CN212556826U - Unmanned aerial vehicle load module quick detach connection structure - Google Patents
Unmanned aerial vehicle load module quick detach connection structure Download PDFInfo
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- CN212556826U CN212556826U CN202020748815.9U CN202020748815U CN212556826U CN 212556826 U CN212556826 U CN 212556826U CN 202020748815 U CN202020748815 U CN 202020748815U CN 212556826 U CN212556826 U CN 212556826U
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Abstract
The utility model discloses an unmanned aerial vehicle load module quick detach connection structure relates to aircraft technical field. The problem that the load module is time-consuming and labor-consuming to assemble and disassemble can be solved. Unmanned aerial vehicle load module quick detach connection structure includes fuselage main part, load module and coupling assembling. The load module is fixed with the machine body through a connecting component. Coupling assembling has the function of quick dismantlement, installation, can install the load module on the fuselage main part when needs like this, accomplishes unmanned aerial vehicle preparation work of taking off more fast.
Description
Technical Field
The utility model relates to an aircraft technical field, in particular to unmanned aerial vehicle load module quick detach connection structure.
Background
Along with the scientific and technological development, the unmanned aerial vehicle technology develops and popularizes rapidly, no matter military or civil unmanned aerial vehicle all has very big progress, is used widely in all trades, like military investigation, agricultural pesticide sprays, takes photo by plane, remote control toy etc.. But in present civil unmanned aerial vehicle's the use, still have a lot of inconveniences, at present, the connection form such as screw-fastening is adopted mostly to unmanned aerial vehicle load module's connection in the market, before unmanned aerial vehicle takes off, goes to lock fixedly by the operator screw one by one, wastes time and energy like this, makes unmanned aerial vehicle can not realize fast assembly and takes off.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve one of the technical problem that exists among the prior art at least, provide an unmanned aerial vehicle load module quick detach connection structure, can fast assembly unmanned aerial vehicle's load module to make unmanned aerial vehicle can take off rapidly and dismantle.
According to a first aspect of the utility model, a fast-dismantling connecting structure of an unmanned aerial vehicle load module is provided, which comprises a main body; and the load module is fastened on the main body of the fuselage through a connecting assembly.
Above unmanned aerial vehicle load module quick detach connection structure has following beneficial effect at least: this unmanned aerial vehicle load module quick detach connection structure includes fuselage main part, load module and coupling assembling. The load module is fixed with the machine body main body through the connecting assembly, and the connecting assembly has the functions of quick disassembly and installation. Can install the load module on the fuselage main part when needing like this, accomplish unmanned aerial vehicle preparation work of taking off more fast.
According to the utility model discloses an unmanned aerial vehicle load module quick detach connection structure of first aspect, coupling assembling includes the lock seat, fixes on one of fuselage main part or the load module; the lock cover is arranged on the lock seat in a freely rotatable manner through a first connecting shaft; the lock tongue is arranged at the lower end of the lock cover in a freely rotatable manner through a second connecting shaft; the spring is arranged on the second connecting shaft; and the lock hook is fixed on one of the machine body main body or the load module and is opposite to the lock seat, and the connection and the disassembly only need to be simply fastened and unfastened, so that the efficiency of loading and unloading the load module is greatly improved.
According to the utility model discloses an unmanned aerial vehicle load module quick detach connection structure of first aspect, be equipped with the concave surface on the latch hook, spring bolt one end is protruding end; the arc-shaped protruding end can be accommodated in the concave surface.
According to the utility model discloses the first aspect unmanned aerial vehicle load module quick detach connection structure, the concave surface is the arc surface, the protrusion end is convex protrusion end.
According to the utility model discloses first aspect unmanned aerial vehicle load module quick detach connection structure, latch hook one end is equipped with hook-like protruding piece, the concave surface is seted up on hook-like protruding piece, lock seat one side is provided with first recess, hook-like protruding piece holding can in the first recess. The first groove is matched with the hook-shaped protruding block, so that the positioning problem of the load module when the load module is butted with the machine body main body is well solved, the positioning is accurate, and dislocation is avoided.
According to the utility model discloses the first aspect unmanned aerial vehicle load module quick detach connection structure, fuselage main part both sides all are equipped with first half groove, load module both sides all are equipped with half groove of second. Work as load module connects when in the fuselage main part, first half groove with half groove butt joint of second forms and is used for placing coupling assembling's complete cell body for coupling assembling does not stick out in the unmanned aerial vehicle profile, reduces the windage, promotes unmanned aerial vehicle flight stability and duration.
Drawings
The present invention will be further described with reference to the accompanying drawings and examples;
FIG. 1 is a schematic structural diagram of a preferred embodiment of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
fig. 3 is an exploded view of the preferred embodiment of the present invention;
fig. 4 is a schematic structural view of a connecting assembly according to a preferred embodiment of the present invention;
fig. 5 is an exploded view of the connection assembly of the preferred embodiment of the present invention.
Detailed Description
This section will describe in detail the embodiments of the present invention, preferred embodiments of the present invention are shown in the attached drawings, which are used to supplement the description of the text part of the specification with figures, so that one can intuitively and vividly understand each technical feature and the whole technical solution of the present invention, but they cannot be understood as the limitation of the protection scope of the present invention.
In the description of the present invention, it should be understood that the orientation or positional relationship indicated with respect to the orientation description, such as up, down, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
In the description of the present invention, a plurality of means are one or more, a plurality of means are two or more, and the terms greater than, less than, exceeding, etc. are understood as not including the number, and the terms greater than, less than, within, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.
In the description of the present invention, unless there is an explicit limitation, the words such as setting, installation, connection, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in combination with the specific contents of the technical solution.
Referring to fig. 1 to 3, the utility model discloses an embodiment unmanned aerial vehicle load module quick detach connection structure includes fuselage main part 10, load module 20 and coupling assembling 30. The load module 20 is fastened to the fuselage body 10 by means of a connection assembly 30.
Fuselage main part 10 both sides all are equipped with first half groove 11, and load module 20 both sides all are equipped with half groove 21 of second, and when load module 20 was connected on fuselage main part 10, first half groove 11 and the butt joint of half groove 21 of second formed the complete cell body that is used for placing coupling assembling 30 for coupling assembling 30 does not stand out in the unmanned aerial vehicle profile, reduces the windage, promotes unmanned aerial vehicle flight stability and duration.
Referring to fig. 4, the connecting assembly 30 includes a lock holder 31, a lock cover 32, a first connecting shaft 33, a locking tongue 34, a second connecting shaft 35, a spring 36, and a locking hook 37. The lock housing 31 is fixed to one of the body 10 or the load module 20. The lock cover 32 is rotatably provided on the lock holder 31 via a first connecting shaft 33. The latch tongue 34 is rotatably provided at the lower end of the latch cover 32 via a second connecting shaft 35. The spring 36 is provided on the second connecting shaft 35. The latch hook 37 is fixed to one of the body 10 or the load module 20, and is opposite to the latch holder 31. Of course, it should be noted that, when the lock holder 31 is fixed to the load module 20, the lock hook 37 engaged with the lock holder 31 is fixed to the body 10. When the lock holder 31 is fixed to the body 10, the latch hook 37 engaged with the lock holder 31 is fixed to the load module 20.
Referring to fig. 5, the latch hook 37 has a concave surface 371a, and one end of the latch tongue 34 is a protruding end 341, and the protruding end 341 can be received in the concave surface 371 a. Preferably, the concave surface 371a is a circular arc surface, and the protruding end 341 is a circular arc protruding end. Of course, it should be noted that the arc surface is only one embodiment of the concave surface 371a, and other embodiments may be other embodiments as long as the arc surface can cooperate with the protruding end 341 to form a locking structure, such as an inclined surface or a curved surface. The circular arc shape is only one embodiment of the protruding end 341, and other embodiments may be other embodiments as long as the circular arc shape can cooperate with the concave surface 371a to form a locking structure, such as a cone shape or a wedge shape.
The latch hook 37 has a hook-shaped protrusion 371 at one end, a concave surface 371a opened on the hook-shaped protrusion 371, and a first recess 311 formed at one side of the latch holder 31, wherein the hook-shaped protrusion 371 is received in the first recess 311. The positioning problem when the load module 20 is butted with the machine body 10 is well solved through the matching of the first groove 311 and the hook-shaped protrusion block 371, so that the positioning is accurate and no dislocation occurs.
When the load module 20 is mounted to the body 10, the load module 20 is inserted into the body 10 and then locked using the connection assembly 30. During disassembly, the connecting assembly 30 is manually opened, and the load module 20 is pulled out, so that disassembly can be completed.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made without departing from the gist of the present invention within the knowledge range of those skilled in the art.
Claims (6)
1. Unmanned aerial vehicle load module quick detach connection structure, its characterized in that includes:
a body main body (10); and
a load module (20), the load module (20) being secured to the fuselage body (10) by a connection assembly (30).
2. The rapid disassembly and assembly structure of unmanned aerial vehicle load module of claim 1, wherein: the connecting assembly (30) comprises
A lock housing (31) fixed to one of the body main body (10) or the load module (20);
a lock cover (32) rotatably provided on the lock base (31) via a first connecting shaft (33);
a lock tongue (34) which is arranged at the lower end of the lock cover (32) in a freely rotating way through a second connecting shaft (35);
a spring (36) provided on the second connecting shaft (35); and
a latch hook (37) fixed to one of the body main body (10) or the load module (20) and opposed to the latch seat (31).
3. The rapid disassembly and assembly structure of unmanned aerial vehicle load module of claim 2, wherein: a concave surface (371a) is arranged on the lock hook (37), one end of the lock bolt (34) is a protruding end (341), and the protruding end (341) can be accommodated in the concave surface (371 a).
4. The rapid disassembly connection structure of unmanned aerial vehicle load module of claim 3, characterized in that: the concave surface (371a) is an arc surface, and the protruding end (341) is an arc protruding end.
5. The rapid disassembly connection structure of unmanned aerial vehicle load module of claim 3, characterized in that: one end of the lock hook (37) is provided with a hook-shaped protruding block (371), the concave surface (371a) is arranged on the hook-shaped protruding block (371), one side of the lock seat (31) is provided with a first groove (311), and the hook-shaped protruding block (371) can be accommodated in the first groove (311).
6. The rapid disassembly and assembly structure of unmanned aerial vehicle load module of claim 1, wherein: fuselage main part (10) both sides all are equipped with first half groove (11), load module (20) both sides all are equipped with second half groove (21), work as load module (20) are connected when fuselage main part (10) is gone up, first half groove (11) with second half groove (21) butt joint forms and is used for placing the complete cell body of coupling assembling (30).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020748815.9U CN212556826U (en) | 2020-05-08 | 2020-05-08 | Unmanned aerial vehicle load module quick detach connection structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202020748815.9U CN212556826U (en) | 2020-05-08 | 2020-05-08 | Unmanned aerial vehicle load module quick detach connection structure |
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| CN212556826U true CN212556826U (en) | 2021-02-19 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114379803A (en) * | 2021-12-28 | 2022-04-22 | 中电科芜湖通用航空产业技术研究院有限公司 | Unmanned aerial vehicle load quick detach mechanism |
| CN115352645A (en) * | 2022-08-31 | 2022-11-18 | 西北工业大学 | Split type aircraft docking mechanism |
-
2020
- 2020-05-08 CN CN202020748815.9U patent/CN212556826U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114379803A (en) * | 2021-12-28 | 2022-04-22 | 中电科芜湖通用航空产业技术研究院有限公司 | Unmanned aerial vehicle load quick detach mechanism |
| CN115352645A (en) * | 2022-08-31 | 2022-11-18 | 西北工业大学 | Split type aircraft docking mechanism |
| CN115352645B (en) * | 2022-08-31 | 2023-03-28 | 西北工业大学 | Split type aircraft docking mechanism |
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