An unmanned aerial vehicle protection structure and unmanned aerial vehicle

Abstract

The utility model relates to the field of unmanned aerial vehicle protection technology, specifically relates to an unmanned aerial vehicle protection structure and unmanned aerial vehicle, its including fuselage cover, the outer periphery of protective shell is used for installing rotor assembly and road condition detection device, the fuselage cover cover is established in the outside of protective shell, and forms the clearance between with protective shell, the fuselage cover is used for at least partial shielding road condition detection device in the up-down direction, the outer periphery of fuselage cover is equipped with the avoidance slot, to make rotor assembly pass through avoidance slot and extend the fuselage cover. Its installation road condition detection device buffer device, form clearance between fuselage cover and protective shell, can form double -deck protection to protective shell and unmanned aerial vehicle functional components in its inside, benefit to reduce the influence of weather to the inside fuselage, greatly improved the protection function of unmanned aerial vehicle itself.

Description

Technical Field

[0001] This utility model belongs to the field of drone protection technology, specifically relating to a drone protection structure and a drone. Background Technology

[0002] In recent years, drone technology has been widely applied in various industries. With the widespread use of drones to perform different tasks over long flight times (such as long-term field inspections, long-distance mapping, and continuous search and rescue), the working environment they face is becoming increasingly complex and diverse. In addition to the erosion of natural environments such as rain, dust, and high temperatures, they also need to cope with problems such as vibration and impact during flight.

[0003] While existing technologies have achieved some degree of protection for drones, their self-protection remains significantly inadequate when facing the erosion of the natural environment. Utility Model Content

[0004] The purpose of this utility model is to solve at least one of the technical problems existing in the prior art, and to provide a drone protection structure and drone, which is covered by a fuselage cover outside the protective shell and road condition detection device, forming a double layer of protection for the drone's functional components inside the protective shell, which helps to reduce the impact of weather on the internal fuselage and greatly improves the drone's own protection function.

[0005] The technical solution adopted by this utility model to solve its technical problem is: In a first aspect, a drone protection structure is provided, the drone including a fuselage, the drone protection structure comprising: The fuselage cover has an opening at its bottom and covers the outside of the fuselage. The fuselage includes a protective shell and drone functional components installed inside the protective shell. A gap is formed between the fuselage cover and the protective shell, and a clearance groove is provided on the outer periphery of the fuselage cover. The protective shell has a rotor assembly and a road condition detection device installed on its outer periphery. The fuselage cover at least partially covers the road condition detection device in the vertical direction. The road condition detection device extends downward through the cover opening of the fuselage cover, and the rotor assembly extends out of the fuselage cover through the clearance groove.

[0006] In conjunction with the first aspect, in some implementations of the first aspect, the front side of the fuselage cover has two inclined plates symmetrically arranged along the vertical central axis of the fuselage cover. The inclined plate located near the left side of the fuselage cover is inclined from front to back to the left, and the inclined plate located near the right side of the fuselage cover is inclined from front to back to the right. Each of the inclined plates is inclined with heat dissipation holes.

[0007] In combination with the first aspect and the above-mentioned implementation methods, in some implementation methods of the first aspect, the heat dissipation holes are arranged at an angle from top to bottom towards the outside of the fuselage cover.

[0008] In a second aspect, an unmanned aerial vehicle (UAV) includes a rotor assembly, a road condition detection device, and a UAV protective structure as described in any implementation of the first aspect. The fuselage cover is disposed outside the fuselage, the fuselage including a protective shell and UAV functional components installed within the protective shell. The rotor assembly and the road condition detection device are both installed on the outer periphery of the protective shell. The rotor assembly extends out of the fuselage cover through the clearance groove. The road condition detection device is at least partially obscured by the fuselage cover in the vertical direction and extends downward out of the fuselage cover through the cover opening.

[0009] In conjunction with the second aspect, in some implementations of the second aspect, the rotor assembly includes two first rotor assemblies and a second rotor assembly disposed on the rear side of the protective shell, with the two first rotor assemblies symmetrically arranged on the left and right sides of the protective shell along the vertical central axis of the protective shell.

[0010] In combination with the second aspect and the above-described implementations, in some implementations of the second aspect, the rotor assembly includes an arm, a propeller, a protective cover, and a drive component. The first end of the arm extends into the clearance groove and is connected to the protective cover. The second end of the arm is provided with a mounting base. The propeller is rotatably mounted on the bottom of the mounting base. The protective cover is placed over the mounting base and has a through hole. The drive component is mounted on the arm, and the output end of the drive component passes through the through hole and is connected to the hub of the propeller.

[0011] In combination with the second aspect and the above implementation methods, in some implementation methods of the second aspect, the protective shell is provided with a mounting groove on its side, and the first end of the robot arm is provided with baffles at both the top and bottom positions. The first end of the robot arm and the baffles pass through the clearance groove and the mounting groove in sequence and then extend into the protective shell. The robot arm is connected to the protective shell through the baffles.

[0012] In conjunction with the second aspect and the above-described implementations, in some implementations of the second aspect, the UAV functional components include a flight control system, the arm has a tubular structure, an electronic speed controller is installed below the arm, the bottom of the arm has a wire hole connecting the inner cavity of the arm to the outside, the electronic speed controller is electrically connected to a first connecting wire and a second connecting wire, the first connecting wire and the second connecting wire pass through the wire hole and extend into the arm, the first connecting wire extends along the arm to the protective shell and is electrically connected to the flight control system, and the second connecting wire extends along the arm to the drive component and is electrically connected to the drive component.

[0013] In combination with the second aspect and the above-mentioned implementation methods, in some implementation methods of the second aspect, the protective shell is provided with a first sealing structure between the baffle and the arm, the arm is provided with a second sealing structure at the wire hole that abuts against the first connecting line and the second connecting line, and the protective cover is provided with a third sealing structure between the mounting base and the mounting seat.

[0014] In combination with the second aspect and the above-described implementations, in some implementations of the second aspect, the road condition detection device includes a lidar and a gimbal camera. The lidar is installed on the front side of the protective shell, and the gimbal camera is installed on the bottom of the protective shell. Both the lidar and the gimbal camera are equipped with a first buffer component. A second buffer component is provided inside the protective shell, and the second buffer component is located in the gap formed between the protective shell and the UAV functional components.

[0015] One of the above technical solutions has at least one of the following advantages or beneficial effects: the UAV protective structure and the UAV are covered by a fuselage cover outside the protective shell and the road condition detection device. The fuselage cover itself can provide an outer layer of protection for the protective shell. Through the combined action of the fuselage cover and the protective shell, a double layer of protection can be formed for the UAV functional components inside the protective shell, effectively ensuring that the UAV can be protected from the effects of rain, sand, or high temperature when it is subjected to harsh outdoor environments.

[0016] In addition, the gap between the fuselage cover and the protective shell can isolate the high or low temperatures outside the fuselage cover, reducing the impact of temperature changes on the internal fuselage. On the other hand, the gap between the two can reduce the direct impact of external rain and dust on the fuselage, greatly improving the protection function of the drone itself. Attached Figure Description

[0017] The present invention will be further described below with reference to the accompanying drawings: Figure 1 This is a structural schematic diagram of one embodiment of the UAV of this utility model; Figure 2 yes Figure 1 A front view schematic diagram of one embodiment is shown; Figure 3 yes Figure 1 A cross-sectional schematic diagram of one embodiment is shown; Figure 4 yes Figure 1 The diagram shown is a structural schematic of an embodiment where the fuselage cover is hidden. Figure 5 yes Figure 1 A top view schematic diagram of one embodiment is shown; Figure 6 yes Figure 5Sectional view at point AA.

[0018] Explanation of icon numbers: 1. Fuselage; 11. Protective shell; 12. UAV functional components; 13. Gap; 14. Baffle; 15. Electronic speed controller; 2. Fuselage cover; 21. Heat dissipation hole; 22. Tilt plate; 23. Clearance groove; 31. LiDAR; 32. Gimbal camera; 41. First rotor assembly; 42. Second rotor assembly; 431. Arm; 432. Propeller; 433. Protective cover; 434. Drive unit; 435. Mounting base. Detailed Implementation

[0019] This section will describe in detail the specific embodiments of the present utility model. The preferred embodiments of the present utility model are shown in the accompanying drawings. The purpose of the drawings is to supplement the textual description with graphics, so that people can intuitively and vividly understand each technical feature and the overall technical solution of the present utility model, but they should not be construed as limiting the scope of protection of the present utility model.

[0020] In this utility model, when directions (up, down, left, right, front, and back) are described, it is only for the purpose of describing the technical solution of this utility model, and does not indicate or imply that the technical features referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation of this utility model.

[0021] In this utility model, "several" means one or more, "multiple" means two or more, "greater than," "less than," "exceeding," etc. are understood to exclude the stated number; "above," "below," "within," etc. are understood to include the stated number. In the description of this utility model, if "first" or "second" is used, it is only for the purpose of distinguishing technical features and should not be construed as indicating or implying relative importance or implicitly indicating the number of indicated technical features or the order of the indicated technical features.

[0022] In this utility model, unless otherwise explicitly defined, terms such as "set," "install," and "connect" should be interpreted broadly. For example, they can refer to a direct connection or an indirect connection through an intermediate medium; a fixed connection, a detachable connection, or an integrally formed connection; a mechanical connection, an electrical connection, or a connection capable of mutual communication; or the internal connection of two components or the interaction between two components. Those skilled in the art can reasonably determine the specific meaning of the above terms in this utility model based on the specific content of the technical solution.

[0023] When drones are used for long-endurance missions such as field inspections, long-distance mapping, or continuous search and rescue, they are often affected by outdoor natural environments such as rain, dust storms, or high temperatures. To prevent erosion caused by outdoor weather changes, see [link to relevant documentation]. Figures 1 to 4This utility model provides a protective structure for a drone. The drone includes a fuselage 1, and the protective structure includes a fuselage cover 2. The fuselage 1 includes a protective shell 11 and drone functional components 12 installed within the protective shell 11. The outer periphery of the protective shell 11 is used to install rotor components and road condition detection devices. The protective shell 11 provides inner protection for the internal drone functional components 12. It is understood that the drone functional components 12 may include flight control systems, voltage reduction modules, and receivers, etc., and can be reasonably configured according to the actual functional requirements of the drone, without limitation.

[0024] The bottom of the fuselage cover 2 has an opening, and the fuselage cover 2 covers the outside of the protective shell 11, forming a gap 13 between the fuselage cover 2 and the protective shell 11. See [reference needed]. Figure 3 On the one hand, the gap 13 can isolate the high or low temperature of the outside, which helps to reduce the impact of temperature changes on the internal fuselage 1; on the other hand, the gap 13 between the two can reduce the direct impact of external rain and dust on the fuselage 1.

[0025] In addition, the fuselage cover 2 itself can provide an outer layer of protection for the protective shell 11, thus better protecting the entire fuselage 1. Through the combined action of the fuselage cover 2 and the protective shell 11, a double layer of protection can be formed for the drone's functional components 12 inside the protective shell 11, effectively ensuring that the drone can withstand the effects of harsh outdoor environments such as rain, dust, or high temperatures, greatly improving the drone's own protective capabilities.

[0026] The fuselage cover 2 is used to at least partially shield the road condition detection device in the vertical direction. The road condition detection device extends downward through the cover opening of the fuselage cover 2 to ensure that the fuselage cover 2 can protect the road condition detection device, so as to reduce or avoid the impact of severe weather and ensure that the road condition detection device can detect the road conditions.

[0027] The outer periphery of the fuselage fairing 2 is provided with a clearance groove 23 to allow the rotor assembly to extend out of the fuselage fairing 2 through the clearance groove 23. It is understood that the clearance groove 23 can be positioned separately from the fairing opening; alternatively, the clearance groove 23 can be located at the bottom of the fuselage fairing 2 and extend downwards to the fairing opening, see [reference needed]. Figure 1 The body cover 2 can be installed over the outside of the protective shell 11 from top to bottom through the cover opening, which is convenient for installation.

[0028] The drone protection structure of this technical solution is covered by the fuselage cover 2 on the outside of the protective shell 11 and the road condition detection device. The fuselage cover 2 itself can provide outer protection for the protective shell 11. Through the combined action of the fuselage cover 2 and the protective shell 11, the drone functional components 12 inside the protective shell 11 can form double protection, effectively ensuring that the drone can be protected from the effects of rain, sand, or high temperature when it is subjected to harsh outdoor environments.

[0029] In addition, the gap 13 formed between the fuselage cover 2 and the protective shell 11 can, on the one hand, isolate the high or low temperature outside the fuselage cover 2, which helps to reduce the impact of temperature changes on the internal fuselage 1; on the other hand, the gap 13 between the two can reduce the direct impact of external rain and sand on the fuselage 1, which greatly improves the protection function of the drone itself.

[0030] Further, see Figure 1 and Figure 2 The front side of the fuselage cover 2 is provided with heat dissipation holes 21, which can effectively dissipate heat from the fuselage 1 and the road condition detection device. Specifically, the front side of the fuselage cover 2 has two inclined plates 22 symmetrically arranged along the vertical central axis of the fuselage cover 2. The inclined plate 22 located near the left side of the fuselage cover 2 is inclined from front to back to the left, and the inclined plate 22 located near the right side of the fuselage cover 2 is inclined from front to back to the right. The heat dissipation holes 21 are inclinedly arranged on the inclined plates 22. The inclined arrangement of the inclined plates 22 conforms to the mechanical design of flight and helps to reduce the flight drag of the UAV. By setting the heat dissipation holes 21 inclinedly on the inclined plates 22, on the one hand, rapid heat dissipation can be achieved by utilizing the windward surface, and on the other hand, rainwater and sand and other foreign objects can be guided to flow outward at an angle, preventing rainwater and sand and other foreign objects from directly entering the heat dissipation holes 21, thus improving the protection effect.

[0031] Furthermore, see Figure 1 and Figure 2 The heat dissipation vents 21 are angled downwards towards the outer side of the fuselage cover 2. In other words, the heat dissipation vents 21 on the inclined plate 22 on the left side of the fuselage cover 2 are angled downwards towards the left side of the fuselage cover 2, while the heat dissipation vents 21 on the inclined plate 22 on the right side of the fuselage cover 2 are angled downwards towards the right side of the fuselage cover 2. During drone flight, the heat dissipation vents 21 designed in this way are more in line with the direction of wind flow, resulting in better heat dissipation and protection.

[0032] See also Figures 1 to 4 This utility model also provides a drone, including a rotor assembly, a road condition detection device, and a drone protective structure. Both the rotor assembly and the road condition detection device are mounted on the outer periphery of the protective shell 11. The rotor assembly extends out of the fuselage cover 2 through a clearance slot 23 to provide power for the drone's flight. The road condition detection device is at least partially shielded by the fuselage cover 2 in the vertical direction and extends downward through the cover opening to perform road condition detection.

[0033] Understandably, the road condition detection device includes a lidar 31 and a four-light gimbal camera 32. The lidar 31 is used for road obstacle detection, and can accurately measure the target's position, movement state, and shape, thereby detecting, identifying, distinguishing, and tracking the target. The four-light gimbal camera 32 is used to take multi-angle pictures of the target and transmit the images back, ensuring that the UAV can fly along the accurate path.

[0034] See Figure 1 and Figure 4 In some embodiments, the rotor assembly includes two first rotor assemblies 41 and a second rotor assembly 42 disposed on the rear side of the protective shell 11. The two first rotor assemblies 41 are symmetrically arranged on the left and right sides of the protective shell 11 along the vertical central axis of the protective shell 11.

[0035] Furthermore, see Figure 5 and Figure 6 The rotor assembly includes an arm 431, a propeller 432, a protective cover 433, and a drive unit 434. The first end of the arm 431 extends into a clearance groove 23 and connects to the protective shell 11. The second end of the arm 431 is provided with a mounting base 435, and the propeller 432 is rotatably mounted on the bottom of the mounting base 435. The protective cover 433 covers the mounting base 435 and has a through hole. The drive unit 434 is mounted on the arm 431, and its output end passes through the through hole and connects to the hub of the propeller 432 to drive the propeller 432 to rotate. By providing the protective cover 433, the connection between the output end of the drive unit 434 and the propeller 432 can be protected.

[0036] Furthermore, by separately providing a protective cover 433 to protect the output end of the drive unit 434 and a fuselage cover 2 to protect the fuselage 1, installation is facilitated while providing more targeted protection for both the drive unit 434 and the fuselage 1. The outer periphery of the protective cover 433 bends downwards, providing better shielding for the mounting base 435. It is understood that the drive unit 434 can be configured as a servo motor or other similar device, depending on actual needs; no restrictions are placed here.

[0037] See Figure 3 , Figure 4 and Figure 5In some embodiments, the protective shell 11 has a mounting groove on its side, and the first end of the arm 431 has baffles 14 at both the top and bottom positions. The first end of the arm 431 and the baffles 14 pass through the clearance groove 23 and the mounting groove in sequence and then extend into the protective shell 11. The arm 431 is connected to the protective shell 11 through the baffles 14. By adding a baffle 14 at the connection between the arm 431 and the protective shell 11, and extending the baffle 14 from the inside of the protective shell 11 to the outside of the fuselage cover 2, rainwater, sand and dust and other foreign objects can be effectively prevented from entering the protective shell 11 through the periphery of the first end of the arm 431, further protecting the UAV functional components 12 inside the fuselage 1 and helping to improve the overall lifespan of the UAV.

[0038] In some embodiments, see Figure 6 The UAV functional components 12 include a flight control system, an arm 431 with a tubular structure, and an electronic speed controller 15 installed at the bottom of the arm 431. The bottom of the arm 431 has a wire hole connecting its inner cavity to the outside. The electronic speed controller 15 is electrically connected to a first connecting wire and a second connecting wire. The first and second connecting wires pass through the wire hole and extend into the arm 431. The first connecting wire extends along the arm 431 into the protective shell 11 and is electrically connected to the flight control system. The second connecting wire extends along the arm 431 to the drive component 434 and is electrically connected to the drive component 434. The electronic speed controller 15 receives commands from the flight control system and precisely controls the rotational speed of the drive component 434, thereby effectively controlling the flight of the UAV.

[0039] Furthermore, both the first and second connecting wires are fitted with protective sleeves to prevent wear and tear on the first and second connecting wires, while also providing waterproof and dustproof protection.

[0040] Furthermore, the protective shell 11 is provided with a first sealing structure between the baffle 14 and the arm 431 to effectively seal the gap between the baffle 14 and the arm 431, providing better dust and water protection. The arm 431 is provided with a second sealing structure at the wire hole, corresponding to and abutting against the first and second connecting wires, to effectively seal the wire hole and prevent sand and rainwater from entering the arm 431 and damaging the first and second connecting wires. A third sealing structure is provided between the protective cover 433 and the mounting base 435 to effectively seal the gap between the protective cover 433 and the mounting base 435, preventing sand and rainwater from seeping into the connection between the output end of the drive component 434 and the hub of the propeller 432, thereby avoiding rust and corrosion.

[0041] It is understandable that the first sealing structure, the second sealing structure, and the third sealing structure may all use sealing strips, sealing rings, etc., and there are no restrictions here.

[0042] Furthermore, see Figures 1 to 4The road condition detection device includes a lidar 31 and a gimbal camera 32. The lidar 31 is mounted on the front side of the protective shell 11; in other words, the lidar 31 is located at the gap 13 and extends downwards from the protective shell 11. The gimbal camera 32 is mounted on the bottom of the protective shell 11. Both the lidar 31 and the gimbal camera 32 are equipped with first buffer components to reduce the impact of vibration on the road condition detection device during flight and landing. A second buffer component is provided inside the protective shell 11, located in the gap between the protective shell 11 and the UAV functional components 12. This second buffer component can effectively absorb vibration energy during flight, reducing the impact of vibration on the flight control system and other UAV functional components 12. It is understood that the first and second buffer components can be made of materials such as rubber or silicone, such as buffer balls or buffer pads, and there are no restrictions on their use.

[0043] In some embodiments, the surfaces of the fuselage cover 2 and the protective cover 433 are coated with a high-temperature resistant coating to ensure that the UAV has good high-temperature resistance, thereby meeting the operational requirements under high-temperature conditions. The protective shell 11 is equipped with heat sinks to dissipate heat from internal functional components such as the electronic control box and other heat-prone components, effectively preventing the impact of high temperatures on battery performance and lifespan.

[0044] Furthermore, both the fuselage cover 2 and the protective cover 433 are made of high-strength, lightweight materials, which are in line with the fuselage 1 and aerodynamic layout of the tri-rotor UAV.

[0045] In the description of this specification, references to terms such as "example," "embodiment," or "some embodiments" indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0046] Of course, the present invention is not limited to the above-described embodiments. Those skilled in the art can make equivalent modifications or substitutions without departing from the spirit of the present invention, and these equivalent modifications or substitutions are all included within the scope defined by the claims of this application.

Claims

1. A drone protection structure, the drone comprising a fuselage, characterized in that, The drone protection structure includes: The fuselage cover has an opening at its bottom and covers the outside of the fuselage. The fuselage includes a protective shell and drone functional components installed inside the protective shell. A gap is formed between the fuselage cover and the protective shell, and a clearance groove is provided on the outer periphery of the fuselage cover. The protective shell has a rotor assembly and a road condition detection device installed on its outer periphery. The fuselage cover at least partially covers the road condition detection device in the vertical direction. The road condition detection device extends downward through the cover opening of the fuselage cover, and the rotor assembly extends out of the fuselage cover through the clearance groove.

2. The drone shield structure of claim 1, wherein, The front side of the fuselage cover has two inclined plates symmetrically arranged along the vertical central axis of the fuselage cover. The inclined plate located near the left side of the fuselage cover is inclined from front to back to left, and the inclined plate located near the right side of the fuselage cover is inclined from front to back to right. Each of the inclined plates is inclined with heat dissipation holes.

3. The drone shield structure of claim 2, wherein, The heat dissipation holes are arranged at an angle from top to bottom towards the outside of the fuselage cover.

4. A drone, characterized in that, The invention includes a fuselage, a rotor assembly, a road condition detection device, and a drone protective structure as described in any one of claims 1 to 3. The fuselage cover is disposed outside the fuselage. The fuselage includes a protective shell and drone functional components installed within the protective shell. The rotor assembly and the road condition detection device are both installed on the outer periphery of the protective shell. The rotor assembly extends out of the fuselage cover through the clearance groove. The road condition detection device is at least partially obscured by the fuselage cover in the vertical direction and extends downward through the cover opening of the fuselage cover.

5. The drone of claim 4, wherein, The rotor assembly includes two first rotor assemblies and a second rotor assembly located at the rear of the protective shell. The two first rotor assemblies are symmetrically arranged on the left and right sides of the protective shell along the vertical central axis of the protective shell.

6. The drone of claim 4, wherein, The rotor assembly includes an arm, a propeller, a protective cover, and a drive unit. The first end of the arm extends into the clearance groove and is connected to the protective cover. The second end of the arm is provided with a mounting base. The propeller is rotatably mounted on the bottom of the mounting base. The protective cover is placed over the mounting base and has a through hole. The drive unit is mounted on the arm, and the output end of the drive unit passes through the through hole and is connected to the hub of the propeller.

7. The drone of claim 6, wherein, The protective shell has a mounting groove on its side. The first end of the robot arm has baffles at the top and bottom. The first end of the robot arm and the baffles pass through the clearance groove and the mounting groove in sequence and then extend into the protective shell. The robot arm is connected to the protective shell through the baffles.

8. The drone of claim 7, wherein, The UAV functional components include a flight control system, the arm has a tubular structure, an electronic speed controller is installed at the bottom of the arm, and a wire hole is provided at the bottom of the arm to connect the inner cavity of the arm to the outside. The electronic speed controller is electrically connected to a first connecting wire and a second connecting wire. The first connecting wire and the second connecting wire pass through the wire hole and extend into the arm. The first connecting wire extends along the arm to the protective shell and is electrically connected to the flight control system. The second connecting wire extends along the arm to the drive component and is electrically connected to the drive component.

9. The drone of claim 8, wherein, The protective shell has a first sealing structure between the baffle and the arm, the arm has a second sealing structure at the wire hole that abuts against the first connecting line and the second connecting line, and the protective cover has a third sealing structure between the mounting base and the mounting plate.

10. The drone of claim 4, wherein, The road condition detection device includes a lidar and a gimbal camera. The lidar is installed on the front side of the protective shell, and the gimbal camera is installed on the bottom of the protective shell. Both the lidar and the gimbal camera are equipped with a first buffer component. A second buffer component is provided inside the protective shell, and the second buffer component is located in the gap formed between the protective shell and the UAV functional components.

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