Carbon fiber take-off and landing device for drones

Abstract

The utility model provides a carbon fiber take -off and landing device for unmanned plane relates to unmanned plane technical field, including unmanned plane base, the unmanned plane base top is fixed with unmanned plane main part, is equipped with the propeller module in unmanned plane main part top, is equipped with take -off and landing device side board 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 take-off and landing device for UAVs. Background Technology

[0002] Drones are high-tech unmanned aerial vehicles that fly by remote control or pre-programmed procedures. They are small, highly flexible, and can maneuver freely in complex environments. In aerial photography, drones can easily capture spectacular scenery and unique perspectives, greatly facilitating film and television production and tourism promotion. They also have wide applications in agriculture, logistics, and power line inspection. For example, they help farmers with precise plant protection operations, assist the logistics industry in achieving rapid delivery of goods, and efficiently inspect power lines to promptly identify potential hazards. The development of drones has not only promoted the advancement of related technologies but also brought numerous conveniences to people's lives and work, demonstrating broad application prospects.

[0003] In existing technologies, the size of the take-off and landing device at the bottom of the drone cannot be adjusted, which has many drawbacks. There are a large number of drones of different sizes, from micro to large, with a wide range of applications. However, the size of the take-off and landing device is fixed and cannot be adapted to drones of different sizes. This greatly reduces its versatility. When a small drone uses a large take-off and landing device, the size mismatch may lead to unstable take-off and landing, or even damage to the device. On the other hand, if a large drone uses a small take-off and landing device, it may not be able to take off and land safely due to insufficient support. This mismatch problem not only increases the risk of take-off and landing, but also limits the flexible application of drones in different scenarios. Utility Model Content

[0004] The purpose of this invention is to address the shortcomings of existing technologies by proposing a carbon fiber take-off and landing device for unmanned aerial vehicles (UAVs).

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a carbon fiber take-off and landing device for unmanned aerial vehicles (UAVs), comprising a UAV base, a UAV body fixed to the top of the UAV base, a propeller module on the top of the UAV body, a take-off and landing device side plate one on one side of the UAV base, and a take-off and landing device side plate two on the other side of the UAV base. A component seat one is fixed to one side of the take-off and landing device side plate one, and a sliding rod is fixed to one side of the component seat one. A component seat two is fixed to the side of the take-off and landing device side plate two near the side plate one. A sliding groove is formed inside the component seat two, and the sliding rod slides on the inner wall of the sliding groove. A support base is fixed to one end of the sliding rod, and a spring is provided on the surface of the sliding rod. One end of the spring is fixed to one side of the support base, and the other end of the spring is fixed to the inner wall of the sliding groove. A central support frame is fixed to the bottom of both the take-off and landing device side plate one and the take-off and landing device side plate two, and a take-off and landing device base is fixed to the bottom of the central support frame.

[0006] Preferably, the propeller module surface is provided with an anti-collision ring, and a support rod is fixed to the bottom of the anti-collision ring. The support rods are arranged in an array, and a mounting seat is fixed to the bottom of the support rod. The mounting seat is located on the surface of the propeller module, and a first thread is formed on the inner wall of the mounting seat. A second thread is formed on the surface of the propeller module, and the mounting seat is threaded to the surface of the propeller module. In the prior art, the protection measures for the surface of UAV propellers have some drawbacks. Fixed protective covers may increase wind resistance, affecting the flight efficiency and battery life of the UAV in open areas. On the other hand, without protection measures, the propeller is easily damaged when flying in complex areas, increasing maintenance costs and flight risks. To address these issues, this utility model adopts a detachable propeller protection structure. An anti-collision ring is set on the surface of the propeller module, and an array of support rods is fixed to the bottom of the anti-collision ring. A mounting seat is fixed to the bottom of these support rods, and the mounting seat is directly located on the surface of the propeller module. To achieve a fixed connection between the mounting seat and the propeller module, a first thread is formed on the inner wall of the mounting seat, and the second thread is threaded to the surface of the propeller module. The propeller module surface has corresponding threaded lines. Through the cooperation of these two threaded lines, the mounting base can be threadedly connected to the propeller module surface, forming a stable protective structure. This allows the anti-collision ring to be easily removed when needed, reducing wind resistance when flying in open areas, while providing necessary protection in complex environments to prevent the propeller from being hit and damaged. This allows for flexible adjustment of protective measures in different flight environments to adapt to different flight conditions. When flying in open areas, the protective cover can be removed to reduce wind resistance, improve flight efficiency and battery life. When flying in complex areas, the protective cover can be installed to effectively prevent the propeller from being hit and damaged, reducing maintenance costs and flight risks.

[0007] Preferably, the first and second side plates of the take-off and landing device are detachably fixed to both sides of the UAV base, and the UAV base is located on top of the first and second component bases. In the prior art, the design of fixing the take-off and landing device to the bottom of the UAV has some drawbacks. Fixed take-off and landing devices may increase space occupation during transportation and storage, making them inconvenient to carry and deploy. This design also hinders the modularity and standardization of the UAV, limiting its versatility in various application scenarios. To address these issues, this utility model adopts a detachable take-off and landing device structure, which can significantly improve the portability, adaptability, and versatility of the UAV. By adopting a detachable or foldable take-off and landing device design, the space occupied by the UAV during transportation and storage will be greatly reduced, facilitating carrying and rapid deployment. The modular design allows the take-off and landing device to be replaced or upgraded according to different application scenarios and mission requirements, enhancing the flexibility and expandability of the UAV.

[0008] Preferably, a first buffer pad is fixed to one side of the first side plate of the take-off and landing device, and a second buffer pad is fixed to one side of the second side plate of the take-off and landing device. The buffer pads can provide additional cushioning during the take-off and landing of the UAV, reducing the impact and vibration caused by hard landing or uneven ground, thereby protecting the structural safety of the UAV, extending its service life, enhancing the UAV's adaptability to various ground conditions, enabling it to take off and land stably in more diverse environments, and improving operational flexibility and reliability.

[0009] Preferably, the inner wall of the sliding groove is smooth, and the surface of the sliding rod is smooth. This reduces friction and wear. The smooth contact surface reduces the resistance when the sliding rod moves within the sliding groove, making the adjustment of the support seat smoother and more precise, improving the operational flexibility of the entire lifting device. At the same time, reducing friction also helps to reduce wear on the lifting device during long-term use, extending the service life of components and reducing maintenance needs and related costs.

[0010] Preferably, the base of the take-off and landing device has anti-slip grooves on its bottom, and these grooves are arranged in an array. This significantly improves the stability and anti-slip performance of the UAV under various ground conditions. The anti-slip grooves increase the friction between the base and the ground, thereby reducing the risk of the UAV sliding or tipping over during take-off and landing. Especially on wet or uneven ground, the arrayed anti-slip grooves can distribute the friction more evenly, further enhancing stability.

[0011] Preferably, the first and second side plates of the take-off and landing device, the central support frame, and the base of the take-off and landing device are all made of carbon fiber. Using carbon fiber reduces overall weight, enhances structural strength, and improves durability. Carbon fiber is known for its lightweight and high strength, which helps reduce the drone's load, potentially improving flight efficiency and battery life. The high strength and rigidity of carbon fiber also help maintain the structural stability of the take-off and landing device, enabling it to withstand greater impacts and pressures without deformation or damage.

[0012] Beneficial effects: 1. In existing technologies, the size of the take-off and landing device at the bottom of a drone cannot be adjusted, which has many drawbacks. There are numerous drones of different sizes, ranging from micro to large, with a wide range of applications. However, the fixed size of the take-off and landing device cannot be adapted to drones of different sizes, which greatly reduces its versatility. When a small drone uses a large take-off and landing device, the size mismatch may lead to unstable take-off and landing, or even device damage. On the other hand, if a large drone uses a small take-off and landing device, it may fail to take off and land safely due to insufficient support. This mismatch not only increases the risk of take-off and landing but also limits the flexible application of drones in different scenarios. To address these issues, this utility model adopts an adjustable take-off and landing device to enhance the versatility of the device, enabling a single device to adapt to drones of various sizes, thereby reducing costs and simplifying inventory management. By ensuring a precise match between the take-off and landing device and the drone size, the stability and safety of take-off and landing can be significantly improved, reducing the risk of device damage and take-off and landing failures due to size mismatch. This adjustable design also allows drones to be used flexibly in more diverse application scenarios, ensuring safe and efficient take-off and landing operations in both confined spaces and open areas.

[0013] 2. Existing technologies have some drawbacks in the protection measures for the surface of drone propellers. Fixed protective covers may increase wind resistance, affecting the drone's flight efficiency and battery life in open areas. On the other hand, drones without protective measures are prone to propeller damage when flying in complex areas, increasing maintenance costs and flight risks. To address these issues, this utility model adopts a detachable propeller protection structure, which allows for flexible adjustment of protection measures in different flight environments to adapt to different flight conditions. When flying in open areas, the protective cover can be removed to reduce wind resistance and improve flight efficiency and battery life. When flying in complex areas, the protective cover can be installed to effectively prevent the propeller from being hit and damaged, reducing maintenance costs and flight risks.

[0014] 3. In the existing technology, the design of the take-off and landing device fixed to the bottom of the drone has some drawbacks. The fixed take-off and landing device may increase the space occupied during transportation and storage, which is not conducive to carrying and deployment. This design is also not conducive to the modularity and standardization of the drone, and limits its versatility in various application scenarios. To address these issues, this utility model adopts a detachable take-off and landing device structure, which can significantly improve the portability, adaptability and versatility of the drone. By adopting a detachable or foldable take-off and landing device design, the space occupied by the drone during transportation and storage will be greatly reduced, making it easier to carry and deploy quickly. The modular design allows the take-off and landing device to be replaced or upgraded according to different application scenarios and task requirements, enhancing the flexibility and expandability of the drone. Attached Figure Description

[0015] Figure 1 This is a three-dimensional structural diagram of the present invention; Figure 2 This is a three-dimensional structural diagram of the adjustable take-off and landing device of this utility model; Figure 3 This is a cross-sectional view of the adjustable take-off and landing device of this utility model; Figure 4 This is an exploded view of the detachable propeller protection structure of this utility model.

[0016] Legend: 1. UAV base; 101. UAV body; 102. Propeller module; 103. Take-off and landing device side plate one; 104. Take-off and landing device side plate two; 105. Component seat one; 106. Component seat two; 107. Sliding rod; 108. Sliding groove; 109. Support seat; 110. Spring; 111. Central support frame; 112. Take-off and landing device base; 2. Anti-collision ring; 201. Support rod; 202. Mounting seat; 203. Thread one; 204. Thread two; 3. Buffer pad one; 301. Buffer pad two. Detailed Implementation

[0017] 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.

[0018] The specific embodiments of this utility model are described below with reference to the accompanying drawings. Specific implementation examples: Reference Figure 1-4A carbon fiber take-off and landing device for unmanned aerial vehicles (UAVs) includes a UAV base 1, a UAV body 101 fixed to the top of the UAV base 1, a propeller module 102 mounted on the top of the UAV body 101, a take-off and landing device side plate 103 on one side of the UAV base 1, and a take-off and landing device side plate 104 on the other side of the UAV base 1. A component base 105 is fixed to one side of the take-off and landing device side plate 103, and a sliding rod 107 is fixed to one side of the component base 105. The side plate 104 of the take-off and landing device is fixed near the side plate 103. There is a component base 106, and a sliding groove 108 is provided inside the component base 106. The sliding rod 107 slides on the inner wall of the sliding groove 108. One end of the sliding rod 107 is fixed to a support base 109. A spring 110 is provided on the surface of the sliding rod 107. One end of the spring 110 is fixed to one side of the support base 109, and the other end of the spring 110 is fixed to the inner wall of the sliding groove 108. The bottom of the lifting device side plate 103 and the lifting device side plate 2 104 are both fixed with a central support frame 111. The bottom of the central support frame 111 is fixed with a lifting device base 112. In existing technologies, the size of the take-off and landing device on the bottom of a drone cannot be adjusted, which has many drawbacks. There are numerous drones of different sizes, ranging from micro to large, with a wide range of applications. However, the fixed size of the take-off and landing device makes it impossible to adapt to drones of different sizes, significantly reducing its versatility. When a small drone uses a large take-off and landing device, the size mismatch may lead to unstable take-off and landing, or even device damage. Conversely, if a large drone uses a small take-off and landing device, it may fail to take off and land safely due to insufficient support. This mismatch not only increases the risk of take-off and landing but also limits the flexible application of drones in different scenarios. To address these issues, this paper… The new adjustable take-off and landing device allows for adjustments to accommodate different sized drones. Pulling side plate 103 and side plate 104 causes the sliding rod 107 to slide within the sliding groove 108, thereby moving the support base 109. The movement of the support base 109 is controlled by a spring 110, one end of which is fixed to one side of the support base 109, and the other end is fixed to the inner wall of the sliding groove 108, ensuring the sliding rod 107 can move smoothly and stably. Side plate 103 and side plate 104 are connected to the base 112 via a central support frame 111, forming a stable structure.

[0020] The surface of the propeller module 102 is provided with an anti-collision ring 2, and a support rod 201 is fixed at the bottom of the anti-collision ring 2. The support rods 201 are arranged in an array, and a mounting base 202 is fixed at the bottom of the support rods 201. The mounting base 202 is located on the surface of the propeller module 102. A first thread 203 is opened on the inner wall of the mounting base 202, and a second thread 204 is opened on the surface of the propeller module 102. The mounting base 202 is threadedly connected to the surface of the propeller module 102. In existing technologies, protective measures for the surface of drone propellers have some drawbacks. Fixed protective covers may increase wind resistance, affecting the drone's flight efficiency and battery life in open areas. Drones without protective measures are more susceptible to propeller damage when flying in complex terrain, increasing maintenance costs and flight risks. To address these issues, this invention employs a detachable propeller protection structure. This involves setting an anti-collision ring 2 on the surface of the propeller module 102. The bottom of the anti-collision ring 2 is fixed with an array of support rods 201, and the bottom of these support rods 201 is fixed with mounting bases 202. Mounting bracket 202 is directly mounted on the surface of propeller module 102. In order to achieve a fixed connection between mounting bracket 202 and propeller module 102, the inner wall of mounting bracket 202 is provided with thread 203, and the surface of propeller module 102 is provided with corresponding thread 204. Through the cooperation of these two threads, mounting bracket 202 can be threadedly connected to the surface of propeller module 102, forming a stable protective structure. This allows anti-collision ring 2 to be easily disassembled when needed to reduce wind resistance when flying in open areas, while providing necessary protection in complex environments to prevent the propeller from being hit and damaged.

[0021] The first and second side plates 103 and 104 of the take-off and landing device are detachably fixed to both sides of the UAV base 1, which is located on top of the first component base 105 and the second component base 106. In the prior art, the design of fixing the take-off and landing device to the bottom of the UAV has some drawbacks. Fixed take-off and landing devices may increase space occupation during transportation and storage, making them inconvenient to carry and deploy. This design also hinders the modularity and standardization of the UAV, limiting its versatility in various application scenarios. To address these issues, this utility model adopts a detachable take-off and landing device structure, which can significantly improve the portability, adaptability, and versatility of the UAV. By adopting a detachable or foldable take-off and landing device design, the space occupied by the UAV during transportation and storage will be greatly reduced, facilitating carrying and rapid deployment. The modular design allows the take-off and landing device to be replaced or upgraded according to different application scenarios and mission requirements, enhancing the flexibility and expandability of the UAV.

[0022] A buffer pad 3 is fixed to one side of the landing gear side plate 103, and a buffer pad 301 is fixed to one side of the landing gear side plate 104. The buffer pads provide additional cushioning during UAV takeoff and landing, reducing impact and vibration caused by hard landings or uneven ground, thus protecting the UAV's structural safety, extending its service life, and enhancing its adaptability to various ground conditions. This allows the UAV to take off and land stably in more diverse environments, improving operational flexibility and reliability. The inner wall of the sliding groove 108 and the surface of the sliding rod 107 are smooth, reducing friction and wear. The smooth contact surface reduces the resistance when the sliding rod moves within the sliding groove, making the adjustment of the support base 109 smoother and more precise, improving the overall operational flexibility of the landing gear. Simultaneously, reduced friction also helps reduce wear during long-term use, extending the service life of components, reducing maintenance needs and related costs. The landing gear base 112 has an opening at its bottom. The anti-slip texture, arranged in an array, significantly improves the stability and anti-slip performance of the drone under various ground conditions. The texture increases friction between the base and the ground, reducing the risk of slipping or tipping over during takeoff and landing. Especially on wet or uneven surfaces, the arrayed texture distributes friction more evenly, further enhancing stability. The landing gear side plate 103, landing gear side plate 104, central support frame 111, and landing gear base 112 are all made of carbon fiber. This design reduces overall weight, enhances structural strength, and improves durability. Carbon fiber is known for its lightweight and high strength, which helps reduce the drone's load, potentially improving flight efficiency and battery life. The high strength and rigidity of carbon fiber also help maintain the structural stability of the landing gear, allowing it to withstand greater impacts and pressures without deformation or damage.

[0023] The working principle of this utility model is as follows: When the take-off and landing device needs to be adjusted to accommodate drones of different sizes, pull the first take-off and landing device side plate 103 and the second take-off and landing device side plate 104. The sliding rod 107 slides in the sliding groove 108, thereby driving the support base 109 to move. The movement of the support base 109 is controlled by the spring 110. One end of the spring 110 is fixed to one side of the support base 109, and the other end is fixed to the inner wall of the sliding groove 108, ensuring that the sliding rod 107 can move smoothly and stably. The first take-off and landing device side plate 103 and the second take-off and landing device side plate 104 are connected by the central support frame 111 and the take-off and landing device base 112 to form a stable structure. By setting an anti-collision ring 2 on the surface of the propeller module 102, the bottom of the anti-collision ring 2... The propeller module 102 is fixed with an array of support rods 201. The bottom of these support rods 201 is fixed with a mounting base 202. The mounting base 202 is directly disposed on the surface of the propeller module 102. In order to achieve a fixed connection between the mounting base 202 and the propeller module 102, a thread 203 is provided on the inner wall of the mounting base 202, and a corresponding thread 204 is provided on the surface of the propeller module 102. Through the cooperation of these two threads, the mounting base 202 can be threadedly connected to the surface of the propeller module 102, forming a stable protective structure. This allows the anti-collision ring 2 to be easily disassembled when needed to reduce wind resistance when flying in open areas, while providing necessary protection in complex environments to prevent the propeller from being hit and damaged.

[0024] 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.

[0025] 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 take-off and landing device for a drone, comprising a drone base (1), wherein a drone body (101) is fixed to the top of the drone base (1), and a propeller module (102) is provided on the top of the drone body (101), characterized in that: The UAV base (1) has a landing device side plate 1 (103) on one side and a landing device side plate 2 (104) on the other side. A component seat 1 (105) is fixed to one side of the landing device side plate 1 (103), and a sliding rod (107) is fixed to one side of the component seat 1 (105). A component seat 2 (106) is fixed to the side of the landing device side plate 2 (104) near the landing device side plate 1 (103). A sliding groove (108) is provided inside the component seat 2 (107). 7) Sliding on the inner wall of the sliding groove (108), one end of the sliding rod (107) is fixed with a support seat (109), the surface of the sliding rod (107) is provided with a spring (110), one end of the spring (110) is fixed to one side of the support seat (109), and the other end of the spring (110) is fixed to the inner wall of the sliding groove (108). The bottom of the first side plate (103) and the second side plate (104) of the lifting device are both fixed with a middle support frame (111), and the bottom of the middle support frame (111) is fixed with a lifting device base (112).

2. The carbon fiber take-off and landing device for unmanned aerial vehicles according to claim 1, characterized in that: The surface of the propeller module (102) is provided with an anti-collision ring (2), and a support rod (201) is fixed at the bottom of the anti-collision ring (2). The support rods (201) are arranged in an array, and a mounting seat (202) is fixed at the bottom of the support rods (201). The mounting seat (202) is located on the surface of the propeller module (102). A first thread (203) is opened on the inner wall of the mounting seat (202), and a second thread (204) is opened on the surface of the propeller module (102). The mounting seat (202) is threaded to the surface of the propeller module (102).

3. A carbon fiber take-off and landing device for unmanned aerial vehicles according to claim 1, characterized in that: The first and second side plates of the take-off and landing device (103) and the second side plate of the take-off and landing device (104) are detachably fixed to both sides of the UAV base (1), and the UAV base (1) is located on the top of the first component base (105) and the second component base (106).

4. A carbon fiber take-off and landing device for unmanned aerial vehicles according to claim 1, characterized in that: A buffer pad 1 (3) is fixed on one side of the first side plate (103) of the lifting device, and a buffer pad 2 (301) is fixed on one side of the second side plate (104) of the lifting device.

5. A carbon fiber take-off and landing device for unmanned aerial vehicles according to claim 1, characterized in that: The inner wall of the sliding groove (108) is smooth, and the surface of the sliding rod (107) is smooth.

6. A carbon fiber take-off and landing device for unmanned aerial vehicles according to claim 1, characterized in that: The bottom of the landing device base (112) is provided with anti-slip texture, which is arranged in an array.

7. A carbon fiber take-off and landing device for unmanned aerial vehicles according to claim 1, characterized in that: The first side plate (103), the second side plate (104), the central support frame (111), and the base (112) of the lifting and landing device are all made of carbon fiber.

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