Multi-rotor unmanned aerial vehicle

Abstract

The utility model discloses a multi-rotor unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. A plurality of arms are radially arranged on the side wall of the unmanned aerial vehicle main body, and at least one embedded mounting groove is formed in the bottom of the unmanned aerial vehicle main body; the rotating shaft is rotatably arranged in the embedded mounting groove; the undercarriage assembly is fixedly connected to the rotating shaft, is used for supporting the unmanned aerial vehicle main body in an unfolded state, and is at least partially accommodated in the embedded mounting groove in a folded state; the driving part is arranged in the unmanned aerial vehicle main body; the two ends of the transmission assembly are connected to the output end of the driving piece and the rotating shaft correspondingly. Therefore, the folded undercarriage assembly is stored through the embedded mounting groove, the overall size of the unmanned aerial vehicle is reduced, the portability and the space utilization rate are improved, and a user does not need to be equipped with a huge storage device. In addition, due to the embedded design, effective protection is provided for the undercarriage assembly, and the risk that the undercarriage assembly is damaged due to collision and extrusion in the transportation and storage process is reduced.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a multi-rotor UAV. Background Technology

[0002] Multi-rotor drones, with their excellent flexibility, are widely used in many fields such as aerial photography, surveying, logistics, and agriculture. Their arms are used to mount rotor motors and propellers to provide flight power, while the landing gear plays a role in supporting and protecting the fuselage during takeoff, landing, and parking. The fixed structure of the arms and landing gear is an important component of the drone.

[0003] However, currently, the arms and landing gear of multi-rotor drones generally adopt traditional fixed structures, which makes the overall size of the drones large. In terms of storage, they occupy a lot of space, requiring users to equip themselves with large storage devices, making them inconvenient to carry. During transportation, they not only increase the space occupied by transport vehicles or aircraft cargo holds, raising transportation costs, but also, due to their large size and many protruding parts, are susceptible to collisions and compression in complex transportation environments, leading to damage, increasing maintenance costs and usage risks. Utility Model Content

[0004] This application provides a multi-rotor unmanned aerial vehicle (UAV) that solves the problems mentioned in the background art.

[0005] This application provides a multi-rotor unmanned aerial vehicle (UAV), comprising: a UAV body with multiple radially arranged arms on its sidewalls and at least one embedded mounting slot at its bottom; a rotating shaft rotatably disposed within the embedded mounting slot; a landing gear assembly fixedly connected to the rotating shaft for supporting the UAV body in an unfolded state and at least partially housed within the embedded mounting slot in a folded state; a drive unit disposed within the UAV body; and a transmission assembly with its two ends respectively connected to the output end of the drive unit and the rotating shaft; wherein the drive unit is configured to drive the rotating shaft to rotate via the transmission assembly, thereby causing the landing gear assembly to switch between an unfolded state supporting the UAV body and a folded state rotated and housed within the embedded mounting slot around the axis of the rotating shaft.

[0006] In one possible implementation, the drive unit is communicatively connected to the UAV flight control system.

[0007] In one possible implementation, the transmission assembly includes: a transmission rod connected to the output end of the drive member; a first gear connected to the end of the transmission rod away from the drive member; and a second gear meshing with the first gear; wherein the rotating shaft is fixedly disposed on the inner wall of the second gear.

[0008] In one possible implementation, the landing gear assembly includes a support rod, a force transmission element, an elastic element, and a buffer pad body;

[0009] The support rod is fixedly connected to the rotating shaft;

[0010] The inner wall of the support rod is provided with an axial groove, and the force transmission element is slidably connected to the axial groove.

[0011] The two ends of the elastic element are respectively connected to the bottom wall inside the support rod and the force transmission element, and are used to provide a restoring elastic force to the force transmission element;

[0012] The main body of the buffer pad is fixedly connected to the end of the force transmission element away from the elastic element, and is located outside the support rod;

[0013] The landing impact force drives the buffer pad body and the force transmission element to move along the axial groove into the support rod, compressing the elastic element to absorb energy.

[0014] In one possible implementation, the bottom of the drone body is provided with a buffer pad groove, and in the folded state, the buffer pad body is embedded in the buffer pad groove.

[0015] In one possible implementation, the embedded mounting groove is provided with a shaft hole, and the rotating shaft is rotatably disposed in the shaft hole.

[0016] In one possible implementation, the multi-rotor drone further includes multiple wing folding mechanisms; the multiple wing folding mechanisms are respectively disposed between the drone body and the corresponding arms; the wing folding mechanisms located on the same side of the drone body are not on the same horizontal plane; each wing folding mechanism includes a rotating base and a locking assembly; the rotating base is fixedly disposed on the side wall of the drone body; the arms are rotatably connected to the rotating base; the locking assembly is disposed between the arms and the rotating base for locking the arms in the unfolded position.

[0017] In one possible implementation, the locking assembly includes a fixing knob, a limiting block, and a fixing block; the fixing knob is movably connected to the arm and the rotating base, and has a limiting block at its bottom; the bottom of the arm has a fixing block; the inner wall of the rotating base has a fixing groove corresponding to the fixing block and a limiting groove corresponding to the limiting block; the fixing knob is configured to, when rotated to a first angle, drive the limiting block, the fixing block, and the limiting groove and fixing groove of the rotating base to connect, thereby locking the arm as it unfolds; when rotated to a second angle, release the connection between the limiting block, the fixing block, and the limiting groove and fixing groove of the rotating base, thereby allowing the arm to rotate and fold.

[0018] In one possible implementation, the inner wall of the rotating seat is provided with a first internal thread, and the inner wall of the machine arm is provided with a second internal thread; the fixing knob is provided with an external thread corresponding to the first internal thread and the second internal thread.

[0019] In one possible implementation, the multi-rotor drone further includes a handle disposed on the top of the drone body; and / or a display screen disposed on the side wall of the drone body; and / or heat dissipation holes disposed on the surface of the drone body; and / or a searchlight disposed on the top of the drone body.

[0020] One or more technical solutions provided in the embodiments of this application have at least the following technical effects:

[0021] The drive unit in this application, located within the drone's main body, transmits power via a transmission assembly to a rotating shaft rotatably mounted within an embedded mounting slot. This, in turn, drives the landing gear assembly, fixedly connected to the rotating shaft, to rotate around the shaft's axis. This allows the landing gear assembly to switch between an extended state supporting the drone's main body and a folded-down state, retracted into the embedded mounting slot. Therefore, by using an embedded mounting slot to store the folded landing gear assembly, this application reduces the overall size of the drone, improving portability and space utilization. Users do not need to equip themselves with bulky storage devices, and it also reduces the space occupied in vehicles or aircraft cargo holds during transportation, lowering transportation costs. Furthermore, the embedded design provides effective protection for the landing gear assembly, reducing the risk of damage from collisions and compression during transportation and storage, lowering maintenance costs and usage risks, and providing a more reliable and convenient solution for the widespread application of multi-rotor drones in various fields. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments of this application will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the structure of a multi-rotor unmanned aerial vehicle according to an embodiment of this application;

[0024] Figure 2 This is a schematic diagram of the bottom structure of the multi-rotor UAV according to an embodiment of this application;

[0025] Figure 3 This is a schematic diagram of the transmission assembly according to an embodiment of this application;

[0026] Figure 4This is a schematic diagram of the landing gear assembly according to an embodiment of this application;

[0027] Figure 5 This is a schematic diagram of the structure of the elastic element in an embodiment of this application;

[0028] Figure 6 This is a schematic diagram of the structure of the robotic arm according to an embodiment of this application;

[0029] Figure 7 This is a schematic diagram of the locking assembly according to an embodiment of this application;

[0030] Figure 8 This is a schematic diagram of the shaft hole structure according to an embodiment of this application.

[0031] Icons: 1-UAV body; 11-Buffer pad groove; 12-Embedded mounting groove; 2-Rotating shaft; 21-Shaft hole; 3-Landing gear assembly; 31-Support rod; 32-Force transmission element; 33-Elastic element; 34-Buffer pad body; 4-Drive component; 5-Transmission assembly; 51-Transmission rod; 52-First gear; 53-Second gear; 6-Wing folding mechanism; 61-Rotating seat; 62-Locking assembly; 621-Fixing knob; 622-Limit block; 623-Fixing block; 624-Fixing slot; 625-Limit slot; 7-Arm; 8-Handle; 9-Display screen; 10-Heat dissipation hole; 101-Searchlight; 102-Rotor; 103-Power motor. Detailed Implementation

[0032] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0033] In the description of the embodiments of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the embodiments of this application and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application according to the specific circumstances.

[0034] This application provides a multi-rotor unmanned aerial vehicle (UAV), such as... Figures 1 to 8 As shown. The multi-rotor drone includes: a drone body 1, with multiple arms 7 radially arranged on its sidewalls, and at least one embedded mounting slot 12 at its bottom. A rotating shaft 2 is rotatably disposed within the embedded mounting slot 12. A landing gear assembly 3 is fixedly connected to the rotating shaft 2, used to support the drone body 1 in the deployed state, and at least partially accommodated within the embedded mounting slot 12 in the folded state. A drive component 4 is disposed within the drone body 1. A transmission assembly 5 has its two ends connected to the output end of the drive component 4 and the rotating shaft 2, respectively. The drive component 4 is configured to drive the rotating shaft 2 to rotate via the transmission assembly 5, thereby causing the landing gear assembly 3 to switch between the deployed state supporting the drone body 1 and the folded state rotated and accommodated within the embedded mounting slot 12 around the axis of the rotating shaft 2.

[0035] Furthermore, a power motor 103 is installed at the end of the arm 7 away from the main body 1 of the drone, and a rotor 102 is installed at the top of the power motor 103. When the drone is working, the power motor 103 on the arm 7 starts and drives the rotor 102 to rotate at high speed. The rotor 102 generates upward lift during rotation, thereby providing the necessary power support for the drone's flight.

[0036] Specifically, when folded up, the outer contour of the landing gear assembly 3 is flush with the bottom of the drone body 1. This design further optimizes the drone's storage characteristics and minimizes space waste.

[0037] It should be noted that the drive component 4, located within the main body 1 of the UAV, transmits power to the rotating shaft 2, which is rotatably mounted in the embedded mounting slot 12, via the transmission assembly 5. This drives the landing gear assembly 3, fixedly connected to the rotating shaft 2, to rotate around the axis of the rotating shaft 2, thus enabling the landing gear assembly 3 to switch between its unfolded state supporting the main body 1 and its folded state, rotated and stored in the embedded mounting slot 12. Therefore, by storing the folded landing gear assembly 3 in the embedded mounting slot 12, this application reduces the overall size of the UAV, improves portability and space utilization, eliminates the need for users to equip themselves with bulky storage devices, and reduces the space occupied in vehicles or aircraft cargo holds during transportation, thereby lowering transportation costs. Furthermore, the embedded design provides effective protection for the landing gear assembly 3, reducing the risk of damage due to collisions and compression during transportation and storage, lowering maintenance costs and usage risks, and providing a more reliable and convenient solution for the widespread application of multi-rotor UAVs in various fields.

[0038] In this embodiment, the drive component 4 is communicatively connected to the UAV flight control system, enabling automatic deployment and retraction. This effectively reduces wind resistance and increases the UAV's endurance during flight. The UAV flight control system can intelligently control the drive component 4 to automatically deploy and fold the landing gear assembly 3 according to a preset program or real-time flight status, eliminating the need for manual operation. This improves the efficiency and convenience of UAV takeoff, landing, and storage. Especially in complex or emergency flight scenarios, it can quickly respond to complete landing gear state transitions, ensuring the smooth execution of flight missions and reducing the risks associated with human error.

[0039] In this embodiment, the transmission assembly 5 includes: a transmission rod 51 connected to the output end of the drive member 4; a first gear 52 connected to the end of the transmission rod 51 away from the drive member 4; and a second gear 53 meshing with the first gear 52. The rotating shaft 2 is fixedly disposed on the inner wall of the second gear 53.

[0040] It should be noted that when the drive component 4 operates, its output end drives the transmission rod 51 to rotate. The transmission rod 51 then drives the first gear 52, which is connected to the end furthest from the drive component 4, to rotate. Since the second gear 53 meshes with the first gear 52, the rotation of the first gear 52 drives the second gear 53 to rotate synchronously. The rotating shaft 2 is fixedly installed on the inner wall of the second gear 53, so when the second gear 53 rotates, it drives the rotating shaft 2 to rotate as well. Ultimately, the drive component 4 drives the rotating shaft 2 to rotate through the transmission assembly 5. Therefore, the transmission assembly 5 of this application has a compact structure, high transmission efficiency, and stable transmission ratio. It can accurately transmit the power of the drive component 4 to the rotating shaft 2, ensuring that the landing gear assembly 3 can stably and reliably switch between the unfolded and folded states. This effectively improves the accuracy and stability of the UAV landing gear operation and ensures the safe take-off, landing, and storage of the UAV under different working conditions.

[0041] Specifically, the transmission component 5 of this application also includes a transmission shaft, which is coaxially arranged with the rotating shaft 2. This design makes the power transmission more stable and efficient.

[0042] In one embodiment of this application, to meet the stability requirements of the drone's take-off and landing support, two embedded mounting slots 12 are provided at the bottom of the drone body 1, located on both sides of the drive component 4. Two rotating shafts 2 are rotatably mounted within their respective embedded mounting slots 12. This symmetrical layout helps balance the overall structure of the drone, resulting in a more reasonable center of gravity distribution when the landing gear assembly 3 is stowed. Four landing gear assemblies 3 are provided, spaced apart along the length of the two rotating shafts 2. This layout ensures uniform force distribution during take-off, landing, and parking, while also making full use of space. Therefore, through the ingenious layout design of the transmission component 5, landing gear assembly 3, and embedded mounting slots 12, this application not only ensures the accuracy and stability of power transmission, allowing the landing gear assembly 3 to reliably and stably switch between unfolded and folded states, but also optimizes the overall structure of the drone, improves its balance and stability, further guarantees safe take-off, landing, and stowage under different operating conditions, and also improves the space utilization and portability of the drone in its stowed state.

[0043] In this embodiment, the landing gear assembly 3 includes a support rod 31, a force transmission element 32, an elastic element 33, and a buffer pad body 34. The support rod 31 is fixedly connected to the rotating shaft 2. An axial groove is provided on the inner wall of the support rod 31, and the force transmission element 32 is slidably connected to the axial groove. The two ends of the elastic element 33 are respectively connected to the bottom wall inside the support rod 31 and the force transmission element 32, and are used to provide a restoring elastic force to the force transmission element 32. The buffer pad body 34 is fixedly connected to the end of the force transmission element 32 away from the elastic element 33 and is located outside the support rod 31. The landing impact force drives the buffer pad body 34 and the force transmission element 32 to move along the axial groove into the support rod 31, compressing the elastic element 33 to absorb energy.

[0044] It should be noted that during UAV landing, the landing impact force acts on the buffer pad body 34. Since the buffer pad body 34 is fixedly connected to the end of the force transmission element 32 away from the elastic element 33, and the force transmission element 32 is slidably connected to the axial groove on the inner wall of the support rod 31, the impact force drives the buffer pad body 34 and the force transmission element 32 to move along the axial groove into the support rod 31, thereby compressing the elastic element 33 connected to the force transmission element 32 and the inner bottom wall of the support rod 31. The elastic element 33 absorbs energy through its own deformation. When the impact force disappears, the elastic element 33 pushes the force transmission element 32 and the buffer pad body 34 to reset along the axial groove under the action of the reset elastic force. Therefore, the landing gear assembly 3 of this application can effectively buffer the impact force during UAV landing by absorbing the landing impact energy through the elastic element 33, reduce the impact and vibration on the fuselage, reduce the risk of damage to the internal precision components of the UAV, improve the safety and stability of UAV landing, extend the service life of the UAV, and at the same time, the structure is relatively simple and reliable, and the cost is low.

[0045] In one embodiment of this application, two axial grooves are provided, which are symmetrically arranged on opposite sides of the inner wall of the support rod 31, thereby avoiding the problems of offset and swaying that may occur with a single axial groove and improving the accuracy and reliability of the movement of the force transmission element 32.

[0046] In this embodiment of the application, a buffer pad groove 11 is provided at the bottom of the drone body 1. In the folded state, the buffer pad body 34 is embedded in the buffer pad groove 11.

[0047] It should be noted that the design of the buffer pad body 34 being embedded in the buffer pad groove 11 at the bottom of the drone body 1 when folded makes the overall structure of the drone more compact and orderly when stored, further reducing space occupation, improving portability, and making it convenient for users to carry and transport. At the same time, the buffer pad groove 11 plays a good protective role for the buffer pad body 34, preventing it from being damaged by external collisions and compression during storage and transportation, extending the service life of the buffer pad body 34, reducing maintenance costs, and ensuring that the buffer pad body 34 can play a normal buffering function during subsequent take-off and landing, ensuring the safety and stability of the drone's take-off and landing.

[0048] In this embodiment, the embedded mounting groove 12 is provided with a shaft hole 21, and the rotating shaft 2 is rotatably disposed in the shaft hole 21, ensuring that the rotating shaft 2 will not deviate or shake during rotation, thereby ensuring that the power is stably transmitted to the rotating shaft 2 through the transmission component 5.

[0049] In this embodiment, the multi-rotor drone further includes multiple wing folding mechanisms 6. The multiple wing folding mechanisms 6 are respectively disposed between the drone body 1 and the corresponding arm 7. Wing folding mechanisms 6 located on the same side of the drone body 1 are not on the same horizontal plane. Each wing folding mechanism 6 includes a rotating base 61 and a locking assembly 62. The rotating base 61 is fixedly disposed on the side wall of the drone body 1. The arm 7 is rotatably connected to the rotating base 61. The locking assembly 62 is disposed between the arm 7 and the rotating base 61, and is used to lock the arm 7 in the unfolded position.

[0050] It should be noted that the multi-rotor drone features multiple wing folding mechanisms 6, and these mechanisms, located on the same side, are not on the same horizontal plane. This staggered layout greatly optimizes space utilization, making the overall structure of the drone more compact in the folded state, effectively reducing its storage volume and facilitating carrying and transportation. This is especially suitable for scenarios with high space requirements, such as storage in confined spaces or backpack carrying. The rotating base 61 in the wing folding mechanism 6 is fixed to the side wall of the drone body 1, and the arm 7 is rotatably connected to the rotating base 61. This design allows the arm 7 to flexibly unfold and fold, improving the convenience and flexibility of drone deployment. The locking component 62 is located between the arm 7 and the rotating base 61, reliably locking the arm 7 when it is unfolded to the designated position, ensuring the stability of the arm 7 during drone flight and preventing flight performance and safety from being affected by arm swaying.

[0051] In this embodiment, the locking assembly 62 includes a fixing knob 621, a limiting block 622, and a fixing block 623. The fixing knob 621 is movably connected to the arm 7 and the rotating base 61, and a limiting block 622 is provided at its bottom. A fixing block 623 is provided at the bottom of the arm 7. The inner wall of the rotating base 61 is provided with a fixing groove 624 corresponding to the fixing block 623 and a limiting groove 625 corresponding to the limiting block 622. The fixing knob 621 is configured to drive the limiting block 622 and the fixing block 623 to connect with the limiting groove 625 and the fixing groove 624 of the rotating base 61 when rotated to a first angle, thereby realizing the unfolding and locking of the arm 7. When rotated to a second angle, the connection between the limiting block 622 and the fixing block 623 and the limiting groove 625 and the fixing groove 624 of the rotating base 61 is released, thereby realizing the rotation and folding of the arm 7.

[0052] In this embodiment, the inner wall of the rotating seat 61 is provided with a first internal thread, and the inner wall of the machine arm 7 is provided with a second internal thread. The fixing knob 621 is provided with an external thread corresponding to the first and second internal threads.

[0053] It should be noted that when the arm 7 needs to be unfolded and locked, the fixing knob 621 is rotated to the first angle. Since the fixing knob 621 is provided with external threads corresponding to the first internal thread on the inner wall of the rotating seat 61 and the second internal thread on the inner wall of the arm 7, during the tightening process, the limiting block 622 at the bottom of the fixing knob 621 will connect with the limiting slot 625 on the inner wall of the rotating seat 61, and at the same time, the fixing block 623 at the bottom of the arm 7 will be engaged in the corresponding fixing slot 624 on the inner wall of the rotating seat 61, thereby locking the unfolded position of the arm 7. When the arm 7 needs to be rotated and folded, the fixing knob 621 is rotated to the second angle. During the loosening process, the limiting block 622 and the fixing block 623 are disengaged from the connection of the limiting slot 625 and the fixing slot 624, respectively. At this time, the arm 7 can rotate freely around the rotating seat 61 to fold. Therefore, the locking component 62 of this application, through threaded connection and slot cooperation, not only ensures the firm locking of the arm 7 when it is unfolded, ensuring the stability of the arm 7 during the flight of the drone, but also allows users to quickly and conveniently perform the folding and unfolding operations of the arm 7, improving the portability and deployment efficiency of the drone; at the same time, the threaded connection has a certain degree of self-locking, which can effectively prevent the arm 7 from being accidentally unlocked due to vibration or other reasons during flight, further improving the safety and reliability of the drone flight.

[0054] In this embodiment, the multi-rotor drone also includes a handle 8 disposed on the top of the drone body 1. When the drone is being transported, moved, or when its attitude needs to be manually controlled, the user can easily grasp the handle 8, improving the convenience and safety of operation and preventing damage or injury to personnel caused by the drone slipping.

[0055] And / or may also include a display screen 9 mounted on the side wall of the drone body 1. The display screen 9 can display various key information of the drone in real time, such as flight status (flight altitude, speed, attitude, etc.), battery level, signal strength, sensor data, etc. This allows operators to intuitively obtain the drone status on-site without the need for external equipment, facilitating timely decision-making and adjustments, and improving the accuracy and efficiency of flight operations.

[0056] And / or may also include heat dissipation holes 10 disposed on the surface of the drone body 1. During operation, the internal electronic components of the drone generate a large amount of heat. The heat dissipation holes 10 effectively increase air circulation, accelerate heat dissipation, and can promptly remove internal heat, avoiding performance degradation, damage, or even safety hazards caused by excessive temperature, thereby ensuring the stability and reliability of the drone under long-term, high-load operation.

[0057] And / or may also include a searchlight 101 mounted on top of the drone body 1. When performing missions at night or in low-light conditions, the searchlight 101 can provide sufficient light to illuminate the flight area.

[0058] Furthermore, this application utilizes precision structures such as rotating shafts and drive shafts to achieve flexible and stable folding of the landing gear assembly 3. After folding, the drone's storage volume is significantly reduced, drastically decreasing the space required for storage and making storage more convenient. During transport, the compact folding structure facilitates placement in various transportation vehicles such as backpacks, vehicle trunks, or air cargo containers, enhancing portability and making it particularly suitable for scenarios requiring frequent movement, such as outdoor surveying and emergency rescue.

[0059] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.

[0060] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.

Claims

1. A multi-copter drone, characterized in that, include: The main body of the drone (1) has multiple arms (7) arranged radially on its side wall and at least one embedded mounting groove (12) at its bottom; The rotating shaft (2) is rotatably disposed within the embedded mounting groove (12); The landing gear assembly (3) is fixedly connected to the rotating shaft (2) and is used to support the main body of the UAV (1) in the unfolded state and is at least partially accommodated in the embedded mounting slot (12) in the folded state. The drive unit (4) is disposed inside the main body (1) of the UAV; The transmission assembly (5) has its two ends connected to the output end of the drive component (4) and the rotating shaft (2), respectively; The drive unit (4) is configured to drive the rotating shaft (2) to rotate via the transmission assembly (5), thereby causing the landing gear assembly (3) to switch between an unfolded state supporting the UAV body (1) and a folded-down state rotated and stored in the embedded mounting slot (12) around the axis of the rotating shaft (2).

2. The multicopter drone of claim 1, wherein, The drive unit (4) is connected to the UAV flight control system.

3. The multicopter drone of claim 1, wherein, The transmission assembly (5) includes: The transmission rod (51) is connected to the output end of the drive component (4); The first gear (52) is connected to the end of the transmission rod (51) away from the driving member (4); The second gear (53) meshes with the first gear (52); The rotating shaft (2) is fixedly disposed on the inner wall of the second gear (53).

4. The multi-rotor UAV according to claim 1, characterized in that, The landing gear assembly (3) includes a support rod (31), a force transmission element (32), an elastic element (33), and a buffer pad body (34); The support rod (31) is fixedly connected to the rotating shaft (2); The inner wall of the support rod (31) is provided with an axial groove, and the force transmission element (32) is slidably connected to the axial groove. The two ends of the elastic element (33) are respectively connected to the bottom wall inside the support rod (31) and the force transmission element (32), and are used to provide a restoring elastic force to the force transmission element (32); The buffer pad body (34) is fixedly connected to the end of the force transmission element (32) away from the elastic element (33) and is located outside the support rod (31); The landing impact force drives the buffer pad body (34) and the force transmission element (32) to move along the axial groove into the support rod (31), compressing the elastic element (33) to absorb energy.

5. The multicopter drone of claim 4, wherein, The bottom of the drone body (1) is provided with a buffer pad groove (11). In the folded state, the buffer pad body (34) is embedded in the buffer pad groove (11).

6. The multicopter drone of claim 1, wherein, The embedded mounting groove (12) is provided with a shaft hole (21), and the rotating shaft (2) is rotatably disposed in the shaft hole (21).

7. The multicopter drone of claim 1, wherein, It also includes multiple wing folding mechanisms (6); Multiple wing folding mechanisms (6) are respectively disposed between the UAV body (1) and the corresponding arms (7); The wing folding mechanism (6) located on the same side of the main body (1) of the UAV is not on the same horizontal plane; The wing folding mechanism (6) includes a rotating base (61) and a locking assembly (62); The rotating base (61) is fixedly mounted on the side wall of the UAV body (1); The arm (7) is rotatably connected to the rotating base (61); The locking assembly (62) is disposed between the arm (7) and the rotating seat (61) for locking the arm (7) in the unfolded position.

8. The multicopter drone of claim 7, wherein, The locking assembly (62) includes a fixing knob (621), a limiting block (622), and a fixing block (623); The fixed knob (621) is movably connected to the arm (7) and the rotating seat (61), and a limit block (622) is provided at its bottom; A fixing block (623) is provided at the bottom of the arm (7); The inner wall of the rotating seat (61) is provided with a fixing slot (624) corresponding to the fixing block (623) and a limiting slot (625) corresponding to the limiting block (622); The fixed knob (621) is configured to drive the limiting block (622), the fixed block (623) to connect with the limiting slot (625) and the fixed slot (624) of the rotating seat (61) when rotated to the first angle, thereby realizing the unfolding and locking of the arm (7); when rotated to the second angle, the connection between the limiting block (622), the fixed block (623) and the limiting slot (625) and the fixed slot (624) of the rotating seat (61) is released, thereby realizing the rotation and folding of the arm (7).

9. The multicopter drone of claim 8, wherein, The inner wall of the rotating seat (61) is provided with a first internal thread, and the inner wall of the arm (7) is provided with a second internal thread; The fixed knob (621) is provided with an external thread corresponding to the first internal thread and the second internal thread.

10. The multicopter drone of claim 1, wherein, It also includes a handle (8) located on the top of the drone body (1); And / or may also include a display screen (9) disposed on the side wall of the main body (1) of the drone; And / or may also include heat dissipation holes (10) disposed on the surface of the drone body (1); And / or may also include a searchlight (101) located on top of the main body (1) of the drone.

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