Low-altitude aircraft and rack thereof

Abstract

The low-altitude aircraft comprises an unmanned aerial vehicle body, the two sides of the bottom end of the unmanned aerial vehicle body are each fixedly connected with two supporting plates, a connecting plate is fixedly connected between the two supporting plates on the same side, and a lifting plate and a grounding plate are sequentially arranged at the bottom of the connecting plate; and a driving part is installed at the bottom end of the connecting plate, the output end of the driving part is in transmission connection with a mounting cylinder, and a distance measuring instrument is arranged at the bottom of the mounting cylinder. According to the utility model, through the arrangement of the distance measuring instrument, when a low-altitude aircraft falls, the distance between the landing gear composed of the supporting plate, the connecting plate, the lifting plate, the grounding plate and other components and the ground can be measured, and then the driving part enables the lifting plate to drive the grounding plate to move under the limiting action of the limiting rod and the anti-falling ball according to the distance measuring structure; and the heights of the undercarriages on the two sides are respectively and vertically moved and adjusted, so that the low-altitude aircraft stably lands on the ground.

Description

Technical Field

[0001] This utility model relates to the field of low-altitude aircraft technology, and in particular to a low-altitude aircraft and its frame. Background Technology

[0002] Low-altitude aircraft generally refer to various types of aircraft that fly in low-altitude airspace, typically below 1,000 meters above the ground or water surface, such as drones, helicopters, and light aircraft. Among them, drones, or unmanned aerial vehicles, are unmanned aircraft controlled by radio remote control equipment and their own program control devices. The drone support frame is an important component of drones, providing the foundation for the installation and support of various components of the drone.

[0003] The existing utility model patent with publication number CN205524988U discloses an aircraft frame. It states that "by setting a pin shaft, clamping arm connecting rod, and clamping arm, the pin shaft can not only be used to clamp cylindrical objects of different diameters, but also achieve the effect of dropping them, solving the problem that existing aircraft cannot carry or drop cylindrical objects; in addition, the aircraft frame structure provided in this application is simple, low-cost, and easy to promote and use." While it solves the problem that "most aircraft frames can carry gimbals and airborne camera equipment, but cannot conveniently carry or drop cylindrical objects such as tear gas or smoke bombs," most low-altitude aircraft have landing gear that, on inclined ground, will tilt to the lower side due to the height difference between the left and right landing gear contact points with the ground, causing the aircraft to be unstable after landing and posing a risk of sideslip or rollover. Therefore, this invention proposes a low-altitude aircraft and its frame. Utility Model Content

[0004] Therefore, it is necessary to provide a low-altitude aircraft and its frame to address the aforementioned technical problems, with the left and right landing gears having independently adjustable heights and adapting to sloping ground.

[0005] In order to solve the above-mentioned technical problems, the present invention solves the problem that the fuselage tilts to the lower side due to the height difference between the left and right landing gear and the ground contact point on the inclined ground through the following technical solution.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A low-altitude aircraft and its frame, comprising:

[0008] The drone body has two support plates fixedly connected to both sides of its bottom end, and a connecting plate is fixedly connected between the two support plates on the same side.

[0009] A lifting plate and a grounding plate are sequentially arranged at the bottom of a connecting plate. A driving unit is installed at the bottom end of the connecting plate. The output end of the driving unit is connected to an installation cylinder. A rangefinder is installed at the bottom of the installation cylinder.

[0010] In a preferred embodiment of the low-altitude aircraft and its frame provided by this utility model, the bottom end of the mounting cylinder is fixedly inserted through the middle of the lifting plate, and the rangefinder is installed in the inner cavity of the mounting cylinder.

[0011] In a preferred embodiment of the low-altitude aircraft and its frame provided by this utility model, two limiting rods are fixedly connected to the middle of the top of the lifting plate, and the tops of the two limiting rods respectively movably pass through one end of the two support plates on the same side.

[0012] In a preferred embodiment of the low-altitude aircraft and its frame provided by this utility model, an anti-detachment ball is fixedly connected to the top of the limiting rod.

[0013] In a preferred embodiment of the low-altitude aircraft and its frame provided by this utility model, a central hole is provided in the middle of the grounding plate, and the position of the central hole corresponds to the position of the rangefinder.

[0014] In a preferred embodiment of the low-altitude aircraft and its frame provided by this utility model, perforations are provided on both sides of the surface of the lifting plate, a screw is slidably inserted into the inner cavity of the perforation, and a nut is threadedly connected to the top of the outer wall of the screw.

[0015] In a preferred embodiment of the low-altitude aircraft and its frame provided by this utility model, fixing blocks are fixedly connected to both sides of the top of the grounding plate, and the fixing blocks have built-in grooves inside.

[0016] In a preferred embodiment of the low-altitude aircraft and its frame provided by this utility model, the bottom end of the screw slides through the top end of the fixed block to the inner cavity of the built-in groove, and is fixedly connected to a movable block.

[0017] In a preferred embodiment of the low-altitude aircraft and its frame provided by this utility model, a buffer pad is connected between the moving block and the built-in slot.

[0018] In a preferred embodiment of the low-altitude aircraft and its frame provided by this utility model, a groove is provided at the front end of the lifting plate, and a monitoring device is installed in the inner cavity of the groove.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] This utility model provides a low-altitude aircraft and its frame. By incorporating a rangefinder, it can measure the distance between the landing gear, composed of components such as a support plate, connecting plate, lifting plate, and grounding plate, and the ground when the low-altitude aircraft is descending. Then, the drive unit, based on the ranging structure, causes the lifting plate to move the grounding plate vertically under the limiting action of the limit rod and anti-detachment ball, thereby adjusting the height of the landing gear on both sides. This allows the low-altitude aircraft to land stably on the ground, avoiding landing instability caused by improper landing gear height and ensuring the safe landing of the aircraft.

[0021] This utility model provides a low-altitude aircraft and its frame. By being equipped with a monitoring device, the low-altitude aircraft can monitor obstacles at the front of the landing gear when flying forward. By transmitting the monitoring data to the drive unit, the lifting and lowering of the landing gear can be controlled to avoid collisions between the landing gear and obstacles. By using a buffer pad set between the moving block and the built-in groove, the impact force during descent can be effectively buffered when the landing plate of the low-altitude aircraft contacts the ground. Attached Figure Description

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

[0023] Figure 1 A schematic diagram of the overall structure of this utility model;

[0024] Figure 2 This utility model provides a structural schematic diagram of the bottom of the drone body;

[0025] Figure 3 This utility model provides a partially disassembled structural schematic diagram;

[0026] Figure 4 Provided for this utility model Figure 3 A structural diagram viewed from below;

[0027] Figure 5 This invention provides a partial structural schematic diagram of the lifting plate;

[0028] Figure 6 A schematic diagram of the screw section is provided for this utility model.

[0029] The markings in the diagram are explained as follows:

[0030] 1. UAV body; 2. Support plate; 3. Connecting plate; 4. Lifting plate; 5. Grounding plate; 6. Drive unit; 7. Mounting cylinder; 8. Rangefinder; 9. Limiting rod; 10. Anti-ball detachment; 11. Perforation; 12. Screw; 13. Nut; 14. Fixing block; 15. Internal groove; 16. Moving block; 17. Buffer pad; 18. Groove; 19. Monitoring device; 20. Center hole. Detailed Implementation

[0031] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of the present invention. Example

[0032] Please refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 A low-altitude aircraft and its frame, including a drone body 1, with two support plates 2 fixedly connected to both sides of the bottom end of the drone body 1, and a connecting plate 3 fixedly connected between the two support plates 2 on the same side.

[0033] The lifting plate 4 and the grounding plate 5, composed of components such as the support plate 2, the connecting plate 3, the lifting plate 4, and the grounding plate 5, form a support landing frame for supporting the UAV body 1. The lifting plate 4 is controlled to lift and lower via the drive unit 6 to adjust the landing gear height. The grounding plate 5 directly contacts the ground, and its bottom can be designed with anti-slip textures or cushioning materials to enhance grip. The lifting plate 4 and the grounding plate 5 are sequentially arranged at the bottom of the connecting plate 3. The drive unit 6, which is a cylinder, is installed at the bottom of the connecting plate 3 to provide driving force for the lifting and lowering of the landing gear. In conjunction with the rangefinder 8 and the monitoring device 19, it allows the UAV body 1 to adapt to the inclined ground. The output end of the drive unit 6 is connected to the mounting cylinder 7. The rangefinder 8 is installed at the bottom of the mounting cylinder 7 to measure the distance between the grounding plate 5 and the ground in real time. This is existing technology and will not be described in detail. The bottom end of the mounting cylinder 7 is fixedly inserted through the middle of the lifting plate 4. The rangefinder 8 is installed in the inner cavity of the mounting cylinder 7. A central hole 20 is opened in the middle of the grounding plate 5, and the position of the central hole 20 corresponds to the position of the rangefinder 8.

[0034] Preferably, two limiting rods 9 are fixedly connected to the middle of the top of the lifting plate 4. The tops of the two limiting rods 9 respectively move through one end of the two support plates 2 on the same side. The tops of the limiting rods 9 are fixedly connected to anti-detachment balls 10. The limiting rods 9 and anti-detachment balls 10 play a limiting and guiding role for the lifting plate 4.

[0035] Preferably, both sides of the surface of the lifting plate 4 are provided with through holes 11, through which screws 12 pass. The screws 12 slide through the inner cavity of the through holes 11. The top of the outer wall of the screws 12 is threaded with nuts 13. The connection between the grounding plate 5 and the lifting plate 4 is achieved by the screws 12 and nuts 13. The top two sides of the grounding plate 5 are fixedly connected with fixing blocks 14. The interior of the fixing blocks 14 is provided with built-in grooves 15. The bottom end of the screws 12 slides through the top end of the fixing blocks 14 to the inner cavity of the built-in grooves 15 and is fixedly connected with a moving block 16. A buffer pad 17 is connected between the moving block 16 and the built-in grooves 15. After the grounding plate 5 contacts the ground, the moving block 16 slides in the built-in grooves 15 to compress the buffer pads 17 to absorb the impact energy.

[0036] Preferably, the front end of the lifting plate 4 is provided with a groove 18, and a monitoring device 19 is installed in the inner cavity of the groove 18 to monitor obstacles at the front end of the landing gear in real time.

[0037] The usage process of the low-altitude aircraft and its frame provided by this utility model is as follows: First, after the UAV body 1 takes off, during descent, the rangefinder 8 installed on the landing gear measures the distance between the two landing gears and the ground through the central hole 20. After the distance measurement is completed, the control drive unit 6 causes the lifting plate 4 to drive the grounding plate 5. Under the limiting action of the limit rod 9 and the anti-detachment ball 10, the two landing gears adjust their height according to the landing ground to ensure the stable attitude of the UAV body 1 after descent. While the grounding plate 5 is in contact with the ground, the buffer pad 17 buffers the impact force during descent. During the flight of the UAV body 1, the monitoring device 19 monitors the distance between the landing gear and obstacles directly in front. The grounding plate 5 causes the landing gear to move upward to avoid obstacles and prevent collision.

[0038] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0039] Obviously, the embodiments described above are only some embodiments of this utility model, not all embodiments. The accompanying drawings show preferred embodiments of this utility model, but do not limit the patent scope of this utility model. This utility model can be implemented in many different forms; rather, the purpose of providing these embodiments is to provide a more thorough and comprehensive understanding of the disclosure of this utility model. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing specific embodiments, or make equivalent substitutions for some of the technical features. Any equivalent structures made using the content of this utility model specification and drawings, directly or indirectly applied to other related technical fields, are similarly within the patent protection scope of this utility model.

Claims

1. A low altitude flying vehicle and its frame, characterized by, It includes: The unmanned aerial vehicle body (1), both sides of the bottom end of the unmanned aerial vehicle body (1) are fixedly connected with two support plates (2), and the same side two support plates (2) are fixedly connected with a connecting plate (3); Lifting plate (4) and ground plate (5), the lifting plate (4) and ground plate (5) are sequentially arranged at the bottom of the connecting plate (3), the bottom end of the connecting plate (3) is provided with a driving part (6), the output end of the driving part (6) is drivingly connected with a mounting cylinder (7), and the bottom of the mounting cylinder (7) is provided with a range finder (8).

2. A low altitude aircraft and its airframe according to claim 1, characterized in that, The bottom end of the mounting cylinder (7) is fixedly penetrated through the middle part of the lifting plate (4), and the range finder (8) is installed in the inner cavity of the mounting cylinder (7).

3. The low altitude aircraft and its airframe according to claim 1, characterized in that, The middle part of the top end of the lifting plate (4) is fixedly connected with two limiting rods (9), and the top end of the two limiting rods (9) is respectively movably penetrated through one end of the same side two support plates (2).

4. A low altitude aircraft and its airframe according to claim 3, wherein, The top end of the limiting rod (9) is fixedly connected with an anti-dropping ball (10).

5. The low altitude aircraft and its airframe according to claim 1, wherein, The middle part of the ground plate (5) is provided with a middle hole (20), and the position of the middle hole (20) corresponds to the position of the range finder (8).

6. A low altitude aircraft and its airframe according to claim 5 wherein, Both sides of the surface of the lifting plate (4) are provided with a through hole (11), the inner cavity of the through hole (11) is slidably inserted with a screw rod (12), and the outer wall surface of the screw rod (12) is threadedly connected with a nut (13) at the top.

7. The low altitude aircraft and its airframe according to claim 1, wherein, The top end of the ground plate (5) is fixedly connected with a fixed block (14), and the inside of the fixed block (14) is provided with an embedded groove (15).

8. The low altitude aircraft and its airframe according to claim 6, characterized by, The bottom end of the screw rod (12) is slidably penetrated through the top end of the fixed block (14) to the inner cavity of the embedded groove (15) and is fixedly connected with a moving block (16).

9. A low altitude aircraft and its airframe according to claim 8, wherein, The moving block (16) and the embedded groove (15) are connected with a buffer pad (17).

10. The low altitude aircraft and its airframe according to claim 1, wherein, The front end of the lifting plate (4) is provided with a recess (18), and the inner cavity of the recess (18) is installed with a monitoring device (19).

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