Wing protection structure of oil-powered heavy-load unmanned aerial vehicle

Abstract

The utility model relates to the technical field of oil-powered heavy-load unmanned aerial vehicles, and discloses a wing protection structure of an oil-powered heavy-load unmanned aerial vehicle, which is provided with a protection device and an auxiliary mechanism, the protection device is used for protecting wings, and the auxiliary mechanism is used for enhancing the protection effect. The problems that wings of an existing oil-powered heavy-load unmanned aerial vehicle are lack of specially-designed protection structures in the transportation process, the unmanned aerial vehicle is usually used for executing heavy goods transportation tasks, the wings are large in size and complex in structure, various high-performance materials and precise assemblies are integrated, and therefore the unmanned aerial vehicle cannot carry out heavy goods transportation in the non-flight state. The problems that in the prior art, during the period of ground transportation or long-time parking, wings are particularly prone to being affected by external environment factors including accidental collision, physical impact, severe weather conditions and the like, and at present, most oil-powered heavy-load unmanned aerial vehicles are not provided with special wing protection devices are solved.

Description

Technical Field

[0001] This utility model belongs to the technical field of oil-powered heavy-load unmanned aerial vehicles (UAVs), and particularly relates to a wing protection structure for oil-powered heavy-load UAVs. Background Technology

[0002] Oil-powered heavy-load drones are unmanned aerial vehicles specifically designed for heavy cargo transportation. They use traditional fuel engines as their power source, rather than the more common electric systems. This design allows the drones to perform long-duration, long-distance missions without relying on ground charging facilities, and they have a large payload capacity. The high energy density provided by the oil-powered system means that the drones can carry more fuel, thereby increasing their range and operating range, making them particularly suitable for applications such as remote areas or emergency material delivery.

[0003] The wings of existing gasoline-powered heavy-payload drones lack a protective structure during transportation. The problem with the aforementioned technology is that these drones face a significant issue during transport: the lack of a specially designed protective structure for their wings. Because these drones are typically used for heavy cargo transport, their wings are not only large but also complex in construction, integrating various high-performance materials and precision components. Therefore, in non-flying states, such as during ground transport or long-term storage, these wings are particularly vulnerable to external environmental factors, including accidental collisions, physical impacts, and severe weather conditions. Currently, most gasoline-powered heavy-payload drones are not equipped with dedicated wing protection devices, leading to several problems. First, without proper protection, the wing surface may suffer scratches, dents, or other forms of mechanical damage. This damage not only affects the appearance but may also weaken structural integrity, increasing maintenance costs and time. Second, exposed electronic components and sensors are susceptible to damage from dust, moisture, and even extreme temperature changes, thus affecting the overall performance and reliability of the drone. Finally, the lack of protective measures also makes the drone more vulnerable during loading and unloading, increasing operational difficulty and risk. Utility Model Content

[0004] In view of the problems existing in the prior art, this utility model provides a wing protection structure for oil-powered heavy-load UAVs that can overcome or at least partially solve the above problems.

[0005] This utility model is implemented as follows: a protective structure for the wing of a fuel-powered, heavy-load unmanned aerial vehicle (UAV) includes a UAV, support rods, and a wing. The surface of the UAV is fixedly connected to the rear ends of the four support rods. The upper front end of each support rod is rotatably connected to one end of the wing. A protective device is provided on the surface of the support rod, and an auxiliary mechanism is provided inside the protective device.

[0006] The protective device is used to protect the wings;

[0007] The auxiliary mechanism is used to enhance the effectiveness of protection.

[0008] To improve operational efficiency, preferably, the protective device includes a first protective box, a second protective box, a fixed block, a fixed rod, a limiting block, a spring, and a mating block. The surface of the first protective box contacts the surface of the second protective box, the surface of the second protective box is fixedly connected to the surface of the fixed block, the inner wall of the fixed block is slidably connected to the surface of the fixed rod, the inner wall of the front end of the fixed rod contacts the lower surfaces of the two limiting blocks, the two sides of the limiting block are fixedly connected to the upper ends of the two springs, and the lower ends of the springs are fixedly connected to the inner wall of the mating block. When the fixed rod moves into position, the force of the spring will push the limiting block to automatically embed into the fixed rod, forming a stable and reliable mechanical lock, thereby providing additional safety for the drone wing.

[0009] To improve the reliability of protection, preferably, the auxiliary mechanism includes a sponge board, an elastic block, a support box, and an adjusting screw. The upper surface of the sponge board is fixedly connected to the lower surface of the elastic block, the upper surface of the elastic block is fixedly connected to the inner wall of the support box, and the upper end of the support box is rotatably connected to the lower end of the adjusting screw. The combined design of the sponge board and the elastic block can provide effective cushioning protection for the drone wing. The sponge board is soft and has good resilience, and can directly contact and wrap the wing surface to prevent damage caused by collision or friction.

[0010] To improve operational stability, preferably, a guide block is provided inside the fixing block, and the surface of the guide block is fixedly connected to the inner wall of the fixing block. The presence of the guide block provides a movement path for the fixing rod, ensuring its straightness and stability during insertion or removal when the fixing rod slides along the guide block.

[0011] To improve the fixing effect, preferably, the inner rear wall of the second protective box contacts the surface of the support rod, the surface of the mating block is fixedly connected to the front surface of the first protective box, the surface of the fixing block contacts the surface of the mating block, the surface of the limiting block is slidably connected to the inner wall of the mating block through a sliding groove, and the front end surface of the fixing rod is slidably connected to the inner wall of the mating block. The contact between the surface of the fixing block and the surface of the mating block, combined with the guiding function set in the fixing block, ensures that the fixing rod can be accurately inserted into the mating block, which enhances the reliability of the connection between the first and second protective boxes and reduces installation problems caused by improper alignment.

[0012] To improve the adaptability of protection, preferably, the surface of the sponge board is slidably connected to the inner wall of the support box. The sponge board can be finely adjusted according to the specific shape and size of the wing by sliding within the support box, so that the sponge board can better fit the surface of the wing with different shapes, ensuring wider applicability and higher protection accuracy.

[0013] To improve operational flexibility, preferably, the surfaces of the two adjusting screws are threadedly connected to the inner walls of the first and second protective boxes, the inner wall of the guide block is slidably connected to the surface of the fixed rod, the surface of the support box is slidably connected to the inner walls of the first and second protective boxes, and the lower surface of the sponge board is in contact with the surface of the wing. The support box can move freely within a certain range to adapt to wings of different sizes and shapes, thereby enhancing the applicability of the protective structure and simplifying the installation and adjustment process.

[0014] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0015] This invention utilizes a protective device, auxiliary mechanism, fixing block, fixing rod, limiting block, mating block, sponge board, support box, and adjusting screw. The protective device protects the wing, while the auxiliary mechanism enhances the protection. When the fixing rod is in place, the spring force pushes the limiting block to automatically engage with the fixing rod, forming a stable and reliable mechanical lock, thus providing additional safety for the drone wing. The combination of the sponge board and elastic block provides effective cushioning protection for the drone wing. The sponge board is soft and has good resilience, allowing it to directly contact and wrap around the wing surface, preventing damage from collisions or friction. This solves a significant problem faced by existing oil-powered, heavy-load drones during transportation: the lack of a specially designed protective structure for their wings. Since these drones are typically used for heavy cargo transportation, their wings are not only large in size, but also... Furthermore, their complex structure, integrating various high-performance materials and precision components, makes these wings particularly vulnerable to external environmental factors, including accidental collisions, physical impacts, and severe weather conditions, when not in flight, such as during ground transport or long-term storage. Currently, most gasoline-powered heavy-load UAVs are not equipped with dedicated wing protection devices, which leads to several problems. First, without proper protection, the wing surface may suffer scratches, dents, or other forms of mechanical damage. This damage not only affects the appearance but may also weaken the structural integrity, increasing maintenance costs and time. Second, exposed electronic components and sensors are susceptible to damage from dust, moisture, and even extreme temperature changes, thus affecting the overall performance and reliability of the UAV. Finally, the lack of protective measures also makes the UAV more vulnerable during loading and unloading, increasing operational difficulty and risks. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the main three-dimensional structure provided in an embodiment of the present utility model;

[0017] Figure 2 This is a three-dimensional structural diagram of the lower end of the main body provided in an embodiment of this utility model;

[0018] Figure 3 This is a three-dimensional structural diagram of the protective device provided in this embodiment of the utility model;

[0019] Figure 4 This is a three-dimensional structural diagram of the auxiliary mechanism provided in an embodiment of this utility model.

[0020] In the diagram: 1. Protective device; 101. First protective box; 102. Second protective box; 103. Fixing block; 104. Fixing rod; 105. Limiting block; 106. Spring; 107. Matching block; 2. Auxiliary mechanism; 201. Sponge board; 202. Elastic block; 203. Support box; 204. Adjusting screw; 3. Guide block; 4. UAV; 5. Support rod; 6. Wing. Detailed Implementation

[0021] To further understand the invention content, features and effects of this utility model, the following embodiments are provided, and detailed descriptions are given in conjunction with the accompanying drawings.

[0022] The structure of this utility model will now be described in detail with reference to the accompanying drawings.

[0023] like Figures 1 to 4As shown in the figure, this utility model provides a protective structure for the wing of a gasoline-powered, high-payload unmanned aerial vehicle (UAV), including a UAV 4, support rods 5, and a wing 6. The surface of the UAV 4 is fixedly connected to the rear ends of four support rods 5. The upper front end of each support rod 5 is rotatably connected to one end of the wing 6. A protective device 1 is provided on the surface of the support rods 5, and an auxiliary mechanism 2 is provided inside the protective device 1. The protective device 1 is used to protect the wing 6, and the auxiliary mechanism 2 is used to enhance the protective effect. The protective device 1 includes a first protective box 101, a second protective box 102, a fixing block 103, a fixing rod 104, a limiting block 105, a spring 106, and a mating block 107. The surface of the first protective box 101 is in contact with the surface of the second protective box 102, and the surface of the second protective box 102 is in contact with the surface of the fixing block 103. The surface is fixedly connected, the inner wall of the fixing block 103 is slidably connected to the surface of the fixing rod 104, the inner wall of the front end of the fixing rod 104 is in contact with the lower surface of the two limiting blocks 105, the two sides of the limiting blocks 105 are fixedly connected to the upper ends of the two springs 106, and the lower ends of the springs 106 are fixedly connected to the inner wall of the mating block 107. When the fixing rod 104 moves into place, the force of the springs 106 will push the limiting blocks 105 to automatically embed into the fixing rod 104, forming a stable and reliable mechanical lock, thereby providing additional safety for the wing 6 of the UAV 4. The auxiliary mechanism 2 includes a sponge plate 201, an elastic block 202, a support box 203 and an adjusting screw 204. The upper surface of the sponge plate 201 is fixedly connected to the lower surface of the elastic block 202, and the upper surface of the elastic block 202 is fixedly connected to the support box 207. 03 The inner wall is fixedly connected, and the upper end of the support box 203 is rotatably connected to the lower end of the adjusting screw 204. The combination design of the sponge board 201 and the elastic block 202 can provide effective cushioning protection for the wing 6 of the UAV 4. The sponge board 201 is soft and has good resilience, and can directly contact and wrap the surface of the wing 6 to prevent damage caused by collision or friction. A guide block 3 is provided inside the fixed block 103. The surface of the guide block 3 is fixedly connected to the inner wall of the fixed block 103. The presence of the guide block 3 provides a movement path for the fixed rod 104. When the fixed rod 104 slides along the guide block 3, it ensures its straightness and stability during insertion or removal. The rear inner wall of the second protective box 102 contacts the surface of the support rod 5, and the surface of the mating block 107 is in contact with the first protective box 10. The front surface is fixedly connected, the surface of the fixing block 103 contacts the surface of the mating block 107, the surface of the limiting block 105 is slidably connected to the inner wall of the mating block 107 through a sliding groove, the front end surface of the fixing rod 104 is slidably connected to the inner wall of the mating block 107, and the contact between the surface of the fixing block 103 and the surface of the mating block 107, combined with the guiding function set in the fixing block 103, ensures that the fixing rod 104 can be accurately inserted into the mating block 107, which enhances the reliability of the connection between the first protective box 101 and the second protective box 102 and reduces installation problems caused by improper alignment. The surface of the sponge plate 201 is slidably connected to the inner wall of the support box 203. The sponge plate 201 can be finely adjusted according to the specific shape and size of the wing 6 by sliding within the support box 203.This design allows the sponge board 201 to better conform to the surfaces of wings 6 with different shapes, ensuring wider applicability and higher protection precision. The surfaces of the two adjusting screws 204 are threadedly connected to the inner walls of the first protective box 101 and the second protective box 102. The inner wall of the guide block 3 is slidably connected to the surface of the fixing rod 104. The surface of the support box 203 is slidably connected to the inner walls of the first protective box 101 and the second protective box 102. The lower surface of the sponge board 201 contacts the surface of the wing 6. The support box 203 can move freely within a certain range to adapt to wings 6 of different sizes and shapes, enhancing the applicability of the protective structure and simplifying the installation and adjustment process.

[0024] The working principle of this utility model:

[0025] To ensure the wings 6 of the drone 4 are not damaged during transportation or storage, firstly, ensure the drone 4 is in the off state, keeping the wings 6 stationary. This is a crucial step before any operation to avoid potential risks from accidental start-up or movement. Next, place the second protective case 102 onto the wings 6 and bring it into contact with the support rod 5, providing initial fixation. This process forms the basis of the entire protection measure and lays the foundation for subsequent reinforcement steps. Subsequently, bring the surfaces of the first protective case 101 and the second protective case 102 into contact, ensuring a tight fit. By pushing the fixing rod 104 inside the fixing block 103 on the second protective case 102, it is inserted into the mating block 107 of the first protective case 101. Utilizing the pointed structure at the front end of the fixing rod 104, it can cleverly push the limiting blocks 105 to both sides during movement. Once in position, the limiting rod will be held in place by the spring 106. Under the action of the automatic locking rod 104, a firm connection between the two is ensured, thereby achieving a safe combination of the first and second protective boxes 102. After completing the above fixing work, the protection effect can be further enhanced. By rotating the adjusting screw 204 located on the top of the first and second protective boxes 102, the position of the internal support box 203 can be adjusted so that it gradually approaches the surface of the wing 6. The support box 203 is equipped with an elastic block 202 and a sponge plate 201, which not only ensures a gentle touch on the wing 6, but also effectively absorbs vibration during transportation, providing additional cushioning protection to ensure the safety of the wing 6 and maximize the safety of the UAV 4 wing 6 during non-use. When it is necessary to disassemble the protective box, simply pull out the limiting block 105 on the upper side of the mating block 107 and pull the fixing rod 104 in the opposite direction to separate the first and second protective boxes 102, thus completing the disassembly work.

[0026] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0027] The above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model in any way. Although the present utility model has been disclosed above with reference to a preferred embodiment, it is not intended to limit the present utility model. Any person skilled in the art can exercise their rights without departing from the scope of the present utility model.

Claims

1. A protective structure for the wing of a heavy-duty, oil-powered unmanned aerial vehicle (UAV), comprising a UAV (4), support rods (5), and a wing (6), wherein the surface of the UAV (4) is fixedly connected to the rear ends of the four support rods (5), and the upper front end of the support rods (5) is rotatably connected to one end of the wing (6), characterized in that: The support rod (5) is provided with a protective device (1) on its surface. The protective device (1) is provided with an auxiliary mechanism (2) inside. The protective device (1) includes a first protective box (101), a second protective box (102), a fixing block (103), a fixing rod (104), a limiting block (105), a spring (106), and a mating block (107). The surface of the first protective box (101) is in contact with the surface of the second protective box (102). The surface of the second protective box (102) is fixedly connected to the surface of the fixing block (103). The inner wall of the fixing block (103) is slidably connected to the surface of the fixing rod (104). The inner wall of the front end of the fixing rod (104) is in contact with the lower surface of the two limiting blocks (105). The two sides of the limiting block (105) are fixedly connected to the upper ends of the two springs (106). The lower end of the spring (106) is fixedly connected to the inner wall of the mating block (107). The protective device (1) is used to protect the wing (6); The auxiliary mechanism (2) is used to enhance the protection effect.

2. The wing protection structure for a gasoline-powered, high-payload unmanned aerial vehicle as described in claim 1, characterized in that: The auxiliary mechanism (2) includes a sponge board (201), an elastic block (202), a support box (203), and an adjusting screw (204). The upper surface of the sponge board (201) is fixedly connected to the lower surface of the elastic block (202), the upper surface of the elastic block (202) is fixedly connected to the inner wall of the support box (203), and the upper end of the support box (203) is rotatably connected to the lower end of the adjusting screw (204).

3. The wing protection structure for a gasoline-powered, high-payload unmanned aerial vehicle as described in claim 2, characterized in that: A guide block (3) is provided inside the fixed block (103), and the surface of the guide block (3) is fixedly connected to the inner wall of the fixed block (103).

4. The wing protection structure for a gasoline-powered, high-payload unmanned aerial vehicle as described in claim 1, characterized in that: The rear inner wall of the second protective box (102) is in contact with the surface of the support rod (5), the surface of the mating block (107) is fixedly connected to the front surface of the first protective box (101), the surface of the fixing block (103) is in contact with the surface of the mating block (107), the surface of the limiting block (105) is slidably connected to the inner wall of the mating block (107) through a sliding groove, and the front end surface of the fixing rod (104) is slidably connected to the inner wall of the mating block (107).

5. The wing protection structure for a gasoline-powered, high-payload unmanned aerial vehicle as described in claim 3, characterized in that: The surface of the sponge board (201) is slidably connected to the inner wall of the support box (203).

6. The wing protection structure for a gasoline-powered, high-payload unmanned aerial vehicle as described in claim 5, characterized in that: The surfaces of the two adjusting screws (204) are threadedly connected to the inner walls of the first protective box (101) and the second protective box (102), the inner wall of the guide block (3) is slidably connected to the surface of the fixing rod (104), the surface of the support box (203) is slidably connected to the inner walls of the first protective box (101) and the second protective box (102), and the lower surface of the sponge board (201) is in contact with the surface of the wing (6).

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