Carbon fiber cushioning structure for multi-copter drones

Abstract

The utility model provides a carbon fiber buffer structure for multi -rotor unmanned plane relates to unmanned plane technical field, including unmanned plane base, unmanned plane base top is equipped with unmanned plane main part, the inside of unmanned plane base is equipped with the energy supply battery, unmanned plane base bottom is equipped with buffer structure top seat, buffer structure top seat bottom is equipped with buffer structure base, buffer structure top seat bottom is fixed with the sliding seat, buffer structure base top is fixed with sliding rod no.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a carbon fiber buffer structure for multi-rotor UAVs. Background Technology

[0002] A multi-rotor drone is an aircraft that relies on multiple rotors to generate lift and thrust for flight. It is typically driven by multiple motors, and the flight attitude and direction are controlled by changing the rotation speed of each rotor. This type of drone has advantages such as flexible take-off and landing, simple operation, and stable flight, making it suitable for use in various complex environments. It is widely used in aerial photography, logistics and distribution, agricultural plant protection, power line inspection and other fields, bringing great convenience to people's lives and work. With the continuous advancement of technology, the performance of multi-rotor drones is also constantly improving, and it is expected to play a greater role in more fields in the future.

[0003] In existing technologies, the lack of a buffer structure in multi-rotor drones significantly increases the risk of impact during landing. When a drone lands in complex terrain or in an emergency, without the protection of a buffer structure, the fuselage and critical components may be damaged by the instantaneous high impact force. Precision equipment such as cameras and sensors may be displaced or damaged due to vibration, resulting in data acquisition failure or blurred images. In addition, frequent high-impact landings will also accelerate the wear and tear of mechanical parts and reduce the service life of the drone. Utility Model Content

[0004] The purpose of this invention is to address the shortcomings of existing technologies by proposing a carbon fiber buffer structure for multi-rotor drones.

[0005] To achieve the above objectives, this utility model adopts the following technical solution: a carbon fiber buffer structure for a multi-rotor drone, comprising a drone base, a drone body on the top of the drone base, a power supply battery inside the drone base, a buffer structure top seat at the bottom of the drone base, a buffer structure base at the bottom of the buffer structure top seat, a sliding seat fixed at the bottom of the buffer structure top seat, a sliding rod one fixed at the top of the buffer structure base, the sliding rod one slidably connected to the inner wall of the sliding seat, a sliding inner shell fixed at the bottom of the buffer structure top seat, a sliding outer shell fixed at the top of the buffer structure base, the sliding inner shell slidably connected to the inner wall of the sliding outer shell, a buffer spring fixed at the top of the buffer structure base, the other end of the buffer spring fixed to the bottom of the sliding seat, a circular groove penetrating through the top of the buffer structure top seat, a sliding rod two slidably connected to the inner wall of the circular groove, and the sliding rod two fixed to the top of the buffer structure base.

[0006] Preferably, the drone base has a component slot one on one side, a battery box is slidably connected to the inner wall of the component slot one, the power supply battery is disposed on the inner wall of the battery box, a component slot two is formed on the inner wall of the component slot one, a drive seat is fixed to the bottom of the battery box, a drive spring is fixed to one side of the drive seat, the other end of the drive spring is fixed to the inner wall of the component slot two, a component slot three is formed on the inner wall of the component slot two, an adjusting handle is rotatably connected to the inner wall of the component slot three, a hook is fixed to one end of the adjusting handle, a return spring is fixed to the surface of the adjusting handle, the other end of the return spring is fixed to the inner wall of the component slot two, a hook groove is formed at the bottom of the battery box, and the hook is disposed on the inner wall of the hook groove. In existing technologies, if the battery design of a multi-rotor drone is not easily replaceable, it will bring a series of inconveniences. When the battery is depleted, users may have to wait for a long time to recharge, which limits the drone's continuous operation capability and affects work efficiency. For application scenarios that require long-term or frequent task execution, such as agricultural monitoring and logistics delivery, inconvenient battery replacement will greatly increase operational complexity and reduce the flexibility of task execution. To address these issues, this utility model adopts a convenient battery replacement structure. Pulling the adjustment handle will cause the hook to disengage from the hook groove. At this time, the elastic force of the drive spring will push the battery box to slide outward, thereby realizing the easy replacement of the battery box and its internal battery. The quick-release mechanism allows users to easily and quickly replace batteries without using any tools, greatly improving the convenience of battery replacement. At the same time, the design of the drive spring and return spring ensures the stability and reliability of the battery box during installation and ejection, which can significantly improve the drone's operational efficiency and flexibility. By implementing a quick and easy battery replacement mechanism, users can quickly replace batteries when they are depleted, thereby reducing the waiting time for charging and ensuring that the drone can continuously perform tasks. This not only improves the drone's continuous operation capability but also enhances its adaptability in scenarios requiring long-term or frequent task execution, such as agricultural monitoring and logistics delivery.

[0007] Preferably, the bottom of the buffer structure base is fixed with anti-slip protrusions, which are arranged in an array on the bottom of the buffer structure base and are made of silicone material. In the prior art, if the bottom of the buffer device lacks anti-slip measures, the drone may slip during landing or placement, especially on smooth or slippery surfaces. This slippage can not only cause instability and tilting of the drone, but also potentially lead to equipment damage or inaccurate data acquisition. Furthermore, slippage may cause the drone to deviate from the intended landing position, increasing the difficulty for the operator to reposition and control the drone, and affecting operational efficiency. To address these problems, this utility model adopts an anti-slip protrusion structure. When the drone lands, the buffer structure base contacts the ground first. Because the anti-slip protrusions are arranged in an array on the bottom of the buffer structure base, these protrusions... The blocks increase the friction between the base and the ground. The anti-slip bumps are made of silicone, which has good elasticity and wear resistance. It can provide sufficient friction while reducing damage to the ground. When the drone lands on a smooth or wet surface, these silicone anti-slip bumps can effectively prevent the cushioning base from sliding, thereby ensuring the stability and safety of the drone. This can significantly improve the stability of the drone when landing or placing it, especially on smooth or wet surfaces. This improvement can effectively prevent the drone from sliding and tilting, reduce the risk of equipment damage, and ensure the accuracy of data collection.

[0008] Preferably, both the first and second sliding rods have smooth surfaces. During buffering, the smooth surfaces of both sliding rods ensure smoother sliding within the sliding seat and groove, reducing friction during sliding and allowing the buffer structure to operate more smoothly and efficiently when absorbing impact forces.

[0009] Preferably, the surface of the hook is smooth. A smooth hook surface reduces friction with the hook groove at the bottom of the battery compartment, making it easier for the hook to slide into and out of the groove, thereby simplifying the locking and unlocking process of the battery compartment. Reduced friction helps to reduce noise during operation and reduces wear between the hook and the groove, extending the service life of the component.

[0010] Preferably, the top mount of the buffer structure is detachably fixed to the bottom of the drone base. This allows users to quickly and easily install or remove the buffer structure, facilitating maintenance and replacement. Especially when the buffer structure is damaged or needs upgrading, this modular design allows the buffer structure to be replaced according to different usage scenarios and requirements, improving the adaptability and flexibility of the drone.

[0011] Preferably, both the top seat and the base of the buffer structure are made of carbon fiber. This achieves the effect of reducing weight and enhancing structural strength. Carbon fiber is known for its lightweight, high strength, and high rigidity. Therefore, using carbon fiber can significantly reduce the overall weight of the UAV, thereby improving flight efficiency and endurance. At the same time, the high strength of carbon fiber also ensures the durability and reliability of the buffer structure when absorbing shocks and vibrations, helping to protect the critical components of the UAV from damage.

[0012] Beneficial effects: 1. In existing technologies, multi-rotor drones lacking a buffer structure significantly increase the impact risk during landing. When a drone lands in complex terrain or in an emergency, without the protection of a buffer structure, the fuselage and critical components may be damaged by the instantaneous high impact force. Precision equipment such as cameras and sensors may be displaced or damaged due to vibration, leading to data acquisition failure or blurred images. In addition, frequent high-impact landings accelerate the wear of mechanical parts and reduce the service life of the drone. To address these issues, this utility model adopts a buffer structure, which can significantly reduce the impact risk during landing and protect the fuselage and critical components from damage caused by instantaneous high impact forces. This not only prevents precision equipment such as cameras and sensors from being displaced or damaged due to vibration, ensuring the accuracy of data acquisition and the clarity of images, but also reduces the wear of mechanical parts caused by frequent high-impact landings, thereby extending the service life of the drone. It also improves the adaptability and reliability of the drone in complex terrain or emergency situations, enhances its stability and durability in various environments, and ultimately improves the overall performance and economic benefits of the drone. 2. In existing technologies, if the battery design of multi-rotor drones is not easily replaceable, it will bring a series of inconveniences. When the battery is depleted, users may need to wait for a long time to recharge, which limits the drone's continuous operation capability and affects work efficiency. For application scenarios that require long-term or frequent task execution, such as agricultural monitoring and logistics delivery, inconvenient battery replacement will greatly increase the complexity of operation and reduce the flexibility of task execution. To address this problem, this utility model adopts a convenient battery replacement structure, which can significantly improve the drone's operating efficiency and flexibility. By realizing a fast and simple battery replacement mechanism, users can quickly replace the battery when it is depleted, thereby reducing the waiting time for charging and ensuring that the drone can continue to perform tasks. This not only improves the drone's continuous operation capability, but also enhances its adaptability in scenarios that require long-term or frequent task execution, such as agricultural monitoring and logistics delivery.

[0013] 3. In existing technologies, if the bottom of the buffer device lacks anti-slip measures, the drone may slip during landing or placement, especially on smooth or slippery surfaces. This slippage can not only cause instability and tilting of the drone, but also lead to equipment damage or inaccurate data collection. In addition, slippage may cause the drone to deviate from the intended landing position, increasing the difficulty for the operator to reposition and control the drone, and affecting work efficiency. To address these issues, this utility model adopts an anti-slip protrusion structure, which can significantly improve the stability of the drone during landing or placement, especially on smooth or slippery surfaces. This improvement effectively prevents the drone from slipping and tilting, reduces the risk of equipment damage, and ensures the accuracy of data collection. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural diagram of the present invention; Figure 2 This is an exploded view of the buffer structure of this utility model; Figure 3 This is a cross-sectional view of the buffer structure of this utility model; Figure 4 This is a three-dimensional structural diagram of the buffer structure of this utility model; Figure 5 An exploded view of the battery replacement structure of this utility model; Figure 6 A cross-sectional view of the battery replacement structure of this utility model; Figure 7 for Figure 6 Enlarged view of point A in the middle.

[0015] Legend: 1. UAV base; 101. UAV body; 102. Buffer structure top seat; 103. Buffer structure base; 104. Sliding seat; 105. Sliding rod one; 106. Sliding inner shell; 107. Sliding outer shell; 108. Buffer spring; 109. Circular groove; 110. Sliding rod two; 2. Component slot one; 201. Battery box; 202. Power supply battery; 203. Component slot two; 204. Drive seat; 205. Drive spring; 206. Component slot three; 207. Adjustment handle; 208. Hook; 209. Reset spring; 210. Hook groove; 3. Anti-slip protrusion. Detailed Implementation

[0016] To make the technical means, creative features, and achieved objectives and effects of this utility model easier to understand, the present utility model is further described below with reference to specific embodiments and accompanying drawings. However, the following embodiments are merely preferred embodiments of this utility model and not all of them. Other embodiments obtained by those skilled in the art based on the embodiments described in the implementation plan without creative effort are all within the protection scope of this utility model.

[0017] The specific embodiments of this utility model are described below with reference to the accompanying drawings. Specific implementation examples: Reference Figure 1-7A carbon fiber buffer structure for a multi-rotor drone includes a drone base 1, a drone body 101 on top of the drone base 1, a power supply battery 202 inside the drone base 1, a buffer structure top seat 102 at the bottom of the drone base 1, a buffer structure base 103 at the bottom of the buffer structure top seat 102, a sliding seat 104 fixed to the bottom of the buffer structure top seat 102, and a sliding rod 105 fixed to the top of the buffer structure base 103. The sliding rod 105 is slidably connected to the inner wall of the sliding seat 104. The bottom of the buffer structure top seat 102 is fixed with a sliding inner shell 106, the top of the buffer structure base 103 is fixed with a sliding outer shell 107, the sliding inner shell 106 is slidably connected to the inner wall of the sliding outer shell 107, the top of the buffer structure base 103 is fixed with a buffer spring 108, the other end of the buffer spring 108 is fixed to the bottom of the sliding seat 104, the top of the buffer structure top seat 102 is provided with a through groove 109, the inner wall of the groove 109 is slidably connected with a sliding rod 110, and the sliding rod 110 is fixed to the top of the buffer structure base 103. In existing technologies, the lack of a buffer structure in multi-rotor drones significantly increases the impact risk during landing. When a drone lands in complex terrain or in an emergency, without the protection of a buffer structure, the fuselage and critical components may be damaged by the instantaneous high impact force. Precision equipment such as cameras and sensors may be displaced or damaged due to vibration, leading to data acquisition failure or blurred images. In addition, frequent high-impact landings will accelerate the wear of mechanical parts and reduce the service life of the drone. To address these issues, this utility model adopts a buffer structure. When the drone 101 lands, the buffer structure base 103 first contacts the ground, and the buffer spring 108 at its top begins to compress. During compression, sliding rod 105 slides within sliding seat 104, while sliding inner shell 106 slides within sliding outer shell 107. These two sliding processes work together to absorb and disperse the impact force. In addition, sliding rod 110, which is slidably connected to the inner wall of the circular groove 109 at the top of the buffer structure top seat 102, also participates in the buffering process. It is fixed to the top of the buffer structure base 103, further enhancing the stability and impact absorption capacity of the entire buffer structure. This design, through the synergistic effect of multiple sliding and spring buffer elements, effectively reduces the impact on the drone body 101 during landing, protecting key components of the drone, such as the power supply battery 202 and the drone body 101 itself.

[0019] The drone base 1 has a component slot 1 2 on one side. A battery box 201 is slidably connected to the inner wall of the component slot 1 2. A power supply battery 202 is located on the inner wall of the battery box 201. A component slot 203 is opened on the inner wall of the component slot 1 2. A drive seat 204 is fixed to the bottom of the battery box 201. A drive spring 205 is fixed to one side of the drive seat 204. The other end of the drive spring 205 is fixed to the inner wall of the component slot 2 203. A component slot 3 206 is opened on the inner wall of the component slot 2 203. An adjustment handle 207 is rotatably connected to the inner wall of the component slot 3 206. A hook 208 is fixed to one end of the adjustment handle 207. A return spring 209 is fixed to the surface of the adjustment handle 207. The other end of the return spring 209 is fixed to the inner wall of the component slot 2 203. A hook groove 210 is opened at the bottom of the battery box 201. The hook 208 is located on the inner wall of the hook groove 210. In existing technologies, if the battery design of a multi-rotor drone is not convenient to replace, it will bring a series of inconveniences. When the battery is depleted, the user may have to wait for a long time to recharge, which limits the drone's continuous operation capability and affects work efficiency. For application scenarios that require long-term or frequent task execution, such as agricultural monitoring and logistics delivery, inconvenient battery replacement will greatly increase the complexity of operation and reduce the flexibility of task execution. To address this problem, this utility model adopts a convenient battery replacement structure. Pulling the adjustment handle 207 will cause the hook 208 to disengage from the hook groove 210. At this time, the elastic force of the drive spring 205 will push the battery box 201 to slide outward, thereby realizing the rapid ejection of the battery box 201 and its internal battery 202. This allows the user to easily and quickly replace the battery without the use of any tools, greatly improving the convenience of battery replacement. At the same time, the setting of the drive spring 205 and the return spring 209 also ensures the stability and reliability of the battery box 201 during the installation and ejection process.

[0020] The bottom of the buffer structure base 103 is fixed with anti-slip protrusions 3, which are arranged in an array on the bottom of the buffer structure base 103. The anti-slip protrusions 3 are made of silicone material. In existing technologies, if the bottom of the buffer device lacks anti-slip measures, the drone may slip during landing or placement, especially on smooth or slippery surfaces. This slippage can not only cause instability and tilting of the drone, but also lead to equipment damage or inaccurate data acquisition. Furthermore, slippage may cause the drone to deviate from the intended landing position, increasing the difficulty for the operator to reposition and control the drone, and affecting operational efficiency. To address these issues, this invention employs an anti-slip bump structure. When the drone lands, the buffer structure base 103 first contacts the ground. Since the anti-slip bumps 3 are arranged in an array on the bottom of the buffer structure base 103, these bumps can increase the friction between the base and the ground. The anti-slip bumps 3 are made of silicone material, which has good elasticity and wear resistance, and can provide sufficient friction while reducing damage to the ground. When the drone lands on a smooth or slippery surface, these silicone anti-slip bumps 3 can effectively prevent the buffer structure base 103 from slipping, thereby ensuring the stability and safety of the drone.

[0021] The surfaces of sliding rod 105 and sliding rod 110 are smooth. During buffering, the smooth surfaces of sliding rod 105 and sliding rod 110 ensure smoother sliding within the sliding seat 104 and circular groove 109, reducing friction during sliding. This allows the buffer structure to operate more smoothly and efficiently when absorbing impact. The smooth surface of hook 208 reduces friction with the bottom groove 210 of the battery box 201, making it easier for hook 208 to slide in and out of the groove 210, simplifying the locking and unlocking process of the battery box. Reduced friction helps reduce operating noise and wear between hook 208 and groove 210, extending the service life of the components. The top seat 102 of the buffer structure can... The buffer structure, which is detached and fixed to the bottom of the drone base 1, allows users to quickly and easily install or remove it, facilitating maintenance and replacement. Especially when the buffer structure is damaged or needs to be upgraded, this modular design allows the buffer structure to be replaced according to different usage scenarios and needs, improving the adaptability and flexibility of the drone. Both the top mount 102 and the base 103 of the buffer structure are made of carbon fiber, achieving the effect of reducing weight and enhancing structural strength. Carbon fiber is known for its lightweight, high strength, and high rigidity. Therefore, using carbon fiber can significantly reduce the overall weight of the drone, thereby improving flight efficiency and endurance. At the same time, the high strength of carbon fiber also ensures the durability and reliability of the buffer structure when absorbing shocks and vibrations, helping to protect the key components of the drone from damage.

[0022] The working principle of this utility model is as follows: When the drone 101 lands, the buffer structure base 103 first contacts the ground, and the buffer spring 108 at its top begins to compress. As the spring 108 is compressed, the sliding rod 105 slides within the sliding seat 104, while the inner sliding shell 106 slides within the outer sliding shell 107. These two sliding processes work together to absorb and disperse the impact force. In addition, the sliding rod 110, which is slidably connected to the inner wall of the circular groove 109 at the top of the buffer structure top seat 102, also participates in the buffering process. It is fixed to the top of the buffer structure base 103, further enhancing the stability and impact absorption capacity of the entire buffer structure. This design, through the synergistic effect of multiple sliding and spring buffering elements, effectively reduces the impact on the drone body 101 during landing, protecting key components of the drone, such as the power supply battery 202 and the drone body 101 itself. Pulling the adjustment handle 207 will cause the hook 208 to disengage from the hook groove 210, at which point the drive spring... The elastic force of 205 pushes the battery box 201 outward, thereby enabling the battery box 201 and its internal battery 202 to pop out quickly. This allows users to easily and quickly replace the battery without using any tools, greatly improving the convenience of battery replacement. At the same time, the setting of the drive spring 205 and the return spring 209 also ensures the stability and reliability of the battery box 201 during installation and pop-out. When the drone lands, the buffer structure base 103 contacts the ground first. Since the anti-slip protrusions 3 are arranged in an array on the bottom of the buffer structure base 103, these protrusions can increase the friction between the base and the ground. The anti-slip protrusions 3 are made of silicone material. Silicone has good elasticity and wear resistance, which can provide sufficient friction while reducing damage to the ground. When the drone lands on a smooth or slippery surface, these silicone anti-slip protrusions 3 can effectively prevent the buffer structure base 103 from sliding, thereby ensuring the stability and safety of the drone.

[0023] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0024] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely preferred examples and are not intended to limit the utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A carbon fiber buffer structure for a multi-rotor unmanned aerial vehicle (UAV), comprising a UAV base (1), a UAV body (101) on top of the UAV base (1), and a power supply battery (202) inside the UAV base (1), characterized in that: The UAV base (1) has a buffer structure top seat (102) at its bottom, a buffer structure base (103) at its bottom, a sliding seat (104) fixed at the bottom of the buffer structure top seat (102), and a sliding rod (105) fixed at the top of the buffer structure base (103). The sliding rod (105) is slidably connected to the inner wall of the sliding seat (104). A sliding inner shell (106) is fixed at the bottom of the buffer structure top seat (102), and the top of the buffer structure base (103) is... A sliding outer shell (107) is fixed to the part, and the sliding inner shell (106) is slidably connected to the inner wall of the sliding outer shell (107). A buffer spring (108) is fixed to the top of the buffer structure base (103), and the other end of the buffer spring (108) is fixed to the bottom of the sliding seat (104). A circular groove (109) is opened through the top of the buffer structure top seat (102), and a sliding rod (110) is slidably connected to the inner wall of the circular groove (109). The sliding rod (110) is fixed to the top of the buffer structure base (103).

2. The carbon fiber buffer structure for a multi-rotor unmanned aerial vehicle according to claim 1, characterized in that: The UAV base (1) has a component slot 1 (2) on one side. A battery box (201) is slidably connected to the inner wall of the component slot 1 (2). The power supply battery (202) is located on the inner wall of the battery box (201). A component slot 2 (203) is opened on the inner wall of the component slot 1 (2). A drive seat (204) is fixed to the bottom of the battery box (201). A drive spring (205) is fixed to one side of the drive seat (204). The other end of the drive spring (205) is fixed to the inner wall of the component slot 2 (203). The inner wall of the component slot two (203) is provided with a component slot three (206). An adjustment handle (207) is rotatably connected to the inner wall of the component slot three (206). A hook (208) is fixed to one end of the adjustment handle (207). A reset spring (209) is fixed to the surface of the adjustment handle (207). The other end of the reset spring (209) is fixed to the inner wall of the component slot two (203). A hook groove (210) is provided at the bottom of the battery box (201). The hook (208) is located on the inner wall of the hook groove (210).

3. The carbon fiber buffer structure for a multi-rotor unmanned aerial vehicle according to claim 1, characterized in that: The bottom of the buffer structure base (103) is fixed with anti-slip protrusions (3), which are arranged in an array on the bottom of the buffer structure base (103). The anti-slip protrusions (3) are made of silicone material.

4. A carbon fiber buffer structure for a multi-rotor unmanned aerial vehicle according to claim 1, characterized in that: The surface of the first sliding rod (105) is smooth, and the surface of the second sliding rod (110) is smooth.

5. A carbon fiber buffer structure for a multi-rotor unmanned aerial vehicle according to claim 2, characterized in that: The surface of the hook (208) is smooth.

6. A carbon fiber buffer structure for a multi-rotor unmanned aerial vehicle according to claim 1, characterized in that: The buffer structure top seat (102) can be detachably fixed to the bottom of the UAV base (1).

7. A carbon fiber buffer structure for a multi-rotor unmanned aerial vehicle according to claim 1, characterized in that: Both the top seat (102) and the base (103) of the buffer structure are made of carbon fiber.

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