CN110937110A - A scray for unmanned aerial vehicle - Google Patents

Abstract

The application provides a folder for an unmanned aerial vehicle, which comprises a first sleeve and a second sleeve which are hinged with each other, wherein the first sleeve and the second sleeve are respectively sleeved at the end parts of two parts needing to be folded; the first and second sleeves are hinged together by a hinge bar such that the first and second sleeves can be folded relative to each other by the hinge bar; a conical boss formed by buckling extends outwards from the matching surface of the first sleeve and the second sleeve; a conical cap which can be connected with the conical boss in a pressing mode is arranged on the outer side of the conical boss; the conical cap is connected to the outer side of the conical boss in an extruding mode through a screw. Through the folder for the unmanned aerial vehicle of this application, unmanned aerial vehicle's cantilever and undercarriage isotructure all can draw close each other and carry out quick folding, can obtain littleer folding volume, and folding efficiency is higher, is favorable to unmanned aerial vehicle's warehousing and transportation.

Description

A scray for unmanned aerial vehicle

Technical Field

The application relates to the technical field of unmanned aerial vehicles, especially relates to a folding unmanned aerial vehicle, in particular to a folder for an unmanned aerial vehicle.

Background

The unmanned aerial vehicle at present is multiaxis unmanned aerial vehicle mostly, like four-axis, six, the complete machine weight of taking off is very little, but the cantilever expansion is very big, brings certain difficulty for unmanned aerial vehicle's transportation, carry and save etc.. For example, CN 204587305U discloses eight rotor electric unmanned aerial vehicle of multi-functional folded cascade, mainly solves the problem that current unmanned aerial vehicle usage is single, the structure is complicated, complete machine transportation difficulty. The angle such as eight rotors of above-mentioned prior art's unmanned aerial vehicle is around the organism setting, leads to the application load of carrying on the organism to set up under the organism only, and because each direction all receives blockking of rotor, the load of carrying can only develop the operation downwards, can not launch the weapon or observe to oblique top, just as introduce in this prior art, this unmanned aerial vehicle can only be suitable for in its description the operation such as sprays below to unmanned aerial vehicle.

In order to solve the technical problem, CN 207550499U provides an electric unmanned aerial vehicle. This prior art's electric unmanned aerial vehicle sets up a longitudinal load passageway that does not shelter from through in the fuselage below, can conveniently set up loads such as photoelectricity hanging storehouse and weapon launch canister, and take place to interfere with cantilever and screw when avoiding surveing and the weapon transmission, influence use and combat efficiency, improved unmanned aerial vehicle's range of application. In addition, this prior art has reduced the volume after folding through setting for the overall layout structure of optimization, the low-cost transportation of the unmanned aerial vehicle of being convenient for. The above prior art effectively overcomes the deficiencies of the prior art, but there is still room for improvement. Especially when the folding volume of unmanned aerial vehicle needs further to dwindle to in quick assembly disassembly, when transporting, current unmanned aerial vehicle's beta structure still has further improved space.

In addition, when reducing unmanned aerial vehicle folding volume, the beta structure of adoption also needs to carry out further improvement on the reliability, further excavates the potentiality that lightens structure weight on the basis of current beta structure, also has very big improvement space.

Disclosure of Invention

The technical problem that this application will be solved is to provide a folder for unmanned aerial vehicle to reduce or avoid the aforementioned problem.

In order to solve the technical problem, the application provides a folder for an unmanned aerial vehicle, which is used for being arranged in a structural part needing to be folded of the unmanned aerial vehicle, wherein the folder comprises a first sleeve and a second sleeve which are hinged with each other, and the first sleeve and the second sleeve are respectively sleeved at the end parts of the two parts needing to be folded; the first and second sleeves are hinged together by a hinge bar such that the first and second sleeves can be folded relative to each other by the hinge bar; a conical boss formed by buckling extends outwards from the matching surface of the first sleeve and the second sleeve; a conical cap which can be connected with the conical boss in a pressing mode is arranged on the outer side of the conical boss; the conical cap is connected to the outer side of the conical boss in an extruding mode through a screw.

Preferably, the matching surfaces of the first sleeve and the second sleeve are provided with convex-concave parts which are mutually buckled.

Preferably, the tapered boss includes a first half boss formed on the second sleeve and a second half boss formed on the first sleeve.

Preferably, a screw passage portion through which the screw passes is formed on one of the first half boss and the second half boss.

Preferably, a nut adapter is arranged on the inner side of the screw channel part; the screw penetrates through the screw channel part and is connected with the screw cap adapter; the screw presses the conical cap on the outer sides of the first half boss and the second half boss to enable the first half boss and the second half boss to be buckled to form the conical boss.

Preferably, the folder is arranged in a foldable undercarriage of the unmanned aerial vehicle, the foldable undercarriage comprises a first foldable support located on one side of the body and a second foldable support corresponding to the first foldable support and located on the other side of the body, and two pull rods are connected between the first foldable support and the second foldable support; the first folding bracket can be folded towards the second folding bracket by the folder arranged therein to be in a state of being parallel to the pull rod; the second folding bracket can be folded toward the first folding bracket to be parallel to the pull rod by the folder provided therein.

Preferably, the first folding bracket is adjacent to the pull rod after being folded; after the second folding support is folded, the second folding support is close to the first folding support, and the first folding support is clamped between the second folding support and the pull rod.

Preferably, the folder is arranged in a foldable cantilever system of the unmanned aerial vehicle, and the foldable cantilever system comprises four first cantilevers obliquely extending outwards from the head and the tail of the fuselage and two second cantilevers extending outwards from the two sides of the middle of the fuselage; the two first cantilevers located on the same side of the fuselage may be folded against each other by the folder provided therein.

Preferably, said second cantilever is divided into a rear arm portion and a front arm portion by one of said folders disposed therein; the front arm part can be folded by the folder to close the rear arm part, the rear arm part can be folded by the other folder to close the side wall of the machine body, and the front arm part is clamped between the rear arm part and the side wall of the machine body.

Through the folder for the unmanned aerial vehicle of this application, unmanned aerial vehicle's cantilever and undercarriage isotructure all can draw close each other and carry out quick folding, can obtain littleer folding volume, and folding efficiency is higher, is favorable to unmanned aerial vehicle's warehousing and transportation.

Drawings

The drawings are only for purposes of illustrating and explaining the present application and are not to be construed as limiting the scope of the present application. Wherein,

fig. 1 shows a schematic structural diagram of a drone according to a specific embodiment of the present application;

fig. 2 shows a schematic view of the unmanned aerial vehicle of fig. 1 in a folded state;

FIG. 3 shows a schematic view of a landing gear according to a particular embodiment of the present application;

figure 4 shows a schematic view of the landing gear of figure 3 in a collapsed state;

fig. 5 shows a schematic structural view of a boom of a drone with a folder according to a particular embodiment of the present application;

fig. 6 shows an enlarged schematic view of a folder for a drone according to a particular embodiment of the present application;

fig. 7 shows an exploded schematic view of a folder for a drone according to another particular embodiment of the present application;

fig. 8 shows an exploded view of a folder for a drone according to yet another particular embodiment of the present application.

Detailed Description

In order to more clearly understand the technical features, objects, and effects of the present application, embodiments of the present application will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.

Just as the background art said, this application is directed against the not enough of the electric unmanned aerial vehicle that discloses in prior art CN 207550499U, has proposed a folding unmanned aerial vehicle who improves structure, can obtain littleer structure size, and unmanned aerial vehicle's folding volume is littleer moreover to quick assembly disassembly and transportation are convenient for.

That is, to achieve the above object, the present application provides a foldable drone, as shown in fig. 1-2, where fig. 1 shows a schematic perspective view of a foldable drone according to an embodiment of the present application; fig. 2 shows a schematic view of the foldable drone of fig. 1 in a folded state.

Referring to fig. 1-2, the foldable drone of the present application comprises a fuselage 1, two foldable undercarriages 2 and a foldable cantilever system 3 supporting motors 4, each motor 4 carrying a propeller 5.

What is different from the prior art in this application is that the cantilever system 3 of unmanned aerial vehicle of this application is collapsible, and it includes four first cantilevers 31 that outwards stretch out to one side from the head and the tail both sides of fuselage 1 to and two second cantilevers 32 that outwards stretch out from the middle part both sides of fuselage 1, and wherein, the end-supported propeller 5 of first cantilever 31 is located the top of first cantilever 31 and arranges upwards, and the end-supported propeller 5 of second cantilever 32 is located the below of second cantilever 32 and arranges downwards.

The foldable unmanned aerial vehicle has the advantages that the distance between the four first cantilevers 31 extending outwards in the inclined mode is the largest, and the problem of interference cannot occur between the propellers 5 on the four first cantilevers 31, so that the propellers 5 on the four first cantilevers 31 can be arranged upwards. Two second cantilevers 32 are located the middle part of fuselage 1, interval between two first cantilevers 31 with the homonymy is less relatively, screw 5 on it interferes with the screw on the adjacent first cantilever 31 easily, therefore screw 5 on two second cantilevers 32 is arranged downwards and is reduced the interference, be favorable to reducing the length of cantilever, unmanned aerial vehicle can obtain littleer structure size on the whole, therefore can greatly reduced unmanned aerial vehicle's volume, be convenient for unmanned aerial vehicle's warehousing and transportation.

Further, propeller 5 on first cantilever 31 and the second cantilever 32 sets up in reverse, further is favorable to unmanned aerial vehicle's folding again. As shown in fig. 2, where the first boom 31 is connected to the main body 1 by a first folder 11, two first booms 31 located on the same side of the main body 1 can be folded opposite to each other by the first folder 11. In order to avoid the mutual interference of the folded structures, it can be seen in the drawing that when the two first cantilevers 31 on the same side are folded toward each other, there is a slight upward angle to avoid the tail end of the folded first cantilever 31 from propping the root of the other first cantilever 31, which is more beneficial to the folded first cantilever 31 to get close to the side wall of the fuselage 1 as much as possible, and is beneficial to obtaining smaller volume.

Further, a second folder 12 is arranged at the joint of the second cantilever 32 and the machine body 1; the middle of the cantilever 32 is provided with a third folder 13, and the second cantilever 32 is divided by the third folder 13 into a rear arm portion 131 and a front arm portion 132; wherein the section near the body 1 is a rear arm part 131, and the section far from the body 1 is a front arm part 132, as shown in the figure. The front arm portion 132 can be folded by the third folder 13 close to the rear arm portion 131, and the rear arm portion 131 can be folded by the second folder 12 close to the side wall of the body 1, and the front arm portion 132 is sandwiched between the rear arm portion 131 and the side wall of the body 1. In the illustrated embodiment, the second boom 32 is folded generally toward the tail of the drone. Of course, depending on the actual situation, the second boom 32 may also be set to fold as a whole towards the head of the drone.

In the above embodiment, the second suspension arm 32 is folded in two stages, and the front arm part 132 is folded toward the rear arm part 131, and then the rear arm part 131 carries the front arm part 132 toward the body. Because the propeller 5 at the end of the second cantilever 32 is arranged downwards, after the second cantilever 32 is folded twice, the propeller 5 at the end of the second cantilever can perfectly avoid the first cantilever 31, and the problem that the folded structures interfere with each other is avoided. In addition, in a preferred embodiment, the vertical installation position of the second suspension arm 32 on the body 1 is lower than the vertical installation position of the first suspension arm 31 on the body 1, so that the second suspension arm 32 as a whole can be arranged below the first suspension arm 31 to be folded, and the second suspension arm 32 can be close to the side wall of the body 1 as much as possible after being folded twice without interference, which is beneficial to reducing the folding volume.

In the folding unmanned aerial vehicle of this application, six cantilevers of cantilever system divide into two sets ofly to fold, and the great first cantilever in interval is folding relatively each other, and the second cantilever at fuselage middle part adopts two segmentation foldings, can form the beta structure of the range upon range of formula shown in figure 2, has avoided the defect that current cantilever fold-down suspended structure is highly big, be difficult to the transportation, has reduced unmanned aerial vehicle's volume, the warehousing and transportation of being convenient for.

Further, the folding unmanned aerial vehicle of this application still has folding undercarriage.

As shown in fig. 3, as mentioned above, the foldable landing gear of the present application is used for being installed at two sides below the fuselage 1 of the unmanned aerial vehicle, that is, two sides of the fuselage 1 are respectively and symmetrically provided with one landing gear 2, and a pull rod 27 for reinforcing the structure is added between two landing gears 2 compared with the prior art. FIG. 3 shows a schematic view of a foldable landing gear according to an embodiment of the present application.

For convenience of explanation of the structure and folding principle of the foldable landing gear of the present application, in the following description, a landing gear on one side of the fuselage 1 is defined as a first folding bracket 20, a landing gear on the other side of the fuselage 1 corresponding to the first folding bracket 20 is defined as a second folding bracket 30, and the first folding bracket 20 and the second folding bracket 30 have substantially the same structure, and two tie rods 27 are connected therebetween. That is, by definition, the foldable landing gear of the present application comprises a first folding bracket 20 located on one side of the fuselage 1, and a second folding bracket 30 located on the other side of the fuselage 1, corresponding to the first folding bracket 20, with two tie rods 27 connected between the first folding bracket 20 and the second folding bracket 30. The above structure is in fact substantially the same as the unmanned aircraft landing gear mentioned in the background, with the difference that the first folding leg 20 and the second folding leg 30 of the foldable landing gear of the present application both have a foldable structure, and that the first folding leg 20 and the second folding leg 30 can be folded in a specific way, which can significantly reduce the bulk of the landing gear.

The collapsible landing gear of the present application is described in further detail below with reference to figures 3-4, which are improvements over the prior art, and as to structures not described in the present application, those skilled in the art will understand with reference to the figures and the prior art. In which figure 4 shows a schematic view of the foldable landing gear shown in figure 3 in a folded state.

As shown in the drawings, in one embodiment of the present application, the first folding bracket 20 is provided with a fourth folder 212 below a position where it is connected to the drawbar 27, and the first folding bracket 20 can be folded toward the second folding bracket 30 by the fourth folder 212 to a state of being substantially parallel to the drawbar 27; the second folding bracket 30 is provided with a fifth folder 213 below the position where it is connected to the draw bar 27, and the second folding bracket 30 can be folded toward the first folding bracket 20 by the fifth folder 213 to a state substantially parallel to the draw bar 27, as shown in fig. 4 after the folding.

In the particular embodiment shown in fig. 5 and 6, the first folding bracket 20 is folded next to the tie rod 27; the second folding bracket 30 is folded next to the first folding bracket 20 and the first folding bracket 20 is sandwiched between the second folding bracket 30 and the draw bar 27. That is, in the illustrated embodiment, the first folding leg 20 is folded first, and then the second folding leg 30 is folded. To ensure that this folding does not interfere, it is preferred that the vertical distance of the fourth folder 212 from the pull rod 27 is less than the vertical distance of the fifth folder 213 from the pull rod 27.

Further, as shown in the drawings, the first folding bracket 20 and the second folding bracket 30 of the present application each include two vertical bars 21 connected to the body and a cross bar 22 disposed at the end of the vertical bar 21, and the upper ends of the two vertical bars 21 are fixedly connected to the body. Specifically, the first folding bracket 20 includes two vertical bars 21 connected to the body and a cross bar 22 disposed at the end of the vertical bars 21; the two vertical rods 21 are respectively connected with a pull rod 27; the two vertical bars 21 of the first folding bracket 20 are each provided with a fourth folder 212 below the position where they are connected to the tie bar 27. The second folding bracket 30 also comprises two vertical rods 21 connected with the machine body and a cross rod 22 arranged at the tail ends of the vertical rods 21; the two vertical rods 21 are respectively connected with a pull rod 27; the two vertical bars 21 of the second folding bracket 30 are each provided with a fifth folder 213 below the position where they are connected to the tie bar 27.

Also to avoid folding interference, it is preferable that the fourth folders 212 on the two vertical bars 21 of the first folding bracket 20 have the same vertical distance from the corresponding tie rods 27. The fifth folders 212 on the two vertical bars 21 of the second folding bracket 30 have the same vertical distance from the corresponding tie rods 27.

The above embodiment has described the folding structure of the foldable unmanned aerial vehicle and the principle thereof in detail, and the foldable cantilever system 3 provided therein is provided with the first folder 11, the second folder 12 and the third folder 13; the foldable landing gear 2 is provided with a fourth folder 212 and a fifth folder 213, and the above five folders can all adopt folders with the same structure principle. For example, fig. 5 shows a schematic view of a cantilever with a folder according to an embodiment of the present application, which is embodied as a second cantilever 32 having a second folder 12 and a third folder 13 thereon, respectively, the second cantilever 32 being divided by the third folder 13 into a rear arm portion 131 and a front arm portion 132. Wherein the second folder 12 is in the mounted state and the third folder 13 is in the unfolded state. As can be seen from fig. 5, the basic structure of the second and third folders 12 and 13 is the same, differing only slightly in size, mounting position, and angle.

The specific structure of the folder for a drone of the present application is described in further detail below with reference to fig. 6-8, wherein fig. 6 shows an enlarged schematic view of the folder for a drone according to one specific embodiment of the present application; fig. 7 shows an exploded schematic view of a folder for a drone according to another particular embodiment of the present application; fig. 8 shows an exploded view of a folder for a drone according to yet another particular embodiment of the present application.

In particular, the present application provides a folder for a drone, for being arranged in a structural part of the drone that needs to be folded, connecting two parts that can be folded with respect to each other by the folder, which can be a cantilever of the drone or a landing gear, as previously described. As shown in fig. 6 to 8, the folder of the present application includes a first sleeve 29 and a second sleeve 28 hinged to each other, and the first sleeve 29 and the second sleeve 28 are respectively sleeved on the ends of two members to be folded, such as the ends of a rod-shaped structure like a cantilever or a landing gear.

As shown in fig. 6 to 8 in particular, the first and second casings 29 and 28 are hinged together by a hinge rod 283 so that the first and second casings 29 and 28 can be folded with respect to each other by the hinge rod 283.

Further, mating surfaces of the first sleeve 29 and the second sleeve 28 are formed with convexities and concavities 284 that are engaged with each other. In the illustrated embodiment, the first sleeve 29 is provided with an upward protrusion, and the second sleeve 28 is provided with a downward recess, which form the convex-concave portion 284 in a matching relationship, so that the two matching surfaces can be fastened together to avoid the mutual dislocation of the matching surfaces, thereby improving the stability and firmness of the connection. Of course, the protrusions and recesses may be interchanged, i.e. the first sleeve 29 is provided with a downward facing recess and correspondingly the second sleeve 28 is provided with an upward facing protrusion cooperating therewith.

Further, the mating surfaces of the first sleeve 29 and the second sleeve 28 are extended outward to form a conical boss 285 formed by buckling; the outside of the conical boss 285 is provided with a conical cap 286 that can be compressed into engagement with the conical boss 285. The folder shown in the above embodiment of the present application can connect the first sleeve 29 and the second sleeve 28 into a whole by pressing the tapered boss 285 formed by buckling the tapered cap 286, and when disassembling the cantilever or the landing gear, only the tapered cap 286 needs to be released, so that the tapered boss 285 is no longer pressed by the tapered cap 286, the first sleeve 29 and the second sleeve 28 can be quickly separated from the constraint, and the second sleeve 28 can be folded towards the first sleeve 29 around the hinge rod 283.

In one particular embodiment, the tapered bosses 285 include a first half boss 2851 formed on the second sleeve 28 and a second half boss 2852 formed on the first sleeve 29. In another embodiment, the tapered cap 286 is attached to the outside of the tapered boss 285 by a threaded rod 287, and the tapered cap 286 can be pressed to the outside of the first half-boss 2851 and the second half-boss 2852 by the threaded rod 287 to snap-fit the two to form the tapered boss 285. That is, during disassembly, the screw 287 is only required to be unscrewed, the cone-shaped cap 286 can be unscrewed, the cone-shaped boss 285 is not extruded any more, the first half boss 2851 and the second half boss 2852 can be disengaged, and the folding can be easily realized. In practice, the screw 287 is preferably not completely unscrewed, but only the conical cap 286 is loosened, so as to avoid losing the screw 287.

In yet another embodiment, a screw channel portion 2871 through which the screw 287 passes is formed on one of the first half boss 2851 and the second half boss 2852. In the illustrated embodiment, the screw channel portion 2871 is formed on the second half-boss 2852 (although the positions of the screw channel portion can be interchanged with the second half-boss 2852), and naturally forms a protrusion, and correspondingly, the first half-boss 2851 is formed with a recess (not shown in the figure) matching with the protrusion, so that a positioning relationship is formed when the first half-boss 2851 and the second half-boss 2852 are fastened, the position misalignment is avoided, and the firmness and stability of the connection are improved.

In a further embodiment, a nut adaptor 2872 is provided inside the screw channel portion 2871; the screw 287 is connected to the nut adapter 2872 through the screw channel portion 2871. The screw 287 is connected to the nut adapter 2872 by a screw thread, and during the process of screwing the screw 287, the screw 287 moves relative to the nut adapter 2872, and the tapered cap 286 can be pressed on the outer sides of the first half-boss 2851 and the second half-boss 2852 to be buckled together to form the tapered boss 285. In the illustrated embodiment, the nut adaptor 2872 is attached to the inside of the screw channel portion 2871 by screws or the like.

In another embodiment, the nut adapter 2872 is preferably made of a hard metal to withstand the large clamping pressure forces and avoid connection failures due to thread damage to the lightweight metal threaded connection. Specifically, the nut adaptor 2872 may be made of hard alloy steel or titanium alloy, which may be itself processed to form an internal thread matching the screw 287, or as shown in fig. 7-8, a nut 288 threadedly connected with the screw 287 may be further disposed on the inner side of the nut adaptor 2872, and the nut 288 may be fixedly connected to the inner side of the nut adaptor 2872 by welding or bonding, so as to prevent the nut 288 from falling into the interior of the first sleeve 29 after the screw 287 is unscrewed.

In conclusion, through the folder for unmanned aerial vehicle of this application, unmanned aerial vehicle's cantilever and undercarriage isotructure all can draw close each other and fold fast, can obtain littleer folding volume, and folding efficiency is higher, is favorable to unmanned aerial vehicle's warehousing and transportation. Folding part owing to need not to dismantle from unmanned aerial vehicle, can directly fold and reduce the volume, also very conveniently resume into the user state from fold condition moreover, has improved unmanned aerial vehicle's warehousing and transportation efficiency greatly.

It should be appreciated by those skilled in the art that while the present application is described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is thus given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including all technical equivalents which are encompassed by the claims and are to be interpreted as combined with each other in a different embodiment so as to cover the scope of the present application.

The above description is only illustrative of the present invention and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations that may be made by those skilled in the art without departing from the spirit and principles of this application shall fall within the scope of this application.

Claims (10)

1. A folder for a drone, for being arranged in a structural part of the drone to be folded, connecting two parts foldable with respect to each other by means of the folder, characterized in that it comprises a first sleeve (29) and a second sleeve (28) hinged to each other, said first sleeve (29) and second sleeve (28) being fitted respectively on the ends of said two parts to be folded; the first and second sleeves (29, 28) are hinged together by a hinge bar (283) such that the first and second sleeves (29, 28) can be folded against each other by the hinge bar (283); a conical boss (285) formed by buckling extends outwards from the matching surfaces of the first sleeve pipe (29) and the second sleeve pipe (28); a conical cap (286) which can be connected with the conical boss (285) in a pressing mode is arranged on the outer side of the conical boss (285); the conical cap (286) is connected to the outer side of the conical boss (285) in a pressing mode through a screw rod (287).

2. A folder as claimed in claim 1, wherein the mating surfaces of said first sleeve (29) and said second sleeve (28) are formed with mutually snapping reliefs (284).

3. The folder as recited in claim 2, wherein the tapered boss (285) comprises a first half boss (2851) formed on the second sleeve (28) and a second half boss (2852) formed on the first sleeve (29).

4. The folder according to claim 3, wherein one of said first half-boss (2851) and said second half-boss (2852) has a screw channel portion (2871) formed thereon through which said screw (287) passes.

5. The folder according to claim 4, characterized in that the inner side of said screw channel portion (2871) is provided with a nut adaptor (2872); the screw rod (287) penetrates through the screw rod channel part (2871) and is connected with the screw nut adapter piece (2872); the screw rod (287) presses the conical cap (286) on the outer sides of the first half boss (2851) and the second half boss (2852) to enable the first half boss and the second half boss to be buckled to form the conical boss (285).

6. The folder according to claim 5, wherein the inside of said nut adaptor (2872) is further provided with a nut (288) in threaded connection with said threaded rod (287).

7. The folder according to claim 1, characterized in that it is arranged in a foldable undercarriage (2) of an unmanned aerial vehicle, said foldable undercarriage (2) comprising a first folding bracket (20) located on one side of the fuselage (1) and a second folding bracket (30) corresponding to the first folding bracket (20) located on the other side of the fuselage (1), two tie rods (27) being connected between said first folding bracket (20) and said second folding bracket (30); the first folding bracket (20) can be folded towards the second folding bracket (30) by the folder arranged therein to a state parallel to the pull rod (27); the second folding support (30) can be folded by the folder arranged therein toward the first folding support (20) into a state parallel to the tie rod (27).

8. The folder according to claim 7, characterized in that said first folding bracket (20) is folded next to said tie-rod (27); the second folding support (30) is adjacent to the first folding support (20) after being folded, and the first folding support (20) is clamped between the second folding support (30) and the pull rod (27).

9. The folder according to claim 1, characterized in that it is provided in a foldable cantilever system (3) of a drone, said foldable cantilever system (3) comprising four first cantilevers (31) projecting obliquely outwards from the head and the tail of the fuselage (1), and two second cantilevers (32) projecting outwards from the middle of the fuselage (1); the two first cantilevers (31) located on the same side of the fuselage (1) can be folded against one another by means of the folder provided therein.

10. The folder according to claim 9, wherein said second cantilever (32) is divided into a rear arm portion (131) and a front arm portion (132) by a folder disposed therein; the front arm part (132) can be folded by the folder to close the rear arm part (131), the rear arm part (131) can be folded by the other folder to close the side wall of the machine body (1), and the front arm part (132) is clamped between the rear arm part (131) and the side wall of the machine body (1).

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