CN221091275U - Wing and fuselage insert structure soon and contain its fixed wing unmanned aerial vehicle that takes off and land perpendicularly - Google Patents
Wing and fuselage insert structure soon and contain its fixed wing unmanned aerial vehicle that takes off and land perpendicularly Download PDFInfo
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- CN221091275U CN221091275U CN202322324216.0U CN202322324216U CN221091275U CN 221091275 U CN221091275 U CN 221091275U CN 202322324216 U CN202322324216 U CN 202322324216U CN 221091275 U CN221091275 U CN 221091275U
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- 230000009286 beneficial effect Effects 0.000 abstract description 5
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 230000006378 damage Effects 0.000 description 6
- 238000003780 insertion Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 229910000967 As alloy Inorganic materials 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
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Abstract
The utility model relates to a fast-inserting structure of a wing and a fuselage, and a vertical take-off and landing fixed-wing unmanned aerial vehicle comprising the fast-inserting structure, wherein the wing and the fuselage are detachably connected through connectors; the connector comprises a female end and a male end which is connected with the female end in an inserting way, wherein the wing plate of the female end is provided with at least two mounting holes, a screw connected with the machine body is inserted in the mounting hole of the female end, the diameter of the screw is smaller than the inner diameter of the mounting hole, the diameter of the head of the screw is larger than the inner diameter of the mounting hole, and a gap is reserved between the head of the screw and the outer side surface of the wing plate of the female end; the male end is fixed with the wing. The beneficial effects are as follows: the female end is not fixed on the machine body, but can have a certain movable space in the up-down left-right direction, the male end is fixed on the wing, when the wing and the machine body vibrate within a certain range, the connectors can synchronously act, and the transmission of a circuit is not influenced, so that the vibration resistance between the wing and the machine body is better, and in addition, when the wing and the machine body are assembled, the female end and the male end can be more easily connected and inserted.
Description
Technical Field
The utility model relates to the field of vertical take-off and landing fixed-wing unmanned aerial vehicle, in particular to a quick-insertion structure of a wing and a fuselage and a vertical take-off and landing fixed-wing unmanned aerial vehicle comprising the same.
Background
The vertical take-off and landing fixed wing unmanned aerial vehicle can take off and land vertically in situ without a runway, and has long endurance and large movable radius, and is mainly applied to dry traffic supervision, oil pipeline inspection, mapping, forest inspection and the like.
The existing vertical take-off and landing fixed wing unmanned aerial vehicle is in order to reduce the space occupied during transportation and promote the convenience, and the fixed wing unmanned aerial vehicle that will take-off and land perpendicularly is split into a plurality of parts generally, say: the wing and the fuselage can be disassembled, and in consideration of wiring problem when the wing and the fuselage are designed to be disassembled, an electric connector (or called a connector) is generally arranged between the wing and the fuselage, and two ends of the electric connector are generally completely fixed with the wing and the fuselage respectively, so that the vibration resistance between the wing and the fuselage is reduced in a completely fixed installation mode.
Disclosure of utility model
The utility model aims to solve the technical problem of providing a fast wing and fuselage plug-in structure so as to overcome the defects in the prior art.
The technical scheme for solving the technical problems is as follows: a wing and fuselage quick-connect structure comprising: the wing and the fuselage are detachably connected through connectors; the connector includes: the female end and the male end connected with the female end are inserted, at least two mounting holes are formed in the wing plate of the female end, screws connected with the machine body are inserted in the mounting holes of the female end, the screw diameters of the screws are smaller than the inner diameters of the mounting holes, the head diameters of the screws are larger than the inner diameters of the mounting holes, and a gap is formed between the head of each screw and the outer side face of the wing plate of the female end; the male end is fixed with the wing.
The beneficial effects of the utility model are as follows: the screw connected with the fuselage is inserted in the mounting hole of female end, and the screw diameter of screw is less than the internal diameter of mounting hole, the head diameter of screw is greater than the internal diameter of mounting hole, in addition, have the clearance between the pterygoid lamina lateral surface of head and female end of screw, make female end not be fixed on the fuselage, but can have certain activity space in upper and lower left and right directions, the male end is fixed on the wing, when there is certain scope vibration between wing and the fuselage, the connector can the synchronous action, and do not influence the transmission of circuit, thereby make the shock resistance between wing and the fuselage better, in addition, because female end can have certain activity space in upper and lower left and right directions at the fuselage, therefore, when wing and fuselage are assembled, female end and male end can more easily meet and insert.
On the basis of the technical scheme, the utility model can be improved as follows.
Further, a first mounting plate is fixed on the side face of the machine body, a first mounting hole is formed in the first mounting plate, and the size of the first mounting hole is larger than the outer contour size of the female end; the side of the wing is fixed with a second mounting plate, the second mounting plate is provided with a second assembly hole, and the size of the second assembly hole is larger than the outer contour size of the male end.
Further, a positioning rod is arranged on the second mounting plate, a positioning hole is formed in the position, opposite to the positioning rod, on the first mounting plate, and the positioning rod is inserted into the positioning hole.
The adoption of the method has the further beneficial effects that: through the cooperation of locating lever and locating hole, can be better let female end and public end meet and insert, in addition, because the locating lever is fixed on the second mounting panel, and the second mounting panel is fixed on the wing to and the locating hole is seted up on first mounting panel, and first mounting panel is fixed on the fuselage, consequently, can bear the atress to a certain extent, reduce the probability that female end and public end damage because of receiving the exogenic action when cooperating.
Further, a lock catch for fixing the wing and the fuselage is arranged between the wing and the fuselage.
The adoption of the method has the further beneficial effects that: the connection between the wing and the fuselage can be enhanced through the lock catch, so that the probability of damage caused by the action of external force when the female end is matched with the male end is further reduced.
Further, the screw adopts a flat head screw, and the section of the screw rod of the flat head screw in the mounting hole is a polished rod section.
The adoption of the method has the further beneficial effects that: when the female end moves on the screw, the polish rod section can not damage the female end.
Based on the technical scheme, the utility model also provides a vertical take-off and landing fixed wing unmanned aerial vehicle, which comprises the wing and fuselage quick-insertion structure.
Drawings
FIG. 1 is a block diagram of a fixed-wing vertical take-off and landing unmanned aerial vehicle with a wing and fuselage quick-insertion structure;
FIG. 2 is a partial block diagram of the fuselage;
fig. 3 is a partial block diagram at the wing.
In the drawings, the list of components represented by the various numbers is as follows:
1. The wing, 2, fuselage, 3, female end, 310, pterygoid lamina, 311, mounting hole, 4, male end, 5, screw, 6, first mounting panel, 610, first mounting hole, 620, locating hole, 7, second mounting panel, 710, second mounting hole, 720, locating lever, 8, hasp.
Detailed Description
The principles and features of the present utility model are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the utility model and are not to be construed as limiting the scope of the utility model.
Example 1
As shown in fig. 1, 2 and 3, a fast insertion structure for a wing and a fuselage includes: the wing 1 and the body 2 are detachably connected through connectors, and the connectors can be also called as electric connectors;
The connector includes: female end 3 and the public end 4 that inserts with female end 3, have at least two mounting holes 311 on the pterygoid lamina 310 of female end 3, preferably: all mounting holes 311 on the wing plate 310 are symmetrically distributed, such as at least one on the left and at least one on the right;
The mounting hole 311 of the female end 3 is inserted with a screw 5 connected with the body 2, and the diameter of the screw 5 is smaller than the inner diameter of the mounting hole 311, and the diameter of the head of the screw 5 is larger than the inner diameter of the mounting hole 311, for example: the inside diameter of the mounting hole 311 is 4mm, the shank diameter of the screw 5 is 3mm, and in addition, a gap is formed between the head of the screw 5 and the outer side surface of the wing plate 310 of the female end 3, for example: the gap is 0.5mm, so that the female end 3 is not fixed on the machine body 2, but can have a certain movable space in the up-down left-right direction;
The wiring end of the female end 3 is connected with the line in the machine body 2, the male end 4 is fixed with the wing 1, and can be fixed by adopting a screw, or can be fixed by adopting other modes, such as an anchor nail and the like, the wiring end of the male end 4 is connected with the line in the wing 1, and the line in the machine body 2 can be communicated with the line in the wing 1 through a connector;
Of course, in the actual design process, it is not excluded to mount the female end 3 on the wing 1, but the male end 4 on the fuselage 2.
Example 2
As shown in fig. 2 and 3, this embodiment is a further improvement of the embodiment 1, and specifically includes the following steps:
the side surface of the machine body 2 is fixed with a first mounting plate 6, the first mounting plate 6 and the machine body 2 can be fixed by adopting screws, the first mounting plate 6 is made of hard materials such as alloy, the first mounting plate 6 is provided with a first mounting hole 610, and the size of the first mounting hole 610 is slightly larger than the outer contour size of the female end 3, so that the female end 3 can have a certain movable space; the side of the wing 1 is fixed with a second mounting plate 7, the second mounting plate 7 and the wing 1 can be fixed by adopting screws, the second mounting plate 7 is made of hard materials such as alloy, the second mounting plate 7 is provided with a second assembly hole 710, and the size of the second assembly hole 710 is slightly larger than the outer contour size of the male end 4.
Example 3
As shown in fig. 2 and 3, this embodiment is a further improvement of the embodiment 2, and specifically includes the following steps:
The second mounting plate 7 is provided with the locating rod 720, the first mounting plate 6 is provided with the locating hole 620 opposite to the locating rod 720, the locating rod 720 is inserted into the locating hole 620, the female end 3 and the male end 4 can be better connected and inserted through the matching of the locating rod 720 and the locating hole 620, in addition, the locating rod 720 is fixed on the second mounting plate 7, the second mounting plate 7 is fixed on the wing 1, the locating hole 620 is formed in the first mounting plate 6, the first mounting plate 6 is fixed on the machine body 2, therefore, stress can be born to a certain extent, and the probability of damage caused by external force when the female end 3 and the male end 4 are matched is reduced.
Example 4
As shown in fig. 1, this embodiment is a further improvement of any of embodiments 1 to 3, and specifically includes the following:
the lock catch 8 for fixing the wing 1 and the fuselage 2 is arranged between the wing 1 and the fuselage 2, and the connection between the wing 1 and the fuselage 2 can be enhanced through the lock catch 8, so that the probability of damage caused by the action of external force when the female end 3 is matched with the male end 4 is further reduced.
Example 5
This example is a further improvement over any of examples 1 to 4, and is specifically as follows:
The screw 5 adopts the flat head screw, and the section that the screw rod of flat head screw is located in mounting hole 311 is the polished rod section, and when female end 3 moves on screw 5, the polished rod section can not harm female end 3.
Example 6
As shown in FIG. 1, a fixed wing unmanned aerial vehicle for vertical take-off and landing comprises a fast-insertion structure of a wing and a fuselage according to any of embodiments 1 to 5.
While embodiments of the present utility model have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the utility model, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the utility model.
Claims (6)
1. A wing and fuselage quick-connect structure comprising: the wing (1) and the fuselage (2) are characterized in that the wing (1) and the fuselage (2) are detachably connected through connectors; the connector includes: the novel screw comprises a female end (3) and a male end (4) connected with the female end (3), wherein the wing plate (310) of the female end (3) is provided with at least two mounting holes (311), a screw (5) connected with the machine body (2) is inserted in the mounting hole (311) of the female end (3), the diameter of the screw rod of the screw (5) is smaller than the inner diameter of the mounting hole (311), the diameter of the head of the screw (5) is larger than the inner diameter of the mounting hole (311), and a gap is reserved between the head of the screw (5) and the outer side face of the wing plate (310) of the female end (3); the male end (4) is fixed with the wing (1).
2. The wing and fuselage quick connect structure of claim 1, wherein: a first mounting plate (6) is fixed on the side surface of the machine body (2), a first assembly hole (610) is formed in the first mounting plate (6), and the size of the first assembly hole (610) is larger than the outer contour size of the female end (3); the side of wing (1) is fixed with second mounting panel (7), have second mounting panel (710) on second mounting panel (7), the size of second mounting panel (710) is bigger than the outline size of public end (4).
3. A wing and fuselage quick connect structure in accordance with claim 2, wherein: the second mounting plate (7) is provided with a positioning rod (720), the first mounting plate (6) is provided with a positioning hole (620) opposite to the positioning rod (720), and the positioning rod (720) is inserted into the positioning hole (620).
4. The wing and fuselage quick connect structure of claim 1, wherein: a lock catch (8) for fixing the wing (1) and the fuselage (2) is arranged between the wing (1) and the fuselage (2).
5. The wing and fuselage quick connect structure of claim 1, wherein: the screw (5) is a flat head screw, and the section of the screw rod of the flat head screw, which is positioned in the mounting hole (311), is a polished rod section.
6. The utility model provides a fixed wing unmanned aerial vehicle that takes off and land perpendicularly which characterized in that: comprising a wing and fuselage plug structure according to any one of claims 1 to 5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322324216.0U CN221091275U (en) | 2023-08-28 | 2023-08-28 | Wing and fuselage insert structure soon and contain its fixed wing unmanned aerial vehicle that takes off and land perpendicularly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322324216.0U CN221091275U (en) | 2023-08-28 | 2023-08-28 | Wing and fuselage insert structure soon and contain its fixed wing unmanned aerial vehicle that takes off and land perpendicularly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221091275U true CN221091275U (en) | 2024-06-07 |
Family
ID=91326003
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322324216.0U Active CN221091275U (en) | 2023-08-28 | 2023-08-28 | Wing and fuselage insert structure soon and contain its fixed wing unmanned aerial vehicle that takes off and land perpendicularly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221091275U (en) |
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2023
- 2023-08-28 CN CN202322324216.0U patent/CN221091275U/en active Active
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