CN210707854U - Novel wing connection structure - Google Patents
Novel wing connection structure Download PDFInfo
- Publication number
- CN210707854U CN210707854U CN201921361016.XU CN201921361016U CN210707854U CN 210707854 U CN210707854 U CN 210707854U CN 201921361016 U CN201921361016 U CN 201921361016U CN 210707854 U CN210707854 U CN 210707854U
- Authority
- CN
- China
- Prior art keywords
- wing
- hole
- auxiliary
- pin
- novel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Landscapes
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
The utility model discloses a novel wing connecting structure, wherein a second wing is detachably connected on a first wing, the connecting structure comprises an inserting column, two auxiliary blocks are relatively and fixedly arranged on the outer side of one end of the inserting column away from the second wing from front to back, two chutes are relatively arranged on the side wall of an inserting hole from top to bottom, and a rotation limiting mechanism is arranged between the first wing and the second wing; during installation, the insertion column is inserted into the insertion hole and drives the two auxiliary blocks to enter the auxiliary cavities along the corresponding sliding grooves, the second wing is rotated to enable the two auxiliary blocks to be not overlapped with the sliding grooves, and the locking pin is locked to complete installation of the first wing and the second wing; when the wing is disassembled, the locking pin is unlocked, the second wing is rotated to enable the two auxiliary blocks to coincide with the two sliding grooves, the inserting column is pulled out from the inserting hole, the first wing and the second wing can be disassembled, the bolt and the nut do not need to be screwed by other tools, and the wing is very convenient to install and disassemble.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field, concretely relates to novel wing connection structure.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned aerial vehicle operated by radio remote control equipment and a self-contained program control device. Unmanned aerial vehicles are in fact a general term for unmanned aerial vehicles, and can be defined from a technical perspective as follows: unmanned fixed wing aircraft, unmanned VTOL aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paravane, etc. Compared with manned aircraft, it has the advantages of small volume, low cost, convenient use, low requirement on the operational environment, strong battlefield viability and the like. Since the unmanned aircraft has important significance for future air battles, the research and development work of the unmanned aircraft is carried out in all major military countries in the world. .
The unmanned fixed wing aircraft is large in size and long in wingspan, so that the unmanned aircraft is inconvenient to package and transport, and great difficulty is brought to the transport process. In the prior art, for an unmanned fixed wing aircraft, a fixed wing, that is, a wing of the unmanned aerial vehicle, is generally divided into two sections. When the unmanned aerial vehicle is not used, the wings are disassembled and stored; when the unmanned aerial vehicle is needed, the wings are reassembled to form a complete wing. The existing assembly mode is generally that bolts are used for assembly and combination, and the bolts and nuts are screwed after the wings are assembled for fixation.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that a novel wing connection structure is provided, need not to utilize other instruments can make things convenient for quick to install and dismantle the wing to solve the problem among the prior art.
In order to solve the technical problem, the technical scheme of the utility model is that: a novel wing connecting structure comprises a first wing and a second wing, wherein the first wing is fixedly installed on a body of an unmanned aerial vehicle, the second wing is detachably connected to the first wing through a connecting mechanism, the second wing is located at the outer end of the first wing, and the outer end of the first wing is matched with the inner end of the second wing; the connecting mechanism comprises an inserting column fixedly arranged at the inner end of the second wing, the inserting column horizontally extends from left to right, and two auxiliary blocks are fixedly arranged on the outer side of one end, far away from the second wing, of the inserting column in a front-back opposite mode; an auxiliary cavity is arranged in the first wing, the auxiliary cavity is provided with an inserting hole which extends towards the outer end of the first wing and penetrates through the first wing, the inserting hole is matched with the inserting column, two sliding grooves matched with the auxiliary blocks are also oppositely arranged on the side wall of the inserting hole from top to bottom, the extending direction of the sliding grooves is the same as the extending direction of the inserting hole, and the length of the sliding grooves is equal to that of the inserting hole; and a rotation limiting mechanism is further arranged between the first wing and the second wing.
As a further improvement, a sealing plate is arranged in the auxiliary cavity in a left-right sliding mode, and a sealing spring is arranged between one side, far away from the plug hole, of the sealing plate and the auxiliary cavity.
As a preferred technical scheme, the rotation limiting mechanism comprises a first mounting cavity located in the first wing, the first mounting cavity is provided with a through hole which extends towards the outer end of the first wing and penetrates through the first wing, a locking pin is movably mounted in the through hole, a stop block is fixedly mounted at the inner end of the locking pin, and a first spring is arranged between the inner side of the stop block and the first mounting cavity; the part of the outer end of the locking pin extending out of the through hole is hemispherical, and the inner end of the second wing is provided with a locking groove matched with the locking pin; and a limiting pin locking mechanism is also arranged in the first wing.
As a preferred technical scheme, the limit pin locking mechanism comprises a second installation cavity located in the first wing, the second installation cavity is provided with a through hole which extends forwards and is communicated with the first installation cavity, a limit pin is movably installed in the through hole in a front-back mode, a baffle is fixedly installed at the rear end of the limit pin, and a second spring is arranged between the rear side of the baffle and the second installation cavity; the stop block is provided with a limit hole matched with the limit pin; the rear side of the baffle is also fixedly provided with a pull rod extending backwards, and the first wing is provided with an auxiliary hole for the pull rod to penetrate out.
As a preferred technical scheme, the limiting pin is conical.
As a further improvement, one end of the pull rod extending out of the first wing is fixedly provided with a pull block, and the pull block is provided with anti-skid grains.
Due to the adoption of the technical scheme, the novel wing connecting structure comprises a first wing and a second wing, wherein the second wing is detachably connected to the first wing through a connecting mechanism, the connecting mechanism comprises an inserting column fixedly installed at the inner end of the second wing, two auxiliary blocks are oppositely and fixedly installed on the outer side of one end, away from the second wing, of the inserting column, an auxiliary cavity is formed in the first wing, an inserting hole is formed in the auxiliary cavity, two sliding grooves matched with the auxiliary blocks are oppositely formed in the side wall of the inserting hole from top to bottom, and a rotation limiting mechanism is further arranged between the first wing and the second wing; when the utility model is installed, the inserting column is inserted into the inserting hole, the inserting column drives the two auxiliary blocks to enter the auxiliary cavities along the corresponding sliding grooves, the locking of the locking pin is released by pulling the pull rod, the second wing is rotated to enable the locking pin to be clamped into the locking groove, meanwhile, the inserting column drives the two auxiliary blocks to rotate to a state which is not overlapped with the sliding grooves, and the first wing and the second wing can be installed by loosening the pull rod to lock the locking pin; during the dismantlement, through the locking of pulling the fitting pin that the pull rod relieved pair to rotate the second wing and make the fitting pin break away from the locking groove, peg graft the post simultaneously and drive two auxiliary blocks and rotate to and coincide with two spout positions, extract the peg graft post from the spliced eye and drive two auxiliary blocks and break away from the auxiliary chamber from corresponding spout and can accomplish the dismantlement of first wing and second wing, need not to utilize other instruments to twist bolt and nut, the installation with dismantle very conveniently.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive exercise.
Fig. 1 is a schematic structural diagram of an embodiment of the present invention;
fig. 2 is a schematic structural view of a connection mechanism according to an embodiment of the present invention;
FIG. 3 is an enlarged view of a portion I of FIG. 2;
fig. 4 is a schematic structural diagram of an insertion hole according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of an insertion column according to an embodiment of the present invention.
In the figure: 1-a first airfoil; 2-a second airfoil; 3-inserting a column; 4-an auxiliary block; 5-an auxiliary cavity; 6-a plug hole; 7-a chute; 8-a closing plate; 9-a closing spring; 10-a first mounting cavity; 11-a through hole; 12-a locking pin; 13-a stopper; 14-a first spring; 15-a second mounting cavity; 16-a via hole; 17-a limit pin; 18-a baffle plate; 19-a second spring; 20-limiting holes; 21-a pull rod; 22-auxiliary wells; 23-pulling the block; 24-a locking groove; 25-organism.
Detailed Description
As shown in fig. 1 to 5, a novel wing connection structure includes a first wing 1 and a second wing 2, the first wing 1 is fixedly mounted on an unmanned aerial vehicle body, the second wing 2 is detachably connected to the first wing 1 through a connection mechanism, the second wing 2 is located at an outer end of the first wing 1, and an outer end of the first wing 1 is matched with an inner end of the second wing 2; the connecting mechanism comprises an inserting column 3 fixedly installed at the inner end of the second wing 2, the inserting column 3 horizontally extends from left to right, and two auxiliary blocks 4 are oppositely and fixedly installed on the outer side of one end, far away from the second wing 2, of the inserting column 3 from front to back; an auxiliary cavity 5 is arranged in the first wing 1, the auxiliary cavity 5 is provided with an inserting hole 6 which extends towards the outer end of the first wing 1 and penetrates through the first wing 1, the inserting hole 6 is matched with the inserting column 3, two sliding grooves 7 which are matched with the auxiliary blocks 4 are also oppositely arranged on the side wall of the inserting hole 6 from top to bottom, the extending direction of the sliding grooves 7 is the same as the extending direction of the inserting hole 6, and the length of the sliding grooves 7 is equal to that of the inserting hole 6; a rotation limiting mechanism is further arranged between the first wing 1 and the second wing 2.
The distance between the auxiliary block 4 and the inner end of the second wing 2 is equal to the length of the plug-in hole 6, when the aircraft wing is installed, the plug-in post 3 is inserted into the plug-in hole 6, so that the outer end of the first wing 1 is abutted against the inner end of the second wing 2, the plug-in post 3 drives the two auxiliary blocks 4 to enter the auxiliary cavity 5 along the corresponding sliding grooves 7, then the second wing 2 is rotated to drive the plug-in post 3 to rotate in the plug-in hole 6 until the outer end of the first wing 1 is matched with the inner end of the second wing 2, meanwhile, the second wing 2 drives the auxiliary blocks 4 to rotate through the plug-in post 3, so that the two auxiliary blocks 4 are rotated to be not matched with the sliding grooves 7, and at the moment, one side, close to the second wing 2, of the auxiliary block 4 is abutted against the side wall, close to the plug-in hole 6.
And a sealing plate 8 is arranged in the auxiliary cavity 5 in a left-right sliding manner, and a sealing spring 9 is arranged between one side of the sealing plate 8, which is far away from the plug hole 6, and the auxiliary cavity 5. When the inserting-connecting hole 6 is not inserted into the inserting-connecting column 3, the closing spring 9 pushes the closing plate 8 to move towards one side of the inserting-connecting hole 6 to close the auxiliary cavity 5, and dust is prevented from entering the auxiliary cavity 5.
The rotation limiting mechanism comprises a first installation cavity 10 positioned in the first wing 1, the first installation cavity 10 is provided with a through hole 11 which extends towards the outer end of the first wing 1 and penetrates through the first wing 1, a locking pin 12 is movably installed in the through hole 11, a stop block 13 is fixedly installed at the inner end of the locking pin 12, and a first spring 14 is arranged between the inner side of the stop block 13 and the first installation cavity 10; the part of the outer end of the locking pin 12 extending out of the through hole 11 is hemispherical, the inner end of the second wing 2 is provided with a locking groove 24 matched with the locking pin 12, specifically, the distance between the locking groove 24 and the plug-in post 3 is equal to the distance between the through hole 11 and the plug-in hole 6, and the locking groove 24 and the through hole 11 are respectively positioned behind the plug-in post 3 and the plug-in hole 6; and a limiting pin locking mechanism is also arranged in the first wing 1.
When the aircraft wing locking device is installed, the outer end of the first aircraft wing 1 is abutted against the inner end of the second aircraft wing 2 by inserting the inserting column 3 into the inserting hole 6, the inserting column 3 drives the two auxiliary blocks 4 to enter the auxiliary cavity 5 along the corresponding sliding grooves 7, then the second aircraft wing 2 is rotated to enable the outer end of the first aircraft wing 1 to be matched with the inner end of the second aircraft wing 2, in the process of rotating the second aircraft wing 2, the second aircraft wing 2 can enable the locking pin 12 to be put into the through hole 11 by pushing the hemispherical surface of the locking pin 12 until the second aircraft wing 2 rotates to a state that the locking groove 24 is overlapped with the through hole 11, the first spring 14 pushes the check block 13 to drive the locking pin 12 to be clamped into the locking groove 24, and at the moment, the outer end of the first aircraft wing 1 is matched with.
The limiting pin locking mechanism comprises a second mounting cavity 15 positioned in the first wing 1, the second mounting cavity 15 is provided with a through hole 16 which extends forwards and is communicated with the first mounting cavity 10, a limiting pin 17 is movably mounted in the through hole 16 in a front-back mode, the rear end of the limiting pin 17 is fixedly provided with a baffle 18, and a second spring 19 is arranged between the rear side of the baffle 18 and the second mounting cavity 15; the stop block 13 is provided with a limit hole 20 matched with the limit pin 17, and specifically, when the limit pin 17 is inserted into the limit hole 20, the stop block 13 is attached to one side of the first installation cavity 10 close to the through hole 11; the rear side of the baffle 18 is also fixedly provided with a pull rod 21 extending backwards, and the first wing 1 is provided with an auxiliary hole 22 for the pull rod 21 to penetrate out.
When the first spring 14 pushes the stop block 13 to drive the locking pin 12 to be clamped into the locking groove 24, the stop block 13 and one side of the first installation cavity 10 close to the through hole 11 are in a state of being attached to each other, at the moment, the second spring 19 pushes the stop block 18 to drive the limiting pin 17 to be inserted into the limiting hole 20 to limit the stop block 13 to move left and right in the second installation cavity 15, at the moment, the locking pin 12 cannot be retracted into the through hole 11, namely, the second wing 2 and the plug-in post 3 cannot rotate around the plug-in hole 6; or the limit pin 17 is driven to be separated from the limit hole 20 through the baffle plate 18 by pulling the pull rod 21 so as to release the limit of the stop block 13.
The limiting pin 17 is conical, specifically, the diameter of one end of the limiting pin 17 close to the baffle 18 is larger than the diameter of one end of the limiting pin 17 far away from the baffle 18, so that the limiting pin 17 can be conveniently inserted into the limiting hole 20.
The pull rod 21 is fixedly provided with a pull block 23 at one end extending out of the first wing 1, and the pull block 23 is provided with anti-skid grains, so that the pull rod 21 can be pulled more conveniently.
The using method comprises the following steps:
during installation, the inserting column 3 is inserted into the inserting hole 6, so that the outer end of the first wing 1 is abutted against the inner end of the second wing 2, the inserting column 3 drives the two auxiliary blocks 4 to enter the auxiliary cavity 5 along the corresponding sliding grooves 7, then the pull rod 21 is pulled to drive the limiting pin 17 to be separated from the limiting hole 20 through the baffle 18, then the second wing 2 is rotated to drive the inserting column 3 to rotate in the inserting hole 6 until the outer end of the first wing 1 is matched with the inner end of the second wing 2, the locking pin 12 is clamped into the locking groove 24, finally the pull rod 21 is loosened, and the second spring 19 pushes the baffle 18 to drive the limiting pin 17 to be inserted into the limiting hole 20.
During disassembly, the pull rod 21 is pulled to drive the limiting pin 17 to be separated from the limiting hole 20 through the baffle plate 18, then the second wing 2 is rotated to drive the plug-in column 3 to rotate in the plug-in hole 6, the plug-in column 6 drives the two auxiliary blocks 4 to rotate to coincide with the two sliding grooves 7, the plug-in column 3 is pulled out of the plug-in hole 6, and the two auxiliary blocks 4 are driven to be separated from the corresponding sliding grooves 7 to form the auxiliary cavities 5.
The basic principles, main features and advantages of the present invention have been shown and described above. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (6)
1. The utility model provides a novel wing connection structure which characterized in that: the unmanned aerial vehicle comprises a first wing and a second wing, wherein the first wing is fixedly installed on a body of the unmanned aerial vehicle, the second wing is detachably connected to the first wing through a connecting mechanism, the second wing is located at the outer end of the first wing, and the outer end of the first wing is matched with the inner end of the second wing; the connecting mechanism comprises an inserting column fixedly arranged at the inner end of the second wing, the inserting column horizontally extends from left to right, and two auxiliary blocks are fixedly arranged on the outer side of one end, far away from the second wing, of the inserting column in a front-back opposite mode; an auxiliary cavity is arranged in the first wing, the auxiliary cavity is provided with an inserting hole which extends towards the outer end of the first wing and penetrates through the first wing, the inserting hole is matched with the inserting column, two sliding grooves matched with the auxiliary blocks are also oppositely arranged on the side wall of the inserting hole from top to bottom, the extending direction of the sliding grooves is the same as the extending direction of the inserting hole, and the length of the sliding grooves is equal to that of the inserting hole; and a rotation limiting mechanism is further arranged between the first wing and the second wing.
2. The novel wing connection structure of claim 1, wherein: and a sealing plate is arranged in the auxiliary cavity in a left-right sliding manner, and a sealing spring is arranged between one side of the sealing plate, which is far away from the plug hole, and the auxiliary cavity.
3. The novel wing connection structure of claim 1, wherein: the rotation limiting mechanism comprises a first mounting cavity positioned in the first wing, the first mounting cavity is provided with a through hole which extends towards the outer end of the first wing and penetrates through the first wing, a locking pin is movably mounted in the through hole, a stop block is fixedly mounted at the inner end of the locking pin, and a first spring is arranged between the inner side of the stop block and the first mounting cavity; the part of the outer end of the locking pin extending out of the through hole is hemispherical, and the inner end of the second wing is provided with a locking groove matched with the locking pin; and a limiting pin locking mechanism is also arranged in the first wing.
4. A novel wing attachment structure according to claim 3, wherein: the limiting pin locking mechanism comprises a second mounting cavity positioned in the first wing, the second mounting cavity is provided with a through hole which extends forwards and is communicated with the first mounting cavity, a limiting pin is movably mounted in the through hole in a front-back mode, a baffle is fixedly mounted at the rear end of the limiting pin, and a second spring is arranged between the rear side of the baffle and the second mounting cavity; the stop block is provided with a limit hole matched with the limit pin; the rear side of the baffle is also fixedly provided with a pull rod extending backwards, and the first wing is provided with an auxiliary hole for the pull rod to penetrate out.
5. The novel wing connection structure of claim 4, wherein: the limiting pin is conical.
6. The novel wing connection structure of claim 4, wherein: one end of the pull rod extending out of the first wing is fixedly provided with a pull block, and anti-skid grains are arranged on the pull block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921361016.XU CN210707854U (en) | 2019-08-21 | 2019-08-21 | Novel wing connection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921361016.XU CN210707854U (en) | 2019-08-21 | 2019-08-21 | Novel wing connection structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210707854U true CN210707854U (en) | 2020-06-09 |
Family
ID=70960662
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921361016.XU Expired - Fee Related CN210707854U (en) | 2019-08-21 | 2019-08-21 | Novel wing connection structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210707854U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111792033A (en) * | 2020-06-17 | 2020-10-20 | 南宁慧视科技有限责任公司 | Waterborne fixed wing unmanned vehicles convenient to equipment |
| CN112278235A (en) * | 2020-11-05 | 2021-01-29 | 湖南浩天翼航空技术有限公司 | Wing quick locking mechanism of fixed-wing unmanned aerial vehicle and using method thereof |
| CN113247235A (en) * | 2021-06-10 | 2021-08-13 | 佛山智壹科技有限公司 | Unmanned plane |
-
2019
- 2019-08-21 CN CN201921361016.XU patent/CN210707854U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111792033A (en) * | 2020-06-17 | 2020-10-20 | 南宁慧视科技有限责任公司 | Waterborne fixed wing unmanned vehicles convenient to equipment |
| CN112278235A (en) * | 2020-11-05 | 2021-01-29 | 湖南浩天翼航空技术有限公司 | Wing quick locking mechanism of fixed-wing unmanned aerial vehicle and using method thereof |
| CN112278235B (en) * | 2020-11-05 | 2022-03-11 | 湖南浩天翼航空技术有限公司 | Wing quick locking mechanism of fixed-wing unmanned aerial vehicle and using method thereof |
| CN113247235A (en) * | 2021-06-10 | 2021-08-13 | 佛山智壹科技有限公司 | Unmanned plane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN210707854U (en) | Novel wing connection structure | |
| CN206939031U (en) | A kind of electronic unmanned plane of fixed-wing | |
| CN105644799A (en) | Separated type parachute ejection capsule for an unmanned aerial vehicle | |
| CN108438200A (en) | A kind of fixed-wing unmanned plane of fast demountable wing | |
| CN204415709U (en) | A kind of can the aircraft frame of automatic deploying and retracting horn | |
| CN108791800B (en) | Connecting fastener for unmanned aerial vehicle | |
| CN205602148U (en) | A disconnect -type parachute ejection capsule for unmanned aerial vehicle | |
| CN205273836U (en) | Be applied to unmanned aerial vehicle's coupling mechanism | |
| CN208422164U (en) | It is a kind of to provide the device of pitching and yaw forces sense for flight simulator emulation side lever | |
| CN107010244B (en) | A kind of split type unmanned plane | |
| CN111017213B (en) | Unmanned aerial vehicle recovery system guide umbrella penetrates umbrella mechanism | |
| CN110697018B (en) | Unmanned aerial vehicle wing and fuselage connecting device | |
| CN210653614U (en) | Fixed wing aircraft with quickly detachable wings | |
| CN208181404U (en) | Landing gear structure and unmanned plane | |
| CN116039981B (en) | Adaptive multi-module assembled unmanned aerial vehicle | |
| CN109795677A (en) | A kind of unmanned plane fast assembling-disassembling landing gear structure | |
| CN106542111B (en) | The fixed device of unmanned plane applied to unmanned plane transmitting | |
| CN205345329U (en) | Unmanned aerial vehicle equipment | |
| CN108639308A (en) | A kind of wing mechanism for assembling-disassembling for Fixed Wing AirVehicle | |
| CN208377044U (en) | A kind of fixed-wing unmanned plane of fast demountable wing | |
| CN205400308U (en) | Tool to lock that anti -riot power was opened | |
| CN107651202A (en) | A kind of hooking device and its unmanned plane | |
| CN207759018U (en) | A kind of foldable unmanned plane wing | |
| CN205891219U (en) | Foot rest mechanism and aircraft of aircraft | |
| CN112278240B (en) | Small-sized fixed wing unmanned aerial vehicle empennage quick dismounting mechanism and using method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200609 Termination date: 20210821 |