CN219524289U - Unmanned aerial vehicle with barrel-type folding wings - Google Patents
Unmanned aerial vehicle with barrel-type folding wings Download PDFInfo
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- CN219524289U CN219524289U CN202320667699.1U CN202320667699U CN219524289U CN 219524289 U CN219524289 U CN 219524289U CN 202320667699 U CN202320667699 U CN 202320667699U CN 219524289 U CN219524289 U CN 219524289U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The utility model discloses a barrel type folding wing unmanned aerial vehicle, which comprises an unmanned aerial vehicle, a transmitting barrel and a throwing mechanism, wherein the unmanned aerial vehicle is arranged on the transmitting barrel; the transmitting cylinder comprises an upper shell and a lower shell, and the upper shell and the lower shell are in butt joint to form a cylindrical structure; the lower end face of the upper shell is provided with at least one first plug-in connection part which is a groove or a bulge, and the upper end face of the lower shell is provided with a second plug-in connection part which is matched with the first plug-in connection part; the roof in the epitheca is provided with throw the mechanism, unmanned aerial vehicle passes through throw the mechanism is fixed in the transmission section of thick bamboo. The utility model can greatly transfer the impact force between the upper shell and the lower shell to the first plug-in part and the second plug-in part which are matched in a plug-in way, thereby solving the problem that the shell of the transmitting cylinder can be separated in advance due to the fact that the cylindrical folding wing unmanned aerial vehicle is always fixed in the transmitting cylinder before being thrown and the axial direction of the transmitting cylinder is greatly impacted in the transmitting stage.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a cylindrical folding wing unmanned aerial vehicle.
Background
The folding wing unmanned aerial vehicle can fold each part through the folding mechanism, so that the space size of the folding wing unmanned aerial vehicle can be effectively reduced, the emission or the throwing of various weapon platforms can be realized, single or multiple tasks such as reconnaissance and damage evaluation, communication relay, target indication, accurate striking and the like can be executed, and the folding wing unmanned aerial vehicle has the characteristics of low cost, high efficiency-cost ratio, small size, strong stealth capability and the like.
The barrel type folding wing unmanned aerial vehicle is usually fixed in the transmitting barrel after folding, and the transmitting barrel plays the role of protecting the unmanned aerial vehicle. The unmanned aerial vehicle is fixed in the transmitting cylinder all the time before throwing, and a great impact force is generated on the axial direction of the transmitting cylinder in the transmitting stage, so that the danger of the early separation of the transmitting cylinder shell exists.
Disclosure of Invention
The embodiment of the utility model provides the barrel type folding wing unmanned aerial vehicle, which solves the problem that in the prior art, the barrel type folding wing unmanned aerial vehicle is always fixed in a transmitting barrel before being thrown, and a great impact force is generated on the axial direction of the transmitting barrel in the transmitting stage, so that the shell of the transmitting barrel can be separated in advance.
In order to achieve the above purpose, the embodiment of the utility model provides a cylindrical folding wing unmanned aerial vehicle, which comprises an unmanned aerial vehicle, a transmitting cylinder and a throwing mechanism;
the transmitting cylinder comprises an upper shell and a lower shell, and the upper shell and the lower shell are in butt joint to form a cylindrical structure; the lower end face of the upper shell is provided with at least one first plug-in connection part which is a groove or a bulge, and the upper end face of the lower shell is provided with a second plug-in connection part which is matched with the first plug-in connection part;
the roof in the epitheca is provided with throw the mechanism, unmanned aerial vehicle passes through throw the mechanism is fixed in the transmission section of thick bamboo.
In one possible implementation, the device further comprises a pre-tightening stud, wherein the pre-tightening stud comprises a mounting cylinder, a limit guide post, a pre-tightening nail, a compression spring and a piston top post;
the installation section of thick bamboo install in on the epitheca, install the lower extreme of installation section of thick bamboo limit guide pillar, pretension nail compression spring with the piston jack-up post from last to set gradually down in the installation section of thick bamboo, pretension nail screw thread install in the installation section of thick bamboo, the lower extreme of piston jack-up post passes behind the hole in limit guide pillar center butt in unmanned aerial vehicle's fuselage.
In one possible implementation manner, the upper end of the compression spring is sleeved on the convex block at the lower end of the pre-tightening nail, and the lower end of the compression spring extends into the blind hole at the upper end of the piston top column;
the limiting guide post is arranged in the threaded hole at the lower end of the mounting cylinder in a threaded mode, an annular table is arranged at the upper end of the piston top column in the circumferential direction, and the annular table is matched with the upper end of the limiting guide post.
In one possible implementation manner, the lower end of the piston jack-prop stretches into a jack-up hole on the unmanned aerial vehicle body, and the end of the piston jack-prop abuts against the bottom wall of the jack-up hole.
In one possible implementation, the method further comprises overhauling the aviation plug and the umbrella bag; the overhaul aerial plug is arranged between the upper shell and the unmanned aerial vehicle body, the lower end of the overhaul aerial plug is connected with a plug on the unmanned aerial vehicle body, and the upper shell is provided with an aerial jack matched with the overhaul aerial plug upper end;
the umbrella package is arranged at the rear end in the transmitting cylinder.
In one possible implementation, the service navigation plug includes a mount, an external navigation plug, an internal navigation plug, and a pass-through cable;
the installation seat is provided with an installation cavity, the outer aviation plug is installed at the upper end of the installation cavity, the inner aviation plug is installed at the lower end of the installation cavity, the outer aviation plug and the inner aviation plug are connected through the conducting cable, and the inner aviation plug is connected to a plug on the unmanned aerial vehicle.
In one possible implementation manner, the mounting seat comprises a mounting shell and a cylinder body, the mounting shell is a shell with a hollow inside, the top surface of the mounting shell is an arc surface, the top surface of the mounting shell is connected to the top wall in the upper shell, the inside of the cylinder body is the mounting cavity, and the cylinder body is arranged on one side of the mounting shell.
In one possible implementation manner, the front end of the transmitting cylinder is in a circular arc shape, and the tail of the transmitting cylinder is provided with stabilizing wings.
In one possible implementation manner, the device further comprises a separation explosion bolt, wherein one end of the separation explosion bolt is installed at the lower end of the upper shell through a fixing seat, and the end part of the bolt penetrates through a connecting hole on the lower shell and then is screwed into a threaded hole at the other end of the separation explosion bolt.
In one possible implementation manner, the unmanned aerial vehicle further comprises a supporting body arranged between the upper shell and the unmanned aerial vehicle body, the supporting body is arranged on two sides of the front portion of the unmanned aerial vehicle body and two sides of the rear portion of the unmanned aerial vehicle body, the top surface of the supporting body is connected to the top wall in the upper shell, and the lower end of the supporting body is in butt joint with the unmanned aerial vehicle body.
One or more technical solutions provided in the embodiments of the present utility model at least have the following technical effects or advantages:
the embodiment of the utility model provides a cylindrical folding wing unmanned aerial vehicle, which is characterized in that the unmanned aerial vehicle receives stronger impact force along the axial direction between an upper shell and a lower shell in a launching stage, and the impact force between the upper shell and the lower shell can be greatly transferred to a first plug-in part and a second plug-in part which are matched in a plug-in way through the design of the first plug-in part and the second plug-in part, so that the shearing force born by a separation explosion bolt for connecting the upper shell and the lower shell is reduced, and the safety of the unmanned aerial vehicle in the storage, transportation and launching stages is improved. The utility model solves the problem that in the prior art, a barrel type folding wing unmanned aerial vehicle is always fixed in a transmitting barrel before being thrown, and a great impact force is generated on the axial direction of the transmitting barrel in the transmitting stage, so that the shell of the transmitting barrel can be separated in advance.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are required to be used in the description of the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the present utility model, and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
Fig. 1 is a schematic structural diagram of a barrel type folding wing unmanned aerial vehicle according to an embodiment of the present utility model.
Fig. 2 is an assembly schematic diagram of a pre-tightening stud and a tightening support according to an embodiment of the present utility model.
Fig. 3 is a schematic structural diagram of a pre-tightening stud according to an embodiment of the present utility model.
Fig. 4 is a schematic structural diagram of an overhaul navigation plug according to an embodiment of the present utility model.
Fig. 5 is a schematic structural diagram of a throwing mechanism according to an embodiment of the present utility model.
Reference numerals: 1-unmanned aerial vehicle; 101-a first hanging point; 102-a second hanging point; 103-an umbrella cabin; 2-a launch canister; 21-an upper shell; 211-upper overlap edges; 22-a lower shell; 221-lower overlap edges; 23-a first plug-in part; 24-a second plug-in part; 25-aviation jack; 3-separating the explosive bolt; 4-pre-tightening the stud; 41-mounting a barrel; 42-limiting guide posts; 43-pre-tightening the nails; 44-compressing the spring; 45-piston jack; 46-an annular table; 5-overhauling the aerial plug; 51-mounting seats; 511-a mounting shell; 512-cylinder; 52-external aerial insertion; 53-internal aviation plug; 54-conducting cable; 6-a driving member; 7-a first link assembly; 71-a first latch hook; 8-a second link assembly; 81-a second latch hook; 9-crank; 10-a bracket; 11-tightly pushing the support; 111-jacking holes; 12-support.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
In the description of the embodiments of the present utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the embodiments of the present utility model and simplify description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present utility model. The terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Furthermore, the terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the embodiments of the present utility model will be understood by those of ordinary skill in the art according to specific circumstances.
As shown in fig. 1 to 5, the barrel type folding wing unmanned aerial vehicle provided by the embodiment of the utility model comprises an unmanned aerial vehicle 1, a transmitting barrel 2 and a throwing mechanism.
The cartridge 2 includes an upper case 21 and a lower case 22, and the upper case 21 and the lower case 22 are butted to form a cylindrical structure. The lower end surface of the upper shell 21 is provided with at least one first plug-in connection part 23, the first plug-in connection part 23 is a groove or a bulge, and the upper end surface of the lower shell 22 is provided with a second plug-in connection part 24 matched with the first plug-in connection part 23.
The top wall in the upper shell 21 is provided with a throwing mechanism, and the unmanned aerial vehicle 1 is fixed in the transmitting cylinder 2 through the throwing mechanism.
It should be noted that, illustratively, the first plugging portion 23 in the present embodiment is a plugging slot disposed on the lower end surface of the upper shell 21, the second plugging portion 24 is a plugging plate disposed on the upper end surface of the lower shell 22, and the plugging plate has a structure with an upper portion not larger than a lower portion, preferably a structure with a small upper portion and a large lower portion, so as to ensure that the first plugging portion 23 and the second plugging portion 24 can be plugged and mounted and separated smoothly. In the launching stage, the upper shell 21 and the lower shell 22 are subjected to stronger impact force along the axial direction, and at the moment, the impact force between the upper shell 21 and the lower shell 22 can be greatly transferred to the first plug-in part 23 and the second plug-in part 24 which are in plug-in fit through the design of the first plug-in part 23 and the second plug-in part 24, so that the shearing force born by the separation explosion bolt 3 for connecting the upper shell 21 and the lower shell 22 is reduced, and the safety of the unmanned aerial vehicle 1 in the storage, transportation and launching stages is improved.
A separation sensor is arranged between the upper shell 21 and the lower shell 22, and the sensor can transmit information about whether the lower shell 22 is separated back to a flight control computer in the unmanned aerial vehicle 1 so that the flight control computer can analyze whether to execute the following program instructions. The separation sensor can adopt a structural form with a publication number of CN217778968U and a name of a casting state detection component in the unmanned aerial vehicle 1 aerial casting mechanism patent.
As shown in fig. 5, the throwing mechanism includes a driving piece 6, a crank 9, a first link assembly 7, and a second link assembly 8. The driving piece 6 is fixedly installed in the support 10, the support 10 is installed on the top wall in the upper shell 21, the middle part of the crank 9 is hinged on the support 10, one end of the crank 9 is hinged on the telescopic end of the driving piece 6 and one end of the first connecting rod assembly 7, and the other end of the first connecting rod assembly 7 is provided with the first locking hook 71. The other end of the crank 9 is hinged to one end of the second link assembly 8, and the other end of the second link assembly 8 is provided with a second latch hook 81. The middle parts of the first latch hook 71 and the second latch hook 81 are hinged to the bracket 10.
The both ends of unmanned aerial vehicle 1 upper portion are provided with first string of points 101 and second string of points 102 respectively, and first latch hook 71 hangs on first string of points 101, and second latch hook 81 hangs on second string of points 102. The driving piece 6 of the throwing mechanism drives the first connecting rod assembly 7 and the second connecting rod assembly 8 to move, so that the first lock hook 71 and the second lock hook 81 are unhooked or mounted, and further throwing or mounting of the unmanned aerial vehicle 1 is achieved. The mechanism disclosed by the utility model is simple in structure, few in transmission stage number, capable of maximally reducing accumulated errors and ensuring normal throwing of the unmanned aerial vehicle 1.
As shown in fig. 1 and 3, the present embodiment further includes a pre-tightening stud 4, where the pre-tightening stud 4 includes a mounting cylinder 41, a limit guide post 42, a pre-tightening nail 43, a compression spring 44, and a piston top post 45.
The installation section of thick bamboo 41 is installed on the epitheca 21, and spacing guide pillar 42 is installed to the lower extreme of installation section of thick bamboo 41, and pretension nail 43, compression spring 44 and piston jack-up 45 set gradually in installation section of thick bamboo 41 from top to bottom, and pretension nail 43 screw thread installation is in installation section of thick bamboo 41, and the lower extreme of piston jack-up 45 passes behind the hole in spacing guide pillar 42 center and abuts in unmanned aerial vehicle 1's fuselage.
It should be noted that, after the unmanned aerial vehicle 1 is fixed through the first latch hook 71 and the second latch hook 81, the pre-tightening nail 43 is screwed up, so that the compression spring 44 is compressed, and then the piston jack-up post 45 is tightly propped up the unmanned aerial vehicle 1, so that the unmanned aerial vehicle 1 can be further fixed without loosening, and the piston jack-up post 45 can push the unmanned aerial vehicle 1 to accelerate and keep away from the mechanism when the unmanned aerial vehicle 1 is thrown, thereby ensuring the reliability when the unmanned aerial vehicle 1 is thrown.
The mechanism is provided with two pre-tightening studs 4, and the two pre-tightening studs 4 are respectively arranged at the two lock hooks, so that the safety of the throwing mechanism in fixing and throwing is improved.
In this embodiment, the upper end of the compression spring 44 is sleeved on the protruding block at the lower end of the pre-tightening nail 43, and the lower end of the compression spring 44 extends into the blind hole at the upper end of the piston top column 45. This allows for better fixation of the compression spring 44.
The limit guide post 42 is arranged in a threaded hole at the lower end of the mounting cylinder 41 in a threaded manner, an annular table 46 is arranged at the upper end of the piston top post 45 in the circumferential direction, and the annular table 46 is matched with the upper end of the limit guide post 42. The limiting guide post 42 limits the piston jack post 45, and prevents the piston jack post 45 from falling out of the lower end of the mounting cylinder 41.
As shown in fig. 2, in the present embodiment, the lower end of the piston jack 45 extends into the jack 111 on the body of the unmanned aerial vehicle 1, and the end of the piston jack 45 abuts against the bottom wall of the jack 111.
The unmanned aerial vehicle 1 is provided with a tightening support 11, and a tightening hole 111 is formed in the center of the tightening support 11. The end part of the piston top column 45 extends into the top tightening hole 111, so that the unmanned aerial vehicle 1 is locked axially and laterally, and the stability of the unmanned aerial vehicle 1 in the storage, transportation and launching stages is improved.
As shown in fig. 4, the embodiment further comprises an overhaul aviation plug 5 and an umbrella bag. The maintenance aviation plug 5 is installed between the upper shell 21 and the fuselage of the unmanned aerial vehicle 1, the lower end of the maintenance aviation plug 5 is connected to a plug on the fuselage of the unmanned aerial vehicle 1, and the upper shell 21 is provided with an aviation jack 25 matched with the upper end of the maintenance aviation plug 5.
The umbrella bag is arranged at the rear end in the transmitting cylinder 2.
It should be noted that, the staff can pass through the aviation jack 25 with the input of check out test set and connect in the maintenance aviation plug 5, and then can go on electricity or lower electricity to unmanned aerial vehicle 1 before unmanned aerial vehicle 1 launches, can also carry out the preceding inertial navigation of launching and decide, consequently unmanned aerial vehicle 1 need not electrified transportation, and then improved the security of barrel folding wing unmanned aerial vehicle, avoided only can remove unmanned aerial vehicle 1 electrified transportation state through dismantling transmission barrel 2, and have the problem of wasting time and energy, the maintenance aviation plug 5 simple structure of the utility model, the practicality is strong.
The umbrella bag comprises a traction rope, a guiding umbrella and a main umbrella, one end of the traction rope is connected to the umbrella cabin 103, and the main umbrella and the guiding umbrella are sequentially arranged on the other side of the traction rope. The parachute cabin 103 is fixed to the tail of the body of the barrel type folding wing unmanned aerial vehicle. The umbrella bag can protect the launching tube 2 and the unmanned aerial vehicle 1 from falling down safely under the unexpected condition, thereby improving the safety of the launching tube 2.
In this embodiment, the service plug 5 includes a mounting base 51, an outer plug 52, an inner plug 53, and a conductive cable 54.
The installation seat 51 is provided with an installation cavity, the outer aviation plug 52 is installed at the upper end of the installation cavity, the inner aviation plug 53 is installed at the lower end of the installation cavity, the outer aviation plug 52 and the inner aviation plug 53 are connected through a conducting cable 54, and the inner aviation plug 53 is connected to a plug on the body of the unmanned aerial vehicle 1.
It should be noted that, during the throwing of the unmanned aerial vehicle 1, the plug on the fuselage is directly disconnected from the internal aerial socket 53, so that the overhaul aerial socket 5 of the present utility model does not affect the transportation and throwing of the unmanned aerial vehicle 1.
In this embodiment, the mounting seat 51 includes a mounting shell 511 and a cylinder 512, the mounting shell 511 is a hollow shell, the top surface of the mounting shell 511 is a cambered surface, the top surface of the mounting shell 511 is connected to the top wall in the upper shell 21, the inside of the cylinder 512 is a mounting cavity, and the cylinder 512 is disposed on one side of the mounting shell 511.
The mounting case 511 is configured to be easily mounted to the thin-walled upper case 21, and has a certain structural strength.
In this embodiment, the front end of the launch canister 2 is arc-shaped, and the tail of the launch canister 2 is provided with stabilizing wings.
The outer shape of the transmitting tube 2 is not limited to the provided illustration, and the tube wall of the transmitting tube 2 adopts an arc shape, so that the overall structural strength is high, and the transmitting tube 2 is simple to install due to the design of the upper shell 21 and the lower shell 22 in two halves. The stabilizing wings can stabilize the posture of the launch canister 2 at the time of casting.
In this embodiment, the explosion-proof device further comprises a separation explosion bolt 3, wherein one end of the separation explosion bolt 3 is installed at the lower end of the upper shell 21 through a fixing seat, and the end of the screw penetrates through a connecting hole on the lower shell 22 and then is screwed into a threaded hole at the other end of the separation explosion bolt 3.
The lower end surface of the upper case 21 is provided with an upper joint edge 211, and the upper end surface of the lower case 22 is provided with a lower joint edge 221. One end of the separation explosion bolt 3 is mounted on the upper joint edge 211 through a fixing seat, and the end of the screw passes through a connecting hole on the lower joint edge 221 and is screwed into a threaded hole at the other end of the separation explosion bolt 3. The upper joint edge 211 and the lower joint edge 221 are overlapped and then the outer wall of the launching tube 2 is flush, so that the structure is attractive and has high strength.
The number of the separation explosion bolts 3 is at least four, and the number of the separation explosion bolts 3 is increased to six or eight according to practical situations, and a plurality of the separation explosion bolts 3 are uniformly distributed in the circumferential direction of the launching tube 2.
One end of the separation explosion bolt 3 is arranged on the upper joint edge 211 through a fixed seat, and the end part of the screw is screwed into a threaded hole at the other end of the separation explosion bolt 3. When the separation explosion bolt 3 receives a throwing signal, the middle part of the separation explosion bolt 3 explodes and breaks, so that one end of the separation explosion bolt 3 and a fixed seat are left on the upper joint edge 211, and the other end of the separation explosion bolt 3 and a screw are left on the lower joint edge 221, so that the upper shell 21 and the lower shell 22 are released from constraint, and the separation of the upper shell 21 and the lower shell 22 is realized.
In this embodiment, the clearance between the first plug portion 23 and the second plug portion 24 is smaller than the clearance between the screws in the connecting holes. Therefore, when the first plug-in part 23 and the second plug-in part 24 are abutted tightly and cannot move relatively, the screw can still move in the connecting hole, so that the shearing force born by the separation explosion bolt 3 is eliminated.
In this embodiment, the unmanned aerial vehicle further comprises a supporting body 12 arranged between the upper shell 21 and the unmanned aerial vehicle 1, the supporting body 12 is arranged on two sides of the front portion and two sides of the rear portion of the unmanned aerial vehicle, the top surface of the supporting body 12 is connected to the top wall in the upper shell 21, and the lower end of the supporting body 12 is abutted to the unmanned aerial vehicle 1.
The top surface of the support body 12 is attached to the inner wall of the upper case 21, and the lower end of the support body 12 is attached to the body structure. The supporting bodies 12 on the front side and the rear side are respectively arranged at the front end and the rear end of the throwing mechanism. The support body 12 can further limit the movement of the unmanned aerial vehicle 1 in the launching tube 2, reduce the vibration of the unmanned aerial vehicle 1 in the transportation and launching processes, and improve the safety of the throwing mechanism.
In the present embodiment, it will be apparent to those skilled in the art that the present utility model is not limited to the details of the above-described exemplary embodiments, but that the present utility model may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the utility model being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
Claims (10)
1. A folding wing unmanned aerial vehicle of cylinder, its characterized in that: comprises an unmanned plane (1), a transmitting cylinder (2) and a throwing mechanism;
the transmitting cylinder (2) comprises an upper shell (21) and a lower shell (22), and the upper shell (21) and the lower shell (22) are in butt joint to form a cylindrical structure; the lower end face of the upper shell (21) is provided with at least one first plug-in part (23), the first plug-in part (23) is a groove or a bulge, and the upper end face of the lower shell (22) is provided with a second plug-in part (24) matched with the first plug-in part (23);
the top wall in the upper shell (21) is provided with the throwing mechanism, and the unmanned aerial vehicle (1) is fixed in the transmitting cylinder (2) through the throwing mechanism.
2. A folding wing drone of cartridge type as claimed in claim 1, wherein: the device further comprises a pre-tightening stud (4), wherein the pre-tightening stud (4) comprises a mounting cylinder (41), a limiting guide post (42), a pre-tightening nail (43), a compression spring (44) and a piston top post (45);
the utility model discloses a unmanned aerial vehicle, including upper shell (21), mounting cylinder (41), spacing guide pillar (42) are installed to the lower extreme of mounting cylinder (41), pretension nail (43) compression spring (44) with piston jack-up post (45) from last down set gradually in mounting cylinder (41), pretension nail (43) screw thread install in mounting cylinder (41), the lower extreme of piston jack-up post (45) pass behind the hole in spacing guide pillar (42) center butt in the fuselage of unmanned aerial vehicle (1).
3. A folding wing drone of claim 2, wherein: the upper end of the compression spring (44) is sleeved on a convex block at the lower end of the pre-tightening nail (43), and the lower end of the compression spring (44) extends into a blind hole at the upper end of the piston top column (45);
the limiting guide post (42) is arranged in a threaded hole in the lower end of the mounting cylinder (41) in a threaded mode, an annular table (46) is arranged at the upper end of the piston top column (45) in the circumferential direction, and the annular table (46) is matched with the upper end of the limiting guide post (42).
4. A folding wing drone of claim 2, wherein: the lower extreme of piston jack-up post (45) stretches into in tight hole (111) in top on the fuselage of unmanned aerial vehicle (1), the tip butt of piston jack-up post (45) in the diapire in tight hole (111).
5. A folding wing drone of cartridge type as claimed in claim 1, wherein: the device also comprises an overhaul aviation plug (5) and an umbrella bag; the overhaul aerial plug (5) is arranged between the upper shell (21) and the body of the unmanned aerial vehicle (1), the lower end of the overhaul aerial plug (5) is connected with a plug on the body of the unmanned aerial vehicle (1), and the upper shell (21) is provided with an aerial jack (25) matched with the upper end of the overhaul aerial plug (5);
the umbrella bag is arranged at the rear end in the transmitting cylinder (2).
6. The folding wing drone of claim 5, wherein: the overhaul aerial plug (5) comprises a mounting seat (51), an outer aerial plug (52), an inner aerial plug (53) and a conducting cable (54);
the installation seat (51) is provided with an installation cavity, the outer aviation plug (52) is installed at the upper end of the installation cavity, the inner aviation plug (53) is installed at the lower end of the installation cavity, the outer aviation plug (52) and the inner aviation plug (53) are connected through the conducting cable (54), and the inner aviation plug (53) is connected to a plug on the body of the unmanned aerial vehicle (1).
7. The folding wing drone of claim 6, wherein: the mounting seat (51) comprises a mounting shell (511) and a barrel body (512), the mounting shell (511) is a shell body with a hollow inside, the top surface of the mounting shell (511) is an arc surface, the top surface of the mounting shell (511) is connected to the top wall in the upper shell (21), the inside of the barrel body (512) is the mounting cavity, and the barrel body (512) is arranged on one side of the mounting shell (511).
8. A folding wing drone of cartridge type as claimed in claim 1, wherein: the front end of the transmitting cylinder (2) is arc-shaped, and the tail of the transmitting cylinder (2) is provided with stabilizing wings.
9. A folding wing drone of cartridge type as claimed in claim 1, wherein: the explosion-proof device is characterized by further comprising a separation explosion bolt (3), wherein one end of the separation explosion bolt (3) is arranged at the lower end of the upper shell (21) through a fixing seat, and the end part of the bolt penetrates through a connecting hole in the lower shell (22) and then is screwed into a threaded hole at the other end of the separation explosion bolt (3).
10. A folding wing drone of cartridge type as claimed in claim 1, wherein: still including set up in support body (12) between the fuselage of epitheca (21) with unmanned aerial vehicle (1), the both sides at fuselage front portion and the both sides at rear portion all are provided with support body (12), the top surface of support body (12) connect in roof in epitheca (21), the lower extreme of support body (12) with the fuselage butt of unmanned aerial vehicle (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320667699.1U CN219524289U (en) | 2023-03-29 | 2023-03-29 | Unmanned aerial vehicle with barrel-type folding wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320667699.1U CN219524289U (en) | 2023-03-29 | 2023-03-29 | Unmanned aerial vehicle with barrel-type folding wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219524289U true CN219524289U (en) | 2023-08-15 |
Family
ID=87584847
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320667699.1U Active CN219524289U (en) | 2023-03-29 | 2023-03-29 | Unmanned aerial vehicle with barrel-type folding wings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219524289U (en) |
-
2023
- 2023-03-29 CN CN202320667699.1U patent/CN219524289U/en active Active
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