranged in the second mounting hole, and part of the quick plug-in pin is further plugged into the first mounting hole to connect the rotorcraft arm docking assembly to the central wing docking assembly, and the quick plug-in pin is further provided with an elastic mechanism inside.

7. The unmanned aerial vehicle according to claim 6, wherein The unmanned aerial vehicle further comprises a fuselage mechanism, and the fuselage mechanism is connected to the central wing mechanism.

8. The unmanned aerial vehicle according to claim 6, wherein The fifth side of the third base is further provided with a pull buckle lock hook, and the sixth side of the second base is further provided with a pull buckle lock, which is buckled with the pull buckle lock hook; wherein the fifth side of the third base is adjacent to the fourth side thereof, and the sixth side of the second base is adjacent to the third side thereof.

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