Lightweight laser radar unmanned aerial vehicle

Abstract

The utility model discloses a kind of lightweight laser radar unmanned aerial vehicle, including unmanned aerial vehicle body, it is characterized by: the bottom of the unmanned aerial vehicle body is fixedly installed with rotating holder, and rotating holder is rotatably installed with laser radar, the left and right sides of unmanned aerial vehicle body shell front end are respectively provided with front mounting seat, and front mounting seat is hingedly installed with front end wing;In the utility model, by strip-shaped opening being set in front end wing and rear end wing surface, while greatly reducing fuselage total weight, reducing energy consumption to prolong endurance time, wave-shaped reinforcing rib in strip-shaped opening can effectively disperse wing stress, enhance bending resistance, anti-deformation ability, cooperate with the stable wrapping of U-shaped section front mounting seat and rear mounting seat to wing connecting end, and the smooth cooperation of connecting column and bearing, both ensure the stability of overall structure, avoid component damage under high-speed flight or air flow impact, realize the balance of "light weight" and "high stability".

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a lightweight lidar UAV. Background Technology

[0002] In the field of drone technology, especially application-oriented drones equipped with lidar, there has long been a technical challenge of balancing "lightweight" and "structural stability".

[0003] To ensure fuselage strength, traditional drones often employ heavy metal materials or dense support structures, resulting in a high overall weight. This not only increases energy consumption and shortens flight time but also reduces flight flexibility. While some drones attempt to achieve weight reduction by reducing material thickness, this significantly decreases the bending and deformation resistance of the wings and fuselage. Under high-speed flight or when encountering airflow impacts, problems such as wing breakage and component loosening are prone to occur, even leading to flight accidents, making it difficult to meet the detection needs in complex scenarios. Furthermore, the wing-fuselage connection structure of traditional drones is poorly designed, mostly using fixed welding or simple bolt connections. This not only prevents folding for storage and takes up a lot of space during transportation and storage but also makes installation and disassembly cumbersome and inconvenient. Some foldable wings lack a robust supporting structure at the connection points, resulting in excessive gaps that cause swaying during flight, further affecting flight stability. Furthermore, the fuselage and wing designs of traditional drones do not fully consider aerodynamic principles. The fuselage is often a regular rectangular structure, and the wing surface is flat and unoptimized, resulting in significant air resistance during flight. This limits flight speed, and the turbulent airflow over the fuselage and wings easily creates turbulence, causing the aircraft to shake and affecting the measurement accuracy of detection equipment such as lidar. Additionally, the wiring layout of traditional drones is often cluttered, with internal wing wiring often exposed or simply bundled. During flight, the wiring is prone to friction with wing components, causing wear and tear and posing a short-circuit risk. Simultaneously, exposed wiring disrupts the flatness of the wing surface, further increasing air resistance and reducing flight efficiency. These shortcomings in existing technologies severely restrict the application expansion of lidar-equipped drones in surveying, inspection, and environmental monitoring.

[0004] To address this issue, a lightweight lidar UAV is proposed, which balances lightweight design with stability, reduces flight drag, improves operational convenience, and ensures line safety, thereby solving the problems mentioned in the background technology. Utility Model Content

[0005] The purpose of this invention is to address the shortcomings of existing technologies by proposing a lightweight lidar drone.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: a lightweight lidar drone, comprising a drone body, characterized in that: a rotating gimbal is fixedly installed at the bottom of the drone body, and a lidar is rotatably installed on the rotating gimbal; front mounting seats are respectively provided on the left and right sides of the front end of the drone body shell, and a front wing is hingedly installed in the front mounting seat; rear mounting seats are respectively provided on the left and right sides of the rear end of the drone body shell, and a rear wing is hingedly installed in the rear mounting seat; flight blades are installed on the top part of both the front and rear wings, and columnar pads are fixedly installed at the bottom of both the front and rear wings; two connecting columns are fixed at one end of both the front and rear wings, and positioning holes are opened on the surface of both the front and rear wings; fastening screws are inserted into the surface of the front and rear mounting seats, and one end of the fastening screws is inserted into the positioning hole of the front or rear wing; the cross-section of both the front and rear mounting seats is U-shaped, and both sides of the front and rear mounting seats are connected to the connecting columns through bearings.

[0007] As a further description of the above technical solution: both the front wing and the rear wing have strip-shaped openings on their surfaces, and wavy reinforcing ribs are fixed inside the strip-shaped openings; lead wire grooves are provided at the two side edges of the front wing and the rear wing.

[0008] As a further description of the above technical solution: the installation height of the front wing is greater than the installation height of the rear wing, and the length of the columnar foot of the front wing is greater than the length of the columnar foot of the rear wing.

[0009] As a further description of the above technical solution: the fuselage of the drone body has a structure that is wider at the front and narrower at the back, the front wing is located at the wider end of the drone body fuselage, and the rear wing is located at the narrower end of the drone body fuselage.

[0010] As a further description of the above technical solution: a drive component is installed below the flight blade, and the drive component is embedded in the housing at the end of the front wing or the rear wing.

[0011] As a further description of the above technical solution: the length of the columnar foot of the front wing is greater than the distance between the lidar and the bottom surface of the UAV body, and a rubber buffer block is interference-fitted to the bottom of the columnar foot of the front wing.

[0012] This utility model has the following beneficial effects: In this invention, by opening strip-shaped openings on the surfaces of the front and rear wings, the total weight of the fuselage is significantly reduced, energy consumption is reduced, and the flight time is extended. At the same time, the wave-shaped reinforcing ribs inside the strip-shaped openings can effectively disperse the stress on the wings and enhance the bending and deformation resistance. Combined with the U-shaped front and rear mounting seats that firmly wrap the wing connection end, as well as the smooth cooperation between the connecting column and the bearing, the stability of the overall structure is ensured, and the damage to the components under high-speed flight or airflow impact is avoided, achieving a balance between "light weight" and "high stability". In this invention, because the front wing is installed at a higher height than the rear wing and the corresponding columnar feet are longer, the aerodynamically optimized height difference design can create a reasonable airflow distribution. Combined with the streamlined fuselage that is wider at the front and narrower at the rear, it significantly reduces flight drag, improves flight speed and stability, and reduces turbulence. The front and rear wings are hinged together by connecting columns and bearing mounting seats, allowing for folding and storage to save space. When unfolded, they can be quickly fixed by inserting fastening screws and positioning holes, making operation convenient. In addition, the lead wire grooves on the wing edges can neatly embed internal wiring, avoiding wire wear, while ensuring a flat wing surface to reduce air resistance, further improving flight efficiency. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overall structure of a lightweight lidar drone according to the present invention; Figure 2 This is a top view of a lightweight lidar drone according to the present invention. Figure 3 This is a schematic diagram of the front wing structure; Figure 4 This is a cross-sectional view showing the connection between the front mounting base and the front wing.

[0014] Legend: 1. UAV body; 2. Front mounting base; 3. Front wing; 4. Flight blade; 5. Rear mounting base; 6. Rear wing; 7. Columnar pad; 8. Rotating gimbal; 9. LiDAR; 10. Connecting column; 11. Fastening screw; 12. Strip-shaped opening; 13. Wavy reinforcing rib; 14. Lead wire groove; 15. Positioning hole. Detailed Implementation

[0015] The technical solutions of the present utility model 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 utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0016] According to an embodiment of the present invention, a lightweight lidar drone is provided.

[0017] The present invention will now be further described in conjunction with the accompanying drawings and specific embodiments, such as... Figure 1-4As shown, a lightweight lidar drone according to an embodiment of the present invention includes a drone body 1, characterized in that: a rotating gimbal 8 is fixedly mounted on the bottom of the drone body 1, and a lidar 9 is rotatably mounted on the rotating gimbal 8; front mounting seats 2 are respectively provided on the left and right sides of the front end of the drone body 1, and a front wing 3 is hingedly mounted in the front mounting seat 2; rear mounting seats 5 are respectively provided on the left and right sides of the rear end of the drone body 1, and a rear wing 6 is hingedly mounted in the rear mounting seat 5; flight blades 4 are mounted on the top of both the front wing 3 and the rear wing 6, and columnar feet 7 are fixedly mounted on the bottom of both the front wing 3 and the rear wing 6; the front wing 3 and the rear wing 6... Two connecting posts 10 are fixed at one end, and positioning holes 15 are opened on the surface of the front wing 3 and the rear wing 6. Fastening screws 11 are inserted into the surface of the front mounting base 2 and the rear mounting base 5. One end of the fastening screw 11 is inserted into the positioning hole 15 of the front wing 3 or the rear wing 6. The cross-section of the front mounting base 2 and the rear mounting base 5 is U-shaped, and both sides of the front mounting base 2 and the rear mounting base 5 are connected to the connecting posts 10 through bearings. A rotating gimbal 8 is fixedly installed on the bottom of the UAV body 1 by bolt assembly. The rotating gimbal 8 has 360-degree horizontal rotation and ±90-degree vertical pitch adjustment functions, which can flexibly adjust the detection angle of the lidar according to the detection requirements. The rotating gimbal 8 has a through-hole. A LiDAR 9 is mounted on a precision bearing. This LiDAR 9 features a miniaturized design and centimeter-level detection accuracy, enabling rapid acquisition of 3D point cloud data of the surrounding environment. Front mounting seats 2 are integrally formed on the left and right sides of the front end of the drone body 1. The inner side of the front mounting seat 2 has mounting grooves adapted to the front wing 3, and the front wing 3 is hinged within the front mounting seat 2 via a pin. The front wing 3 can be folded at a certain angle around the pin, saving space during transport and storage. Rear mounting seats 5 are located on the left and right sides of the rear end of the drone body 1. The structure of the rear mounting seats 5 is similar to that of the front mounting seats 2, and they are also hinged within the rear mounting seats via pins. The rear wing 6 is hinged to the shaft; the top of the front wing 3 and the rear wing 6 are respectively mounted with flight blades 4 via motor brackets. The flight blades 4 adopt a biomimetic airfoil design, which can generate greater lift during rotation and has lower noise during operation. The bottom of the front wing 3 and the rear wing 6 are both fixed with columnar pads 7 by welding. The columnar pads 7 are made of hard alloy material and play a role in supporting the smooth landing of the UAV. One end of the front wing 3 and the rear wing 6 is fixed with two connecting posts 10 by screws. The surface of the connecting posts 10 is treated with rust prevention, and the surface of the front wing 3 and the rear wing 6 are both provided with positioning holes 15. The inner diameter of the positioning holes 15 matches the outer diameter of the fastening screws 11.Both the front mounting base 2 and the rear mounting base 5 have threaded holes on their surfaces. Fastening screws 11 are inserted into the threaded holes. One end of the fastening screw 11 passes through the threaded hole and is inserted into the positioning hole 15 of the front wing 3 or the rear wing 6. By tightening the fastening screw 11, the front wing 3 and the rear wing 6 can be firmly fixed to the mounting base to prevent the wings from shaking during flight. Both the front mounting base 2 and the rear mounting base 5 have U-shaped cross sections. This structural design can better wrap the connecting end of the wing and improve the stability of the connection. Both sides of the front mounting base 2 and the rear mounting base 5 are connected to the connecting column 10 through bearings. The bearings can reduce the friction when the connecting column 10 rotates, making the folding and unfolding operation of the wing smoother. Please refer to Figure 2 and Figure 3 Both the front wing 3 and the rear wing 6 have strip-shaped openings 12 on their surfaces, and corrugated reinforcing ribs 13 are fixed inside the strip-shaped openings 12. Guide wire grooves 14 are provided on both sides of the front wing 3 and the rear wing 6. The strip-shaped openings 12 not only further reduce the weight of the wings but also improve the aerodynamic performance of the wings to a certain extent, reducing air resistance during flight. The corrugated reinforcing ribs 13 are made of high-strength plastic, and their unique corrugated structure can disperse the external forces on the wings, effectively enhancing the wings' resistance to bending and deformation, and preventing damage to the wings during high-speed flight or when encountering airflow impact. The width and depth of the guide wire grooves 14 are designed according to the diameter of the internal wiring of the UAV. The internal wiring can be embedded in the guide wire grooves 14, which can both protect the wiring from wear during flight and ensure the flatness of the wing surface, reducing the impact of air resistance on flight. Please refer to Figure 1 The installation height of the front wing 3 is greater than that of the rear wing 6, and the length of the columnar foot 7 of the front wing 3 is greater than that of the rear wing 6. This height difference design is derived from aerodynamic simulation optimization, which enables the UAV to form a more reasonable airflow distribution during flight, improve the stability of the fuselage, and effectively reduce turbulence during flight. In addition, the length of the columnar foot 7 of the front wing 3 is greater than that of the rear wing 6. Since the front wing 3 is installed at a higher height, the corresponding increase in the length of the front columnar foot 7 can ensure that the UAV can maintain a horizontal state when landing, avoid the fuselage tilting due to the inconsistent length of the front and rear feet, and thus protect the bottom-mounted lidar 9 from colliding with the ground.

[0018] Please refer to Figure 1 and Figure 2The drone body 1 has a shell structure that is wider at the front and narrower at the rear. The front wing 3 is located at the wider end of the drone body 1 shell, and the rear wing 6 is located at the narrower end of the drone body 1 shell. This structural design conforms to the principles of aerodynamics, which can effectively reduce air resistance during flight and improve the drone's flight speed and endurance. The wider end of the shell provides a more stable mounting base for the front wing 3 and also better balances the lift generated by the front wing. The rear wing 6 is located at the narrower end of the shell, forming a symmetrical layout with the front wing, which makes the overall center of gravity of the drone more evenly distributed, further improving flight stability and avoiding the problem of fuselage tilting caused by center of gravity shift during flight. Secondly, this design provides space for the rotation and folding of the front wing 3 and the rear wing 6, reducing the space occupied by the drone body 1 when stored.

[0019] Please refer to Figure 1 A drive unit is installed below the flight blade 4, and the drive unit is embedded in the housing at the end of the front wing 3 or the rear wing 6. The drive unit is a brushless motor. Brushless motors have the advantages of high efficiency, long life and low noise, and can provide continuous and stable power output for the flight blade 4. The drive unit is embedded in the housing at the end of the front wing 3 or the rear wing 6. This embedded installation method can not only save installation space and make the overall wing structure more compact, but also protect the drive unit from damage caused by collisions with external objects during flight. At the same time, it can also reduce the impact of vibration generated by the drive unit during operation on the wing and improve flight stability.

[0020] Please refer to Figure 1 The length of the columnar foot 7 of the front wing 3 is greater than the distance between the lidar 9 and the bottom surface of the drone body 1, and the bottom of the columnar foot 7 of the front wing 3 is interference-fitted with a rubber buffer block. This length design is to ensure that the columnar foot 7 can make contact with the ground first when the drone lands, thereby avoiding the lidar 9 from directly touching the ground and causing damage, and providing effective protection for the lidar 9. The rubber buffer block has good elasticity and can absorb the impact force generated by the ground on the fuselage when the drone lands, reducing the impact force on the drone body 1, the rotating gimbal 8 and the lidar 9 and other components, further improving the stability and safety of the drone during landing.

[0021] Working principle: In use, unfold the folded front wing 3 and rear wing 6 around the pivot, so that the connecting post 10 at one end of the wing can be precisely matched with the bearings of the front mounting base 2 and the rear mounting base 5. Then, pass the fastening screw 11 through the threaded hole on the surface of the mounting base, insert it into the positioning hole 15 of the wing and tighten it to complete the wing fixation. At the same time, test the rotating gimbal 8 and the lidar 9 to ensure that the gimbal rotates smoothly and the radar detection function is normal. Check whether the rubber buffer block at the bottom of the columnar pad 7 is intact to prepare for flight. After starting the flight control system, the drive component (brushless motor) embedded in the end shell of the front wing 3 and the rear wing 6 starts to operate, driving the top flight blade 4 to rotate at high speed. The biomimetic airfoil-shaped flight blade 4 cuts through the air during rotation, generating upward lift. Because the drive components of the front and rear wings output power synchronously, and the lift design of the flight blade 4 is adapted to the fuselage weight, the drone takes off smoothly when the lift exceeds the total weight of the drone. During flight, the streamlined fuselage of the drone body 1, wider at the front and narrower at the rear, reduces air resistance. The height difference between the front wing 3 and the rear wing 6 creates a reasonable airflow distribution, maintaining a stable attitude and avoiding turbulence. Based on detection requirements, the rotation angle of the rotating gimbal 8 is adjusted remotely, driving the lidar 9 to achieve 360-degree horizontal scanning or ±90-degree vertical detection, rapidly acquiring three-dimensional point cloud data of the surrounding environment. The data is transmitted in real-time to ground receiving equipment to complete tasks such as mapping and inspection. During this stage, the strip-shaped openings 12 on the wing surface further optimize the airflow path, while the wave-shaped reinforcing ribs 13 ensure that the wing does not deform under airflow impact, ensuring flight and detection stability. After completing the detection task, the speed of the drive components is reduced, the lift generated by the flight blade 4 gradually decreases, and the drone descends slowly. Because the length of the columnar foot 7 of the front wing 3 is greater than that of the rear wing 6 and greater than the distance between the lidar 9 and the bottom of the fuselage, the front and rear feet make contact with the ground simultaneously during landing, keeping the fuselage level and preventing the lidar 9 from touching the ground. At the same time, the rubber buffer block at the bottom of the foot is compressed and deformed to absorb the impact force of the ground on the fuselage, reducing the impact of vibration on the UAV body 1, the rotating gimbal 8 and the lidar 9, and finally achieving a smooth landing, shutting down the drive components and detection equipment, and completing the entire workflow.

[0022] Finally, it should be noted that the above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Although the present 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 embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A lightweight lidar drone, comprising a drone body (1), characterized in that: A rotating gimbal (8) is fixedly mounted on the bottom of the UAV body (1), and a laser radar (9) is rotatably mounted on the rotating gimbal (8). Front mounting seats (2) are respectively provided on the left and right sides of the front end of the UAV body (1), and a front wing (3) is hingedly mounted inside the front mounting seat (2). Rear mounting seats (5) are respectively provided on the left and right sides of the rear end of the UAV body (1), and a rear wing (6) is hingedly mounted inside the rear mounting seat (5). Flight blades (4) are installed on the top part of both the front wing (3) and the rear wing (6), and the bottom of both the front wing (3) and the rear wing (6) are fixedly mounted. The front wing (3) and the rear wing (6) are each equipped with columnar pads (7). Two connecting columns (10) are fixed at one end of each of the front wing (3) and the rear wing (6). Positioning holes (15) are opened on the surface of the front mounting base (2) and the rear mounting base (5). Fastening screws (11) are inserted through the surface of the front mounting base (2) and the rear mounting base (5). One end of the fastening screw (11) is inserted into the positioning hole (15) of the front wing (3) or the rear wing (6). The cross-section of the front mounting base (2) and the rear mounting base (5) is U-shaped. Both sides of the front mounting base (2) and the rear mounting base (5) are connected to the connecting columns (10) through bearings.

2. The lightweight lidar UAV according to claim 1, characterized in that: The front wing (3) and the rear wing (6) are provided with strip-shaped openings (12), and wave-shaped reinforcing ribs (13) are fixed inside the strip-shaped openings (12). Lead wire grooves (14) are provided on both sides of the front wing (3) and the rear wing (6).

3. A lightweight lidar UAV according to claim 1, characterized in that: The installation height of the front wing (3) is greater than that of the rear wing (6), and the length of the columnar foot (7) of the front wing (3) is greater than that of the columnar foot (7) of the rear wing (6).

4. A lightweight lidar UAV according to claim 1, characterized in that: The fuselage of the UAV body (1) has a structure that is wider at the front and narrower at the back. The front wing (3) is located at the wider end of the fuselage of the UAV body (1), and the rear wing (6) is located at the narrower end of the fuselage of the UAV body (1).

5. A lightweight lidar UAV according to claim 1, characterized in that: A drive unit is installed below the flight blade (4), and the drive unit is embedded in the housing at the end of the front wing (3) or the rear wing (6).

6. A lightweight lidar UAV according to claim 1, characterized in that: The length of the columnar foot (7) of the front wing (3) is greater than the distance between the lidar (9) and the bottom surface of the UAV body (1), and the bottom of the columnar foot (7) of the front wing (3) is press-fitted with a rubber buffer block.

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