Folding unmanned aerial vehicle

Abstract

The invention provides a folding unmanned aerial vehicle. The folding unmanned aerial vehicle comprises a fuselage; the foot stools are respectively connected to at least two opposite side parts of the machine body; wherein the foot stool is provided with a folding structure, when the folding structure is in a first posture, the foot stool is unfolded and protrudes out of the bottom of the fuselage, and when the folding structure is in a second posture, the foot stool is folded and protrudes out of the top of the fuselage. According to the arrangement, the foot stool is connected to the side portion of the machine body and can be folded upwards relative to the machine body, the folded foot stool is not located at the bottom of the machine body, an access hole in the bottom of the machine body cannot be shielded, and supporting of the bottom of the machine body cannot be interfered in the placing and transporting process. Moreover, the foot stool is folded upwards relative to the fuselage, so that the foot stool can protrude out of the top of the fuselage, the size can be reduced, the inverted fuselage can be supported, and the bottom of the fuselage can be overhauled conveniently.

Description

Technical Field

[0001] This application relates to the technical field of flight devices, and particularly to a foldable unmanned aerial vehicle (UAV). Background Art

[0002] With the development of UAVs, large-load UAVs are getting larger and larger. When they reach a certain level, traditional transportation means such as SUVs and trucks are difficult to transport and transfer them. Special transportation tools are required to transport them, which increases the transportation cost and is also easy to damage the UAV during transportation, affecting its flight performance.

[0003] In the prior art, generally, each component of the UAV is disassembled and folded to be stored in a smaller volume. However, in the existing storage methods, the landing gear of the UAV is folded at the bottom of the UAV, which is easy to block the maintenance opening at the bottom of the UAV and make the bottom of the UAV unstable to support, being not conducive to the placement and transportation of the UAV. Summary of the Invention

[0004] In view of this, this application provides a foldable UAV, the landing gear of which is convenient for maintenance and support of the bottom after folding.

[0005] In order to achieve the above object, this application provides the following technical solutions:

[0006] A foldable UAV, comprising:

[0007] A fuselage;

[0008] A plurality of landing gears, respectively connected to at least two opposite sides of the fuselage;

[0009] Wherein, the landing gear has a folding structure. When the folding structure is in the first posture, the landing gear is unfolded and protrudes from the bottom of the fuselage. When the folding structure is in the second posture, the landing gear is folded and protrudes from the top of the fuselage.

[0010] Optionally, it includes:

[0011] A plurality of wing assemblies, respectively detachably connected to two sides of the fuselage;

[0012] Wherein, when the folding structure is in the second posture, the plurality of landing gears and the top of the fuselage enclose an accommodation space for accommodating the plurality of wing assemblies.

[0013] Optionally, it includes:

[0014] A plurality of rotor assemblies, respectively connected to at least two opposite sides of the fuselage through foldable hanging arms, and the rotor assemblies can be folded with the foldable hanging arms on the sides of the fuselage;

[0015] When the folding structure is in the second posture, the rotor assembly and the foldable hanging arm are limited between the tripod and the fuselage.

[0016] Optionally, the folding structure includes:

[0017] A fixing member connected to the side of the fuselage;

[0018] A folding member hinged to the fixing member;

[0019] A limiting member detachably connected between the fixing member and the folding member and capable of restricting relative rotation between the fixing member and the folding member.

[0020] Optionally, a plurality of the limiting members are provided and are respectively connected to both sides of the fixing member and the folding member through pin shafts;

[0021] When the limiting member connects the fixing member and the folding member, the middle part of the pin shaft is disposed in the fixing member or the folding member, and two end parts of the pin shaft are respectively disposed in a plurality of the limiting members.

[0022] Optionally, the tripod includes:

[0023] A fixed rod, one end of which is connected to the side of the fuselage and the other end of which is connected to the fixing member;

[0024] A folding rod, one end of which is connected to the folding member;

[0025] Wherein, the fixed rod is perpendicular to the side of the fuselage, and the folding rod is perpendicular to the fixed rod when the folding structure is in the first posture and the second posture.

[0026] Optionally, the tripod includes a support rod and a plurality of the folding rods, and one ends of the plurality of folding rods far from the folding structure are all connected to the support rod.

[0027] Optionally, the tripod is connected to the side of the fuselage and near the bottom.

[0028] Optionally, the wing assembly and the fuselage are detachably connected through a plugging structure and a locking structure, and the plugging direction of the plugging structure and the locking direction of the locking structure are consistent with the extending direction of the wing assembly.

[0029] Optionally, the plugging structure includes a plurality of plugging rods. When the wing assembly and the fuselage are assembled, the middle part of the plugging rod is disposed in the fuselage, and two end parts of the plugging rod are respectively disposed in two wing assemblies.

[0030] Optionally, when the folding structure is in the second posture, the multiple wing assemblies located in the accommodation space are stacked end to end in a staggered manner and are integrated by a storage member.

[0031] Optionally, on the same side of the fuselage, the folding directions of multiple foldable hanging arms are parallel and form an angle with the extending direction of the fuselage.

[0032] For the foldable drone provided in this application, the landing gear has a folding structure. By adjusting the posture of the folding structure, the landing gear can be unfolded and folded. Among them, the folding structure has a first posture and a second posture. When the folding structure is in the first posture, the landing gear unfolds relative to the fuselage, and at the same time, the landing gear protrudes from the bottom of the fuselage so that the lowest point of the landing gear is lower than the lowest point of the fuselage, and thus the bottom of the fuselage can be supported by the landing gear; when the folding structure is in the second posture, the landing gear folds relative to the fuselage, and at the same time, the landing gear protrudes from the top of the fuselage so that the highest point of the landing gear is higher than the highest point of the fuselage, and thus the top of the fuselage can be supported by the landing gear. With such a setting, the landing gear is connected to the side of the fuselage and can be folded upward relative to the fuselage. The folded landing gear is not at the bottom of the fuselage and will not block the inspection opening at the bottom of the fuselage, and will not interfere with the support at the bottom of the fuselage during placement and transportation. Moreover, by folding the landing gear upward relative to the fuselage, the landing gear can protrude from the top of the fuselage, which can not only reduce the volume but also support the inverted fuselage, facilitating the inspection of the bottom of the fuselage. Description of the Drawings

[0033] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are only the embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained according to the provided drawings.

[0034] Figure 1 It is an unfolded schematic diagram of a foldable drone shown in some embodiments;

[0035] Figure 2 It is a side view of a foldable drone disassembling the wing assembly shown in some embodiments;

[0036] Figure 3 It is a folded perspective view of a foldable drone shown in some embodiments;

[0037] Figure 4 It is a folded side view of a foldable drone shown in some embodiments;

[0038] Figure 5 It is a schematic diagram of a landing gear shown in some embodiments;

[0039] Figure 6 Schematic diagram of the folding structure shown for some embodiments;

[0040] Figure 7 Schematic diagram of the storage of the wing assembly shown for some embodiments.

[0041] In the figure: 1, fuselage; 2, rotor assembly; 3, wing assembly; 4, landing gear; 5, folding structure; 6, hanging arm; 7, storage member; 11, sleeve; 12, first sleeve; 13, hollow hole; 31, second sleeve; 41, fixing rod; 42, folding rod; 43, support rod; 51, fixing member; 52, folding member; 53, limiting member; 54, first ear plate; 55, second ear plate. Detailed implementation manners

[0042] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0043] As Figures 1-7 shown, the embodiments of the present application provide a folding unmanned aerial vehicle, including a fuselage 1 and a landing gear 4. A plurality of landing gears 4 are provided and are respectively connected to at least two opposite sides of the fuselage 1. For example, two, three or four landing gears 4 are provided and are respectively located on two, three or four sides of the fuselage 1. Among them, the two opposite sides of the fuselage 1 are respectively located on the longitudinal two sides of the fuselage 1, that is, the left and right sides of the fuselage 1 during the traveling process. Of course, the landing gear 4 can also be provided on other sides of the fuselage 1. For example, a plurality of landing gears 4 are arranged in a circumferential manner around the fuselage 1, and the plurality of landing gears 4 act on the four sides of the fuselage 1 to facilitate ensuring the stability of the fuselage 1.

[0044] It should be noted that this folding unmanned aerial vehicle can be set as one of a multi-rotor unmanned aerial vehicle, a fixed-wing unmanned aerial vehicle and a compound-wing unmanned aerial vehicle. Here, only the landing gear 4 is limited, and the structure of the folding unmanned aerial vehicle is not specifically limited.

[0045] The tripod 4 has a folding structure 5. By adjusting the posture of the folding structure 5, the tripod 4 can be deployed and folded. Among them, the folding structure 5 has a first posture and a second posture. When the folding structure 5 is in the first posture, the tripod 4 is deployed relative to the fuselage 1, and at the same time, the tripod 4 protrudes from the bottom of the fuselage 1, so that the lowest part of the tripod 4 is lower than the lowest part of the fuselage 1, and thus the bottom of the fuselage 1 can be supported by the tripod 4; when the folding structure 5 is in the second posture, the tripod 4 is folded relative to the fuselage 1, and at the same time, the tripod 4 protrudes from the top of the fuselage 1, so that the highest part of the tripod 4 is higher than the highest part of the fuselage 1, and thus the top of the fuselage 1 can be supported by the tripod 4.

[0046] With such a setting, the tripod 4 is connected to the side of the fuselage 1 and can be folded upward relative to the fuselage 1. The folded tripod 4 is not at the bottom of the fuselage 1 and will not block the maintenance opening at the bottom of the fuselage 1, and will not interfere with the support of the bottom of the fuselage 1 during placement and transportation. Moreover, by folding the tripod 4 upward relative to the fuselage 1, the tripod 4 can protrude from the top of the fuselage 1, which can not only reduce the volume but also support the inverted fuselage 1, facilitating the maintenance of the bottom of the fuselage 1.

[0047] Among them, the tripod 4 is connected to the side of the fuselage 1 and close to the bottom. In this way, when the tripod 4 is deployed relative to the fuselage 1, the part of the tripod 4 protruding from the bottom of the fuselage 1 is relatively large, having a large support height, and has a good support and protection performance for the fuselage 1 when the UAV lands; when the tripod 4 is folded relative to the fuselage 1, the part of the tripod 4 protruding from the top of the fuselage 1 is relatively small, making the folded UAV have a smaller volume and being convenient for storage and transportation.

[0048] In some preferred solutions, the folding structure 5 includes a fixing member 51, a folding member 52, and a limiting member 53. Among them, the fixing member 51 is connected to the fuselage 1, for example, it can be connected to the side of the fuselage 1. Of course, in other solutions, it can also be connected to the bottom of the fuselage 1; the folding member 52 is hinged to the fixing member 51. For example, one end of the fixing member 51 is connected to the fuselage 1 and the other end is hinged to the end of the folding member 52, so that the folding member 52 can rotate relative to the fixing member 51 and the fuselage 1. When the folding member 52 rotates to the first position, the folding structure 5 is deployed and in the first posture, and at this time the tripod 4 is deployed and in the deployed posture. When the folding member 52 rotates to the second position, the folding structure 5 is folded and in the second posture, and at this time the tripod 4 is folded and in the folded posture.

[0049] The limiting member 53 is detachably connected between the fixing member 51 and the folding member 52. For example, the limiting member 53 is connected to the fixing member 51 and the folding member 52 through a detachable structure such as a pin shaft, a screw, or a buckle. When the limiting member 53 is detached from at least one of the fixing member 51 and the folding member 52, the limiting effect of the limiting member 53 between the fixing member 51 and the folding member 52 is lost, and they can rotate relative to each other, thereby enabling the folding structure 5 to be converted between the first posture and the second posture, and enabling the tripod 4 to be converted between the deployed posture and the folded posture. When the limiting member 53 is connected to both the fixing member 51 and the folding member 52 at the same time, the fixing member 51 and the folding member 52 are limited by the limiting member 53 and cannot rotate relative to each other, thereby enabling the folding structure 5 to be maintained in the first posture and the second posture, and enabling the tripod 4 to be maintained in the deployed posture and the folded posture.

[0050] In this way, during the folding process of the folding drone, the tripod 4 is folded through the folding structure 5 and can be maintained in the second posture through the folding structure 5, so that the tripod 4 is maintained in the folded posture, avoiding ineffective deployment when being interfered by external forces, which is beneficial to improving the stability of the folding, placement, and transportation of the folding drone.

[0051] In a further solution, multiple limiting members 53 are provided, that is, the same folding structure 5 has multiple limiting members 53, such as two or four. The multiple limiting members 53 are respectively arranged on both sides of the fixing member 51 and the folding member 52. While the limiting members 53 connect the fixing member 51 and the folding member 52, the force balance on both sides of the fixing member 51 and the folding member 52 can also be improved, thereby improving the stability of the folding structure 5.

[0052] Two end parts of the limiting member 53 are respectively connected to the fixing member 51 and the folding member 52 through pin shafts, that is, at least two pin shafts are provided. When the limiting member 53 connects the fixing member 51 and the folding member 52, one pin shaft penetrates through one end part of the limiting member 53 and the fixing member 51, and the other pin shaft penetrates through the other end part of the limiting member 53 and the folding member 52. In this way, through the way of being penetrated and fixed by the pin shaft, it is convenient to realize the disassembly of the limiting member 53 relative to the fixing member 51 and the folding member 52, which is beneficial to improving the folding efficiency.

[0053] Among them, in the solution where multiple limiting members 53 are provided, when the multiple limiting members 53 connect the fixing member 51 and the folding member 52, the pin shafts sequentially penetrate through the limiting member 53, the fixing member 51 / folding member 52, and the limiting member 53, so that the middle part of the pin shaft penetrates through the fixing member 51 or the folding member 52, and the two end parts of the pin shaft respectively penetrate through the multiple limiting members 53, which is beneficial to ensuring the connection balance of the limiting member 53.

[0054] In some preferred embodiments, a plurality of first ear plates 54 are stacked at the end of the fixing member 51. For example, there are two or three first ear plates 54, and the plurality of first ear plates 54 all protrude from the end face of the fixing member 51 close to the folding member 52. A plurality of second ear plates 55 are stacked at the end of the folding member 52. For example, there are two or three second ear plates 55, and the plurality of second ear plates 55 all protrude from the end face of the folding member 52 close to the fixing member 51. When the fixing member 51 and the folding member 52 are hinged, the plurality of first ear plates 54 and the plurality of second ear plates 55 are staggered, so that a second ear plate 55 is embedded between two adjacent first ear plates 54, and a first ear plate 54 is embedded between two adjacent second ear plates 55. The hinge shaft sequentially passes through and connects the plurality of first ear plates 54 and the plurality of second ear plates 55. By hinging the plurality of first ear plates 54 and the plurality of second ear plates 55, the hinging of the fixing member 51 and the folding member 52 is realized. In this way, the form of stacking and hinging a plurality of ear plates can limit the fixing member 51 and the folding member 52 along the axial direction of the hinge shaft, and can also improve the balance when the fixing member 51 and the folding member 52 rotate relative to each other, making the hinge of the fixing member 51 and the folding member 52 more stable.

[0055] The width of the first ear plate 54 gradually decreases in the direction away from the fixing member 51. For example, the first ear plate 54 is provided with a semicircle, and the straight edge of the first ear plate 54 is connected to the fixing member 51, or the first ear plate 54 is provided as a triangle, and one of the sides of the first ear plate 54 is connected to the fixing member 51. Here, the first ear plate 54 is provided as an isosceles right triangle, and the hypotenuse of the first ear plate 54 is connected to the fixing member 51. Correspondingly, the width of the second ear plate 55 gradually decreases in the direction away from the folding member 52. For example, the second ear plate 55 is provided with a semicircle, and the straight edge of the second ear plate 55 is connected to the folding member 52, or the second ear plate 55 is provided as a triangle, and one of the sides of the second ear plate 55 is connected to the folding member 52. Here, the second ear plate 55 is provided as an isosceles right triangle, and the hypotenuse of the second ear plate 55 is connected to the folding member 52. In this way, through the shape design of the first ear plate 54 and the second ear plate 55, the folding member 52 and the fixing member 51 can have a relatively large rotation angle, that is, a relatively large folding angle, which can adapt to more folding methods and is beneficial to reducing the size of the folded folding UAV.

[0056] The fixing member 51, the folding member 52 and the limiting member 53 are all made of metal materials. Of course, the fixing member 51, the folding member 52 and the limiting member 53 can also be made of other wear-resistant and hard materials, which can make the connection between the limiting member 53 and the fixing member 51 and the folding member 52 more stable and reliable, and can also adapt to multiple rotations and disassembly and assembly, which is beneficial to improving the service life.

[0057] In some preferred embodiments, such as Figure 5 , 6As shown, the tripod 4 includes a fixed rod 41 and a folding rod 42. One end of the fixed rod 41 is connected to the fuselage 1, and the other end is connected to a fixing member 51. One end of the folding rod 42 is connected to a folding member 52. Through the hinge connection between the folding member 52 and the fixing member 51, the hinge connection between the folding rod 42 and the fixed rod 41 is realized. By restricting the rotation of the folding member 52 and the fixing member 51 through a limiting member 53, the rotation of the folding rod 42 and the fixed rod 41 can be restricted. For example, the fixing member 51 is sleeved on the outer periphery of the end of the fixed rod 41 and fixed by screws, and the folding member 52 is sleeved on the outer periphery of the end of the folding rod 42 and fixed by bolts.

[0058] When the folding structure 5 is in the first posture and the second posture, the tripod 4 is in the unfolded posture and the folded posture. The limiting member 53 connects the fixing member 51 and the folding member 52. The folding rod 42 and the fixed rod 41 are perpendicular, and at the same time, the fixed rod 41 is perpendicular to the side of the fuselage 1. In this way, when the tripod 4 is in the unfolded posture and the folded posture, the angles formed by the folding rod 42 and the fixed rod 41 are the same, and the folding rod 42 is parallel to the side of the fuselage 1, so that the tripod 4 can support the fuselage 1 in the vertical direction, and the support effect is stable and reliable. Moreover, the connection position of the limiting member 53 on the fixing member 51 and the folding member 52 remains unchanged, which is convenient for the disassembly and assembly of the limiting member 53.

[0059] Among them, the tripod 4 includes a support rod 43. There are multiple folding rods 42, fixed rods 41 and folding structures 5 arranged in one-to-one correspondence and arranged along the extending direction of the fuselage 1. The extending direction of the support rod 43 is the same as the extending direction of the fuselage 1. One ends of the multiple folding rods 42 far from the folding structure 5 are connected to the support rod 43. In this way, through one support rod 43, multiple folding rods 42, multiple fixed rods 41 and multiple folding structures 5 can be connected into one body, which is beneficial to improving the structural stability and the support area.

[0060] In some embodiments, the folding unmanned aerial vehicle includes a plurality of wing assemblies 3. The plurality of wing assemblies 3 are respectively detachably connected to two sides of the fuselage 1. Here, the two sides of the fuselage 1 are respectively located on the longitudinal two sides of the fuselage 1, that is, the left and right sides of the fuselage 1 during the traveling process. For example, the extending direction of the fuselage 1 is the traveling direction, the extending direction of the fuselage 1 is the longitudinal direction, and the longitudinal two sides of the fuselage 1 are the two sides of the extending direction of the fuselage 1. Specifically, two or four wing assemblies 3 can be provided.

[0061] It should be noted that the folding unmanned aerial vehicle in this embodiment can be set as a fixed-wing unmanned aerial vehicle or a compound-wing unmanned aerial vehicle.

[0062] When the folding structure 5 is in the second posture, when the plurality of tripod legs 4 are folded, they all protrude from the top of the fuselage 1, and an accommodation space is formed between the plurality of tripod legs 4 and the top of the fuselage 1. This accommodation space is used to accommodate the plurality of wing assemblies 3 after disassembly. In this way, placing the disassembled wing assemblies 3 in the accommodation space surrounded by the plurality of tripod legs 4 and the fuselage 1 can not only make the folded drone have better integrity, but also avoid the loss and damage caused by placing the wing assemblies 3 independently.

[0063] Furthermore, after the folding drone is folded, the plurality of wing assemblies 3 located in the accommodation space are stacked and staggered at the head and tail. As Figure 7 shown, in two adjacent wing assemblies 3, the proximal end of one wing assembly 3 is opposite to the distal end of the other wing assembly 3. In this way, the volume when the plurality of wing assemblies 3 are stacked and stored can be reduced, and the plurality of wing assemblies 3 have a relatively regular outer contour shape.

[0064] Moreover, the plurality of wing assemblies 3 are integrated by the storage member 7, which can improve the integrity of the stacked placement of the plurality of wing assemblies 3 and prevent individual wing assemblies 3 from shaking. For example, the storage member 7 is set as a square foam or a flexible plastic part. A plurality of through holes for the plurality of wing assemblies 3 to pass through respectively are arranged inside the storage member 7. There are a plurality of storage members 7, which are arranged along the extending direction of the wing assembly 3. Specifically, the width of the accommodating member is the same as the width of the formed accommodating space, and the accommodating member can be limited by the plurality of tripod legs 4.

[0065] In some preferred solutions, the wing assembly 3 and the fuselage 1 are detachably connected by a plug-in structure and a locking structure, and the plug-in direction of the plug-in structure and the locking direction of the locking structure are the same as the extending direction of the wing assembly 3. During the disassembly and assembly process, when the locking structure is in the unlocked state, the wing assembly 3 can be plugged into the side of the fuselage 1 through the plug-in structure. The plug-in direction is the same as the extending direction of the wing assembly 3 and perpendicular to the side of the fuselage 1, having good plug-in stability; when the locking structure is in the locked state, the locking structure can limit the relative displacement of the wing assembly 3 and the fuselage 1 along the extending direction of the wing assembly 3, so as to keep the plug-in structure in the plugged state and form a stable plug-in connection between the wing assembly 3 and the fuselage 1. In this way, through the cooperation of the plug-in structure and the locking structure, it is beneficial to improve the connection stability between the wing assembly 3 and the fuselage 1, and can also improve the disassembly and assembly efficiency of the wing assembly 3 and the fuselage 1.

[0066] The plug-in structure includes a plurality of plug-in rods, for example, the number of the plug-in rods is two, three or four. When the wing assembly 3 is assembled with the fuselage 1 assembly, the middle portion of the plug-in rod is inserted into the fuselage 1, and the two ends of the plug-in rod are respectively inserted into the two wing assemblies 3. In this way, the plug-in of the two wing assemblies 3 relative to the fuselage 1 is realized by the same plug-in rod, and the ends of the plug-in rod are limited by the two wing assemblies 3. The structure is simple and is conducive to improving the plug-in stability. Among them, the plug-in rod extends into the interior of the wing assembly 3 and the fuselage 1, which can form the internal skeleton of the wing assembly 3 and the fuselage 1, and further improve the structural stability of the wing assembly 3 and the fuselage 1. Moreover, by plugging in multiple plug-in rods, the plug-in strength can be improved and the rotation of the wing assembly 3 and the fuselage 1 can be prevented.

[0067] Among them, Figure 2 , 7 As shown, a first sleeve 12 is provided inside the fuselage 1, and two ports of the first sleeve 12 are respectively located at two opposite sides of the fuselage 1, and a second sleeve 31 is provided inside the wing assembly 3, and the second sleeve 31 extends along the extension direction of the wing assembly 3. During the assembly of the wing assembly 3 and the fuselage 1, the plug-in rod is first plugged into the first sleeve 12, and the two ends of the plug-in rod are respectively exposed at the two sides of the fuselage 1, and then the plug-in rod is plugged into the second sleeve 31, and finally locked and limited by the lock structure. In this way, the plug-in rod can be guided and limited by the first sleeve 12 and the second sleeve 31, so as to prevent the plug-in rod from damaging the internal parts of the wing assembly 3 and the fuselage 1.

[0068] It should be noted that the inner diameters of the first sleeve 12 and the second sleeve 31 match the outer diameters of the plug-in rod, so that the plug-in rod is not prone to axial sliding and radial shaking when plugged into the first sleeve 12 and the second sleeve 31 .

[0069] In the specific scheme, the plug-in rod is set as a carbon tube formed by a braided pultrusion process. The carbon tube formed by this process only uses carbon fiber yarn and resin, does not require manual rolling, has low production cost, light weight, and high stiffness and strength. In this way, the plug-in rod has the characteristics of high strength, low cost, and light weight, which is conducive to improving the carrying capacity of the drone and increasing the range.

[0070] In some preferred embodiments, multiple locking structures are provided and distributed around the circumference of the wing assembly 3, so that the multiple locking structures can be used to lock and connect at multiple positions on the circumference of the wing assembly 3, thereby improving the connection strength between the wing assembly 3 and the fuselage 1. For example, the locking structures are provided on the outer shell of the wing assembly 3 and the outer shell of the fuselage 1, and multiple locking structures can improve the sealing of the outer shell connection.

[0071] like Figure 2As shown, a sleeve 11 is provided on the side of the fuselage 1. The inner peripheral surface profile of the sleeve 11 is consistent with the outer peripheral surface profile of the insertion end of the wing assembly 3. When the wing assembly 3 and the fuselage 1 are assembled by inserting, the sleeve 11 is sleeved on the outer periphery of the wing assembly 3, so that the inner peripheral surface of the sleeve 11 fits the outer peripheral surface of the wing assembly 3, which is beneficial to improving the sealing performance of the connection. Moreover, a locking structure is provided between the sleeve 11 and the wing assembly 3. Through the locking of the locking structure, the wing assembly 3 and the sleeve 11 can be locked, further improving the sealing performance of the connection between the wing assembly 3 and the sleeve 11.

[0072] A plurality of hollow holes 13 are provided on the side of the fuselage 1. The plurality of hollow holes 13 are all provided inside the sleeve 11. In this way, the design of the hollow holes 13 can reduce the weight of the fuselage 1 and form a reinforcing rib to strengthen the strength of the fuselage 1. Correspondingly, the port of the first sleeve 12 is also provided inside the sleeve 11.

[0073] In some embodiments, the folding unmanned aerial vehicle includes a plurality of rotor assemblies 2. The plurality of rotor assemblies 2 are respectively connected to at least two opposite sides of the fuselage 1. For example, the plurality of rotor assemblies 2 are arranged circumferentially around the fuselage 1. When the rotor assemblies 2 are operating, the plurality of rotor assemblies 2 act on the four sides of the fuselage 1 to facilitate ensuring the stability of the fuselage 1. Here, the rotor assemblies 2 can be provided with three, four, five or six. Alternatively, the rotor assemblies 2 are provided with an even number, such as four, six or eight. The rotor assemblies 2 are mirror-symmetrically arranged on two sides of the fuselage 1. During the traveling process of the fuselage 1, the number of rotor assemblies 2 on the left and right sides of the fuselage 1 is equal and symmetrically arranged, which can keep the fuselage 1 in good balance performance in the left-right direction and improve the flight speed and range.

[0074] It should be noted that the folding unmanned aerial vehicle in this embodiment can be set as a multi-rotor unmanned aerial vehicle or a compound-wing unmanned aerial vehicle. When set as a compound-wing unmanned aerial vehicle, the plurality of rotor assemblies 2 are mirror-symmetrically arranged on two sides of the fuselage 1, and the wing assembly 3 is arranged between two adjacent rotor assemblies 2, so that the wing assembly 3 is close to the middle of the fuselage 1, which can keep the fuselage 1 in good balance performance in the front-back direction. In a specific solution, there are four rotor assemblies 2 and two wing assemblies 3. Two rotor assemblies 2 and one wing assembly 3 are respectively provided on two opposite sides of the fuselage 1, and the wing assembly 3 is located at a position between the two rotor assemblies 2. In this way, the structure is simple and reliable, easy to process and manufacture, and has a low cost.

[0075] Among them, the rotor assembly 2 is connected to the side of the fuselage 1 through a foldable hanging arm 6. The foldable hanging arm 6 is set as a foldable rod-shaped structure. When the foldable hanging arm 6 is unfolded, it is in a strip shape. When the foldable hanging arm 6 is folded, it is in an L shape, and the rotor assembly 2 is folded with the foldable hanging arm 6 on the side of the fuselage 1. Moreover, when the folding structure 5 is in the second posture, the landing gear 4 is folded relative to the fuselage 1 and is spaced from the side of the fuselage 1, thereby limiting the rotor assembly 2 and the foldable hanging arm 6 between the landing gear 4 and the side of the fuselage 1. In this way, the landing gear 4 can be kept in a folded state through the folding structure 5. At this time, the rotor assembly 2 and the foldable hanging arm 6 are limited between the landing gear 4 and the side of the fuselage 1. The folding of the landing gear 4 forms a limit on the rotor assembly 2 and the foldable hanging arm 6, which is beneficial to improving the stability and integrity of the folded folding drone, and is convenient for transportation and storage.

[0076] Furthermore, on the same side of the fuselage 1, the folding directions of multiple foldable hanging arms 6 are parallel, and the folding direction of the foldable hanging arm 6 forms an angle with the extending direction of the fuselage 1. As Figure 3 , 4 shown, when the rotor assembly 2 is folded with the foldable hanging arm 6, the adjacent rotor assembly 2 and foldable hanging arm 6 are arranged in a staggered manner, and both are adjacent to the side of the fuselage 1. In this way, it is beneficial to reduce the volume of the folded folding drone, make the outer contour shape of the folded one neat, and is convenient for storage and transportation.

[0077] It should be noted that the "parallel" in this application means that one direction is parallel to another direction, but it is not limited to the absolute parallelism of the two. For example, one is close to parallel to the other, and here it is defined that the included angle of being close to parallel is less than 2 degrees. The "perpendicular" in this article means that one direction is perpendicular to another direction, but it is not limited to the absolute perpendicularity of the two. For example, one is close to perpendicular to the other, and here it is defined that the included angle of being close to perpendicular is less than 92 degrees and greater than 88 degrees.

[0078] The basic principle of this application has been described above in combination with specific embodiments. However, it should be pointed out that the advantages, advantages, effects, etc. mentioned in this application are only examples and not limitations. It cannot be considered that these advantages, advantages, effects, etc. are essential for each embodiment of this application. In addition, the above-disclosed specific details are only for the purpose of illustration and easy understanding, rather than limitations. The above details do not limit this application to necessarily adopt the above specific details to implement.

[0079] The block diagrams of the devices, apparatuses, equipment, and systems involved in the present application are only illustrative examples and are not intended to require or imply that they must be connected, arranged, and configured in the manner shown in the block diagrams. As those skilled in the art will recognize, these devices, apparatuses, equipment, and systems can be connected, arranged, and configured in any manner. Words such as "including", "comprising", "having", etc. are open-ended terms, meaning "including but not limited to", and can be used interchangeably with each other. The words "or" and "and" used herein refer to the phrase "and / or", and can be used interchangeably with it, unless the context clearly indicates otherwise. The word "such as" used herein refers to the phrase "such as but not limited to", and can be used interchangeably with it.

[0080] It should also be noted that in the devices, equipment, and methods of the present application, each component or each step can be decomposed and / or recombined. These decompositions and / or recombinations should be regarded as equivalent solutions of the present application.

[0081] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present application. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein can be applied to other aspects without departing from the scope of the present application. Therefore, the present application is not intended to be limited to the aspects shown herein, but rather to the broadest scope consistent with the principles and novel features disclosed herein.

[0082] It should be understood that the qualifiers "first", "second", "third", "fourth", "fifth", and "sixth" used in the description of the embodiments of the present application are only for more clearly elaborating the technical solutions and cannot be used to limit the protection scope of the present application.

[0083] The above description has been given for purposes of illustration and description. In addition, this description is not intended to limit the embodiments of the present application to the forms disclosed herein. Although multiple example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations thereof.

Claims

1. A foldable drone, characterized in that, Comprising: Airframe; A plurality of legs, respectively connected to at least two opposite sides of the airframe; Wherein, the leg has a folding structure. When the folding structure is in the first posture, the leg is unfolded and protrudes from the bottom of the airframe. When the folding structure is in the second posture, the leg is folded and protrudes from the top of the airframe.

2. The foldable drone according to claim 1, wherein, Comprising: A plurality of wing assemblies, respectively detachably connected to two sides of the airframe; Wherein, when the folding structure is in the second posture, the plurality of legs and the top of the airframe enclose an accommodation space for accommodating the plurality of wing assemblies.

3. The foldable drone according to claim 1, wherein Comprising: A plurality of rotor assemblies, respectively connected to at least two opposite sides of the airframe through foldable hanging arms, and the rotor assemblies can be folded with the foldable hanging arms on the side of the airframe; Wherein, when the folding structure is in the second posture, the rotor assemblies and the foldable hanging arms are limited between the legs and the airframe.

4. The foldable drone according to claim 1, wherein The folding structure includes: A fixing member, connected to the side of the airframe; A folding member, hinged to the fixing member; A limiting member, detachably connected between the fixing member and the folding member, and capable of restricting the relative rotation of the fixing member and the folding member.

5. The foldable drone according to claim 4, characterized in that, A plurality of the limiting members are provided and are respectively connected to both sides of the fixing member and the folding member through pin shafts; When the limiting member connects the fixing member and the folding member, the middle part of the pin shaft is inserted into the fixing member or the folding member, and the two end parts of the pin shaft are respectively inserted into a plurality of the limiting members.

6. The foldable drone according to claim 4, wherein, The leg includes: A fixed rod, one end of which is connected to the side of the airframe and the other end is connected to the fixing member; A folding rod, one end of which is connected to the folding member; Wherein, the fixed rod is perpendicular to the side of the airframe, and the folding rod is perpendicular to the fixed rod when the folding structure is in the first posture and the second posture.

7. The foldable drone according to claim 6, wherein The leg includes a support rod and a plurality of the folding rods, and one ends of the plurality of folding rods far from the folding structure are all connected to the support rod.

8. The foldable drone according to claim 1, wherein, The leg is connected to the side of the airframe and close to the bottom position.

9. The foldable drone according to claim 2, wherein The wing assembly and the airframe are detachably connected through a plugging structure and a locking structure, and the plugging direction of the plugging structure and the locking direction of the locking structure are consistent with the extending direction of the wing assembly.

10. The foldable drone according to claim 9, wherein, The plugging structure includes a plurality of plugging rods. When the wing assembly and the airframe are assembled, the middle part of the plugging rod is inserted into the airframe, and the two end parts of the plugging rod are respectively inserted into two of the wing assemblies.

11. The foldable drone according to claim 2, wherein When the folding structure is in the second posture, the plurality of wing assemblies located in the accommodation space are arranged in a staggered and stacked manner end to end and are integrated through a storage member.

12. The foldable drone according to claim 3, wherein, On the same side of the airframe, the folding directions of the plurality of foldable hanging arms are parallel and form an angle with the extending direction of the airframe.

Images