UTO duct vertical unmanned aerial vehicle

Abstract

The invention relates to a UTO duct vertical unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, and the UTO duct vertical unmanned aerial vehicle comprises a flight module with a vehicle body and an undercarriage connected to the vehicle body. The undercarriage is composed of a first connecting base, a supporting assembly, a bidirectional driving assembly and the like, the supporting assembly achieves multi-direction buffering through a main plate, supporting blocks distributed in a matrix mode and a first elastic piece, and the bidirectional driving assembly drives a screw to rotate through a double-head motor and is matched with an adapter to achieve back-and-forth sliding of the main plate in the second direction; and meanwhile, a first telescopic rod, a second telescopic rod, a second elastic piece and a lifting assembly are arranged to enhance the structural stability and adaptability. The technical effect of optimizing the takeoff and landing stability of the unmanned aerial vehicle is achieved.

Description

Technical Field

[0001] The present application relates to the field of UAVs, and in particular to a UTO ducted vertical take-off UAV. Background Art

[0002] UAV technology has developed rapidly in recent years, especially in the fields of logistics distribution, aerial photography and military reconnaissance. As a special type of UAV, the ducted vertical take-off UAV has the ability to take off and land vertically, which greatly improves the flexibility and adaptability of operations. This type of UAV can achieve efficient take-off and landing in a small space through a special aerodynamic layout and power system design, and has good stability and control performance. However, in practical applications, the safety of UAV take-off and landing has gradually become prominent, especially the stability in complex terrain environments has become a technical problem that needs to be solved urgently. In order to ensure the safety of take-off and landing of UAVs on uneven terrain, the existing technology usually adopts a semi-arc landing gear, which opens downward and can be supported on the ground at both ends. However, the landing gear design in the existing technology still has obvious defects when dealing with complex terrain. Although the traditional semi-arc landing gear has a simple structure, it is difficult to provide sufficient support stability on uneven ground, which can easily cause the UAV to tilt or even overturn, affecting flight safety. Therefore, how to design a UAV that can maintain stable support on uneven terrain has become a key technical problem that needs to be solved urgently. Summary of the invention

[0003] In order to maintain stable support on uneven terrain, the present application provides a UTO ducted vertical take-off drone.

[0004] The UTO ducted vertical take-off drone provided in this application adopts the following technical solution: A UTO ducted vertical take-off unmanned aerial vehicle, comprising: a flight module having a body; and, A landing gear is connected to the fuselage; the landing gear comprises: A first connection seat, the first connection seat is connected to the body; and Two support assemblies, the support assemblies are connected to the first connecting seat, and the two support assemblies are symmetrically arranged on both sides of the machine body; the support assemblies include: A mainboard, the mainboard being connected to the body; A plurality of support blocks; in a first direction, the support blocks are located on a side of the mainboard away from the body; the plurality of support blocks are distributed in a matrix on a plane perpendicular to the first direction; and, A plurality of first elastic members, each of the support blocks is correspondingly connected to the main board through the first elastic member; the expansion and contraction direction of the first elastic member is parallel to the first direction.

[0005] By adopting the above technical solution, the landing gear design of the UTO ducted vertical take-off drone can effectively solve the problem in the prior art that drones are difficult to stand firmly on uneven terrain. The specific effects are as follows: by symmetrically arranging support components on both sides of the fuselage, each support component includes a main board, multiple support blocks and a first elastic member, so that when the drone lands, even if the ground is uneven, it can achieve multi-point support through the cooperation of the support blocks and the first elastic member, thereby improving stability. In addition, the support blocks are distributed in a matrix on a plane perpendicular to the height direction of the fuselage, which further enhances the uniformity and adaptability of the support, ensuring that the drone can stand stably in various complex terrains.

[0006] Optionally, the landing gear further includes a bidirectional drive assembly, and the bidirectional drive assembly includes: a second connection socket, the second connection socket being connected between the first connection socket and the mainboard; A double-headed motor, the double-headed motor is fixedly connected to the second connecting seat; Two screws, the screws are parallel to the second direction, and the two ends of the double-headed motor are respectively connected to a corresponding screw to drive the screws to rotate around the screw axis; and, Two adapters, each of the screw rods is connected to the main board via one of the adapter rods, and the screw rods are threadedly connected to the adapter rods; The mainboard is connected to the body by reciprocating sliding along the second direction.

[0007] By adopting the above technical solution, the UAV can achieve automatic adjustment of the landing gear during take-off and landing. Specifically, the setting of the two-way drive assembly enables the two main boards to move relative to each other in the second direction, thereby adjusting the support range of the landing gear according to actual needs. The double-headed motor drives the screw to rotate, and combined with the threaded connection of the adapter, the accuracy and stability of the main board movement are ensured. This design not only improves the adaptability of the UAV on uneven terrain, but also can retract the landing gear in flight to reduce wind resistance, significantly improving the overall performance and operational flexibility of the UAV.

[0008] Optionally, the adapter includes: A vertical plate, the vertical plate is fixedly connected to the main board and is located at one end where the two main boards are close to each other; and A sleeve, the sleeve is fixedly connected to the vertical plate; the sleeve is parallel to the second direction, one end of the sleeve is passed through the vertical plate, and the other end extends to a side of the vertical plate close to the double-headed motor; The screw rod is passed through the sleeve and is threadedly connected with the sleeve.

[0009] By adopting the above technical solution, the setting of the vertical plate and the sleeve makes the connection between the screw and the main board more stable, while extending the distance between the vertical plate and the double-headed motor, thereby increasing the maximum spacing between the two main boards and improving the standing stability of the machine body.

[0010] Optionally, the support assembly further includes: A first telescopic rod, one end of which is hinged to the vertical plate around a first axis, and the other end of which is hinged to the first connecting seat around a second axis; the first axis and the second axis are both parallel to the third direction.

[0011] By adopting the above technical solution, the setting of the first telescopic rod can guide and limit the movement of the mainboard along the second direction, ensuring that the mainboard remains stable during movement and avoiding displacement due to uneven force or external interference; at the same time, the hinged design of the first telescopic rod enables it to adapt to the posture changes of the mainboard in different positions.

[0012] Optionally, the landing gear also includes: a second telescopic rod, wherein a telescopic direction of the second telescopic rod is parallel to the second direction; One end of the second telescopic rod is fixedly connected to the first connecting seat, and the other end is fixedly connected to the second connecting seat.

[0013] By adopting the above technical solution, the second telescopic rod can support and guide the overall structure of the landing gear. Specifically, the second telescopic rod is connected between the first connecting seat and the second connecting seat, and its telescopic direction is parallel to the second direction, so as to provide a stable guiding path when the main board moves along the second direction, and avoid the main board from being offset or stuck during the movement; the second telescopic rod, the first telescopic rod, and the main board that can move along the second direction can form triangles of different sizes, which can be suitable for the size requirements of different scenes.

[0014] Optionally, the landing gear further includes a second elastic member, the second elastic member is connected between the first connecting seat and the second connecting seat; the extension direction of the second elastic member is parallel to the first direction; When the second telescopic rod is in the shortest posture, the second elastic member is in a posture capable of recovering its deformation and has a force capable of driving the second telescopic rod to move from the shortest posture to the longest posture.

[0015] By adopting the above technical solution, the presence of the second elastic member can buffer external impact force and improve the shock absorption performance of the landing gear.

[0016] Optionally, the landing gear further includes two lifting assemblies, and each of the screw rods is connected to a corresponding lifting assembly; the lifting assembly includes: a winding wheel, the winding wheel being coaxially fixedly connected to the screw rod; and, A pulling rope, one end of which is fixedly connected to the winding wheel, and the other end of which is fixedly connected to the first connecting seat.

[0017] By adopting the above technical solution, the lifting assembly can adjust the posture of the second telescopic rod. Specifically, the winding wheel is coaxially fixed to the screw rod, and when the screw rod rotates, the winding wheel can be synchronously driven to rotate, thereby realizing the winding or release of the lifting rope. When the lifting rope is wound, the second telescopic rod is adjusted from the longest posture to the shortest posture; when the lifting rope is released, the second telescopic rod is adjusted from the shortest posture to the longest posture. This design can not only effectively control the overall height of the landing gear, but also can flexibly switch between the flight posture and the landing posture, thereby improving the stability and adaptability of the UAV.

[0018] Optionally, an annular winding groove is provided on the outer peripheral wall of the winding wheel, and the winding groove is used to accommodate the pulling rope.

[0019] By adopting the above technical solution, the annular winding groove opened on the outer peripheral wall of the winding wheel can effectively accommodate the pulling rope, preventing the pulling rope from deviating or detaching from the winding wheel during the winding process, thereby improving the stability of the winding process.

[0020] Optionally, a wire hole for the pulling rope to pass through is formed on the second connecting seat, and the pulling rope is passed through the wire hole.

[0021] By adopting the above technical solution, the setting of the wire hole can prevent the pulling rope from being deflected or entangled during the winding or releasing process, ensuring that the pulling rope passes through the second connecting seat smoothly, thereby improving the reliability of the landing gear during the adjustment process.

[0022] Optionally, the opening of the wire hole is provided with a rounded corner.

[0023] By adopting the above technical solution, the rounded corners at the opening of the wire hole can effectively reduce the wear of the pulling rope during movement, thereby increasing the service life of the pulling rope and the reliability of the system.

[0024] In summary, the present application includes at least one of the following beneficial technical effects: 1. By providing a plurality of support blocks and a first elastic member, the landing gear can adapt to the uneven terrain and improve the support stability of the UAV; 2. The bidirectional drive assembly can drive the two main boards to move in opposite directions, thereby reducing the landing gear area in the flying posture to reduce wind resistance, and increasing the support area in the landing posture to improve stability; 3. The cooperation between the second elastic member and the second telescopic rod can provide a buffer force when the UAV lands, and at the same time ensure that the landing gear automatically adjusts to the longest posture, further enhancing the supporting effect; BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 It is a schematic diagram of the overall structure of an embodiment of the present application; Figure 2 is a schematic diagram of the structure of the support assembly in an embodiment of the present application; Figure 3 yes Figure 2 A magnified view of part A; Figure 4 It is a structural schematic diagram of a bidirectional drive component in an embodiment of the present application.

[0025] Explanation of the reference numerals in the accompanying drawings: 1. flight module; 11. fuselage; 12. wing; 13. lift ducted fan; 14. propulsion propeller; 15. horizontal tail; 151. connecting rod; 16. unidirectional vector ducted fan; 17. vertical tail; 2. first connecting seat; 3. support assembly; 31. main board; 32. support block; 33. first elastic member; 34. first telescopic rod; 4. two-way drive assembly; 41. second connecting seat; 411. cross plate; 412. side plate; 413. wire hole; 414. fillet; 42. double-headed motor; 43. screw; 44. adapter; 441. vertical plate; 442. sleeve; 5. second telescopic rod; 6. second elastic member; 7. lifting assembly; 71. winding wheel; 711. winding groove; 72. lifting rope. DETAILED DESCRIPTION

[0026] The following is combined with Figure 1-4 The present application is further described in detail. For ease of description, the present application introduces directional words such as a first direction, a second direction, and a third direction to form a three-dimensional reference direction. The directional words used, such as "a first direction, a second direction, and a third direction", can be specifically shown with reference to the figure, where X represents the first direction, Y represents the second direction, and Z represents the third direction, and the first direction, the second direction, and the third direction are perpendicular to each other.

[0027] The present application embodiment discloses a UTO ducted vertical take-off drone. Figure 1The UTO ducted vertical take-off drone includes a flight module 1 with a body 11 and a landing gear. For the convenience of description, the first direction in the present disclosure is the height direction of the body 11, the second direction is the width direction of the body 11, and the third direction is the length direction of the body 11; the flight module 1 also includes wings 12, and the wings 12 are symmetrically arranged on both sides of the body 11. A lift ducted fan 13 is connected to the end of the wing 12 away from the body 11, and the lift ducted fan 13 is used to provide lift during vertical take-off and landing; a propulsion propeller 14 is connected to the tail of the body 11, and the propulsion propeller 14 is used to lift Provide the thrust required for level flight; a horizontal tail 15 is also provided at the rear end of the fuselage 11, and the horizontal tail 15 is fixedly connected to the rear end of the fuselage 11 by a connecting rod 151; a unidirectional vector ducted fan 16 is embedded in the horizontal tail 15, and the unidirectional vector ducted fan 16 is used to provide the head-up and head-down moments required for the longitudinal pitch during the vertical take-off and landing stage; in the second direction, the vector ducted fan is located in the middle of the horizontal tail 15; in addition, at both ends of the second direction, a vertical tail 17 is provided at each end of the horizontal tail 15, that is, in the second direction, the vector ducted fan is located between the two vertical tails 17.

[0028] Reference Figure 1 , Figure 2 and Figure 3 The landing gear is connected to the body 11 so as to allow the body 11 to stand on the ground. In the present disclosure, two landing gears are provided, and the two landing gears are spaced apart in the third direction. The landing gear includes a first connecting seat 2, two supporting assemblies 3 and a bidirectional driving assembly 4. The first connecting seat 2 is fixedly connected to the bottom of the body 11, the support assembly 3 is connected to the first connecting seat 2, and the two support assemblies 3 are symmetrically arranged on both sides of the body 11. The support assembly 3 includes a main board 31, a plurality of support blocks 32 and a plurality of first elastic members 33; the main board 31 is directly or indirectly mounted on the body 11. In the present disclosure, the main board 31 is indirectly mounted on the body 11 through the bidirectional driving assembly 4; the main board 31 is perpendicular to the first direction, and the main board 31 is located below the body 11. In the first direction, the support block 32 is located on the side of the main board 31 away from the body 11; the plurality of support blocks 32 are distributed in a matrix on a plane perpendicular to the first direction, and each support block 32 is connected to the main board 31 through a corresponding first elastic member 33. The first elastic member 33 in the present disclosure is a spring, and the extension direction of the first elastic member 33 is parallel to the first direction; when the main board 31 falls on the ground, if the ground is uneven, the support blocks 32 at different positions can support the main board 31, which has higher stability compared to landing on a large area.

[0029] Reference Figure 2 , Figure 3 and Figure 4The bidirectional driving assembly 4 is used to drive the two main boards 31 to move in opposite directions in the second direction. The bidirectional driving assembly 4 includes a second connecting seat 41, a double-headed motor 42, two screws 43 and two adapters 44. The connecting seat is connected to the first connecting seat 2; The second connection seat 41 is located directly below the machine body 11, and includes a transverse plate 411 and two side plates 412 fixedly connected to both ends of the transverse plate 411, so that the second connection seat 41 forms a concave shape, and the opening end of the concave shape faces the side away from the machine body 11, and the double-headed motor 42 is located in the groove of the connection seat, and the double-headed motor 42 is fixedly connected to the transverse plate 411 in the second connection seat 41; The screw 43 is parallel to the second direction, and the two ends of the double-headed screw 43 are respectively coaxially fixedly connected with a screw 43, so that the double-headed motor 42 drives the screw 43 to rotate around the axis of the screw 43 itself; each screw 43 is respectively connected to the main board 31 through an adapter 44, and the screw 43 is threadedly connected to the adapter 44; the main board 31 can move in the second direction, so in the process of driving the screw 43 to rotate, under the action of the screw 43 and the adapter 44, the main board 31 can be driven to move in the second direction; about the rotation direction of the screw 43 and the rotation direction of the screw 43, it is based on the adaptation of the two main boards 31 to be able to move in opposite directions, which is a conventional setting in the field, and the present application will not elaborate on it here, but only gives a setting method, specifically, the two screws 43 in the present disclosure have the same rotation direction and opposite thread rotation directions; The adapter 44 includes a vertical plate 441 fixedly connected to the main board 31 and a sleeve 442 fixedly connected to the vertical plate 441; the vertical plate 441 is arranged perpendicular to the second direction, and is located at one end of the two main boards 31 close to each other, and is located on the side of the main board 31 close to the body 11; the sleeve 442 is parallel to the second direction, and one end of the sleeve 442 is penetrated through the vertical plate 441, and the other end extends to the side of the vertical plate 441 close to the double-headed motor 42; the screw 43 is penetrated through the sleeve 442 along the second direction, and is threadedly connected to the sleeve 442; the screw When 43 is rotating, the main board 31 will move synchronously with the adapter 44; since the sleeve 442 extends toward one side of the double-headed motor 42, when the length of the screw 43 is the same, threading the screw 43 and the sleeve 442 is compared to directly threading the screw 43 and the vertical plate 441. The existence of the sleeve 442 can increase the distance between the vertical plate 441 and the double-headed motor 42. The longer the distance between the two vertical plates 441, that is, the larger the distance between the two main boards 31, the more stably the body 11 will stand on the ground.

[0030] Reference Figure 2 , Figure 3 and Figure 4In order to guide the movement of the main board 31 along the second direction, the support assembly 3 further includes a first telescopic rod 34, one end of the first telescopic rod 34 is hinged to the vertical plate 441 around the first axis, and the other end is hinged to the first connecting seat 2 around the second axis; the first axis and the second axis are parallel to the third direction, and the telescopic direction of the first telescopic rod 34 is perpendicular to the third direction, so that the first telescopic rod 34 can guide the main board 31 to move on a plane perpendicular to the third direction; The landing gear also includes a second telescopic rod 5 and a second elastic member 6. The telescopic direction of the second telescopic rod 5 is parallel to the second direction. One end of the second telescopic rod 5 is fixedly connected to the first connecting seat 2, and the other end is fixedly connected to the second connecting seat 41. Under the guidance of the first telescopic rod 34 and the second telescopic rod 5, a guide is provided for the movement of the main board 31 along the second direction, so that the second telescopic rod 5 can be adjusted between the longest posture and the shortest posture. The second elastic member 6 is connected between the first connecting seat 2 and the second connecting seat 41. Specifically, one end of the second elastic member 6 is fixedly connected to the first connecting seat 2, and the other end is fixedly connected to the second connecting seat 41. The extension direction of the second elastic member 6 is parallel to the first direction. In the present disclosure, the second elastic member 6 is a compression spring. When the second telescopic rod 5 is in the shortest posture, the second elastic member 6 is in a compressed state in which the deformation can be restored, and the second elastic member 6 has a force to drive the second telescopic rod 5 to move from the shortest posture to the longest posture.

[0031] Reference Figure 4 In order to adjust the second telescopic rod 5 from the longest posture to the shortest posture, in some embodiments of the present application, the landing gear also includes two lifting assemblies 7, and each screw 43 is connected to a corresponding lifting assembly 7; the lifting assembly 7 includes a winding wheel 71 and a lifting rope 72; in the present disclosure, the winding wheel 71 is located in the groove formed by the second connecting seat 41, and the winding wheel 71 is coaxially fixedly connected to the screw 43 so that the winding wheel 71 rotates synchronously with the screw 43, and the winding wheel 71 is used to wind the lifting rope 72, and one end of the lifting rope 72 is fixedly connected to the winding wheel 71, and the other end is fixedly connected to the first connecting seat 2; in the process of rotating the winding wheel 71 in different directions, the lifting rope 72 can be wound around the winding wheel 71, or the lifting rope 72 can be peeled off from the winding wheel 71; When the pulling rope 72 is wound around the reel 71, the second telescopic rod 5 is in the shortest posture; During the process of the pulling rope 72 being peeled off from the reel 71, the second telescopic rod 5 is adjusted from the shortest posture to the longest posture; In order to prevent the pulling rope 72 from escaping from the winding wheel 71 , in some embodiments of the present application, an annular winding groove 711 is coaxially formed on the outer peripheral wall of the winding wheel 71 , and the winding groove 711 is used to accommodate the winding wheel 71 .

[0032] In order to make the process of winding up the pulling rope 72 smoother, in some embodiments of the present application, two wire holes 413 for the pulling rope 72 to pass through are opened on the second connecting seat 41. The wire holes 413 in the present disclosure are located on the horizontal plate 411, and a corresponding pulling rope 72 is passed through each wire hole 413. When the pulling rope 72 is located at the center of the wire hole 413, the pulling rope 72 is parallel to the first direction. In order to reduce the wear of the pulling rope 72, rounded corners 414 are provided at the openings at both ends of the wire hole 413.

[0033] The implementation principle of a UTO ducted vertical take-off drone in an embodiment of the present application is as follows: when the aircraft is in a landing posture, the landing gear can support the fuselage 11, and at this time the second elastic member 6 pushes the second telescopic rod 5 to be in a longer posture, and the distance between the two main boards 31 in the second direction is at the maximum distance, and at this time a relatively stable support can be provided for the fuselage 11; when the aircraft is in a flying posture, the double-headed motor 42 drives the two screws 43 to rotate to reduce the distance between the two main boards 31, and as the screw 43 rotates, the pulling rope 72 is wound on the winding wheel 71 to reduce the area of ​​the entire landing gear and reduce wind resistance.

[0034] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. A UTO ducted vertical take-off drone, characterized in that: include: A flight module (1) having a body (11); as well as, A landing gear is connected to the fuselage (11); the landing gear comprises: a first connecting seat (2), the first connecting seat (2) being connected to the machine body (11); and Two support assemblies (3), the support assemblies (3) being connected to the first connection seat (2), and the two support assemblies (3) being symmetrically arranged on both sides of the machine body (11); the support assemblies (3) comprising: A main board (31), the main board (31) being connected to the machine body (11); A plurality of support blocks (32); in a first direction, the support blocks (32) are located on a side of the main board (31) away from the machine body (11); the plurality of support blocks (32) are distributed in a matrix on a plane perpendicular to the first direction; and, A plurality of first elastic members (33), each of the support blocks (32) being connected to the main board (31) via the first elastic member (33); the expansion and contraction direction of the first elastic member (33) is parallel to the first direction.

2. A UTO ducted vertical take-off drone according to claim 1, characterized in that: The landing gear further comprises a bidirectional drive assembly (4), wherein the bidirectional drive assembly (4) comprises: A second connecting seat (41), the second connecting seat (41) being connected between the first connecting seat (2) and the main board (31); A double-headed motor (42), the double-headed motor (42) being fixedly connected to the second connecting seat (41); Two screw rods (43), the screw rods (43) are parallel to the second direction, and the two ends of the double-headed motor (42) are respectively connected to a corresponding screw rod (43) to drive the screw rod (43) to rotate around the axis of the screw rod (43); and, Two adapters (44), each of the screw rods (43) is connected to the main board (31) via one of the adapters (44), and the screw rods (43) are threadedly connected to the adapters (44); The main board (31) is connected to the machine body (11) in a reciprocating sliding manner along the second direction.

3. A UTO ducted vertical take-off drone according to claim 2, characterized in that: The adapter (44) comprises: a vertical plate (441), the vertical plate (441) being fixedly connected to the main plate (31) and being located at one end where the two main plates (31) are close to each other; and a sleeve (442), the sleeve (442) being fixedly connected to the vertical plate (441); the sleeve (442) being parallel to the second direction, one end of the sleeve (442) being passed through the vertical plate (441), and the other end of the sleeve (442) extending toward a side of the vertical plate (441) close to the double-headed motor (42); The screw rod (43) is inserted into the sleeve (442) and is threadedly connected to the sleeve (442).

4. A UTO ducted vertical take-off drone according to claim 3, characterized in that: The support assembly (3) further comprises: A first telescopic rod (34), one end of the first telescopic rod (34) is hinged to the vertical plate (441) around a first axis, and the other end of the first telescopic rod (34) is hinged to the first connecting seat (2) around a second axis; the first axis and the second axis are both parallel to the third direction.

5. A UTO ducted vertical take-off drone according to claim 4, characterized in that: The landing gear also includes: A second telescopic rod (5), wherein the telescopic direction of the second telescopic rod (5) is parallel to the second direction; One end of the second telescopic rod (5) is fixedly connected to the first connecting seat (2), and the other end is fixedly connected to the second connecting seat (41).

6. A UTO ducted vertical take-off drone according to claim 5, characterized in that: The landing gear further comprises a second elastic member (6), wherein the second elastic member (6) is connected between the first connecting seat (2) and the second connecting seat (41); the extension direction of the second elastic member (6) is parallel to the first direction; When the second telescopic rod (5) is in the shortest posture, the second elastic member (6) is in a posture capable of recovering its deformation and has a force capable of driving the second telescopic rod (5) to move from the shortest posture to the longest posture.

7. A UTO ducted vertical take-off drone according to claim 6, characterized in that: The landing gear further comprises two lifting assemblies (7), each of the screw rods (43) being connected to a corresponding lifting assembly (7); the lifting assembly (7) comprises: a winding wheel (71), the winding wheel (71) being coaxially fixedly connected to the screw rod (43); and A pulling rope (72), one end of the pulling rope (72) is fixedly connected to the winding wheel (71), and the other end of the pulling rope (72) is fixedly connected to the first connecting seat (2).

8. A UTO ducted vertical take-off drone according to claim 7, characterized in that: An annular winding groove (711) is provided on the outer peripheral wall of the winding wheel (71), and the winding groove (711) is used to accommodate the pulling rope (72).

9. The UTO ducted vertical take-off drone according to claim 7, characterized in that: The second connecting seat (41) is provided with a wire hole (413) for the pulling rope (72) to pass through, and the pulling rope (72) is passed through the wire hole (413).

10. A UTO ducted vertical take-off drone according to claim 9, characterized in that: A rounded corner (414) is provided at the opening of the wire hole (413).

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