Integrated carrying device and unmanned aerial vehicle

Abstract

The utility model discloses an integrated carrying device and an unmanned aerial vehicle. The integrated carrying device comprises a radar support, a carrying bin and a rack which are sequentially connected from top to bottom. The radar support is used for installing a radar, and the carrying bin is used for installing a holder and an airborne computer. The radar support, the carrying bin and the rack are formed by integrally cutting carbon fiber plates, and hollow weight reduction areas are arranged on the radar support, the carrying bin and the rack. The utility model has the characteristics of compact structure, high space utilization rate, high reliability and the like, realizes extreme light weight on the premise of ensuring the structural strength, and modularizes the installation of the radar, the airborne computer and the pan-tilt in the vertical space, so that the installation, debugging and replacement of various task equipment are more convenient, and the installation cost is reduced. And a universal carrying platform with high integration level and high reliability is provided for the multifunctional unmanned aerial vehicle.

Description

Technical Field

[0001] This utility model relates to the field of drone mounting technology, specifically to an integrated mounting device and a drone. Background Technology

[0002] Unmanned aerial vehicles (UAVs), especially multi-rotor UAVs, have been widely used in surveying and modeling, precision agriculture, power line inspection, and emergency rescue due to their flexible takeoff, landing, and hovering capabilities. As mission complexity increases, UAV platforms need to simultaneously carry multiple payloads, such as lidar, visual gimbals, and onboard computers, to achieve real-time perception, online processing, and autonomous operation. However, existing general-purpose UAVs are not designed with full consideration of scalability and high integration of multiple modules, making it difficult to meet the demands of current secondary development of UAVs in terms of multiple payloads and high integration. Existing mounting solutions are mostly based on standard frames, using "stacked" or "external" integration methods for mounting onboard equipment. This easily leads to a loose overall structure, low space utilization, and unreasonable spatial layout of modules, which can cause center of gravity shift, seriously affecting flight stability and endurance.

[0003] Specifically, the existing technology has the following main drawbacks:

[0004] First, there is structural redundancy. The additional adapter plates, brackets, and numerous fasteners added to accommodate different devices significantly increase the non-payload weight of the drone, which contradicts the fundamental requirements of lightweight and long-endurance drones.

[0005] Secondly, the integration and reliability are low. The non-integrated design results in many connection points and complex assembly. Under long-term high-frequency vibration, it is prone to problems such as loosening and deformation of the machine structure, which reduces the overall reliability and space utilization of the system.

[0006] To address the need for lightweight design, most mainstream airframes utilize carbon fiber plates as the main components of the airframe. However, the integration method still follows traditional approaches, installing components through simple stacking and external mounting. While this traditional installation method partially solves the equipment installation problem, it makes it difficult to achieve uniformity and convenience in connecting the various components. Furthermore, due to the irrational structural layout, it results in low structural efficiency and cannot meet the current optimization design requirements of unmanned algorithms for the overall structure of drones. At the same time, the non-modular design makes equipment maintenance, replacement, or upgrades extremely inconvenient, requiring the airframe to be disassembled, reassembled, and recalibrated for each adjustment. Utility Model Content

[0007] The technical problem to be solved by this utility model is to address the problems of structural redundancy, low integration and insufficient reliability of existing drone mounting devices, and to provide an integrated mounting device and drone with a compact structure, high space utilization and convenient maintenance.

[0008] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is as follows:

[0009] An integrated mounting device includes a radar bracket, a mounting compartment, and a frame connected sequentially from top to bottom; the radar bracket is used to install a radar, and the mounting compartment is used to install a gimbal and an onboard computer; the radar bracket, mounting compartment, and frame are all integrally cut from carbon fiber plates, and each of the radar bracket, mounting compartment, and frame has a hollowed-out weight-reduction area.

[0010] As a further improvement of this utility model, the mounting compartment is arranged parallel to the frame at intervals, and multiple columns are evenly distributed between the mounting compartment and the frame.

[0011] As a further improvement of this utility model, the radar bracket includes a mounting plate and a base plate. The base plate is installed on the top of the mounting compartment, and the mounting plate is installed obliquely on the base plate. The mounting plate is used to install the radar.

[0012] As a further improvement of this utility model, a support column is provided between the mounting plate and the base plate.

[0013] As a further improvement of this utility model, the mounting compartment includes an airborne computer compartment for installing an airborne computer and a gimbal carrier plate for installing a gimbal; the top of the airborne computer compartment is connected to the radar bracket, and the bottom of the airborne computer compartment is connected to the frame through a column; the gimbal carrier plate is integrally formed on the front end of the airborne computer compartment.

[0014] As a further improvement of this utility model, the airborne computer compartment has a rectangular cavity structure, and strip-shaped ventilation holes are evenly opened on the side of the airborne computer compartment.

[0015] As a further improvement of this utility model, the frame includes a flight control carrier plate, the side of which is integrally formed with an arm, and the end of the arm is integrally formed with a motor carrier plate.

[0016] As a further improvement of this utility model, the bottom of the arm is provided with a footrest.

[0017] As a further improvement of this utility model, the legs are provided with reinforcing ribs.

[0018] As a general technical concept, this utility model also provides another type of drone, including the aforementioned integrated mounting device.

[0019] Compared with the prior art, the integrated mounting device and drone of this utility model have the following advantages:

[0020] 1. Extremely lightweight design: The frame, payload compartment and radar bracket are all made of carbon fiber plate cut into one piece. The payload compartment and the frame are connected by a column interconnection structure instead of the traditional adapter plate and multiple fastener connection method. While ensuring structural strength, the weight of non-effective payload is reduced to the minimum, which meets the core requirements of lightweight and long-endurance UAV.

[0021] 2. High integration and modularity: The radar, onboard computer, flight control and gimbal are arranged in a layered modular layout in the vertical space. The payload bay is equipped with dedicated mounting holes and physical isolation partitions, which not only improves space utilization and avoids center of gravity shift, but also makes the installation, debugging and replacement of various mission equipment more convenient without the need for major modifications to the overall structure.

[0022] 3. High reliability and stability: The integrated molding structure reduces the number of connection points and assembly complexity, effectively avoiding structural loosening and deformation caused by long-term high-frequency vibration; the rigid main frame and symmetrically distributed column design ensure that the connection of each component is stable during flight, improving the overall reliability and flight stability of the system.

[0023] 4. High versatility and adaptability: This mounting device provides a highly integrated and reliable universal mounting platform for multi-functional UAVs. It can be adapted to a variety of common mission payloads such as LiDAR, visual gimbal, and onboard computer, and is suitable for multiple fields such as surveying and modeling, precision agriculture, power line inspection and emergency rescue. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the overall structural principle of the integrated mounting device in a specific embodiment of this utility model;

[0025] Figure 2 This is a schematic diagram of the exploded structure principle of the integrated mounting device in a specific embodiment of this utility model;

[0026] Figure 3 This is a schematic diagram of the overall mounting structure in a specific embodiment of this utility model.

[0027] Legend: 1. Mounting plate; 2. Support column; 3. Base plate; 4. Ventilation hole; 5. Onboard computer compartment; 6. Flight controller mounting plate; 7. Arm; 8. Gimbal mounting plate; 9. Motor mounting plate; 10. Connecting screw hole; 11. Landing frame; 12. Reinforcing rib; 13. Column; 14. Radar bracket; 15. Battery; 16. Mounting compartment; 17. Frame; 18. Radar; 19. Gimbal; 20. Flight controller; 21. Remote controller receiver. Detailed Implementation

[0028] The present invention will be further described below with reference to the accompanying drawings and specific preferred embodiments, but this does not limit the scope of protection of the present invention.

[0029] In the description of this utility model, it should be understood that the terms "side", "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0030] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "multiple" means two or more, unless otherwise explicitly specified.

[0031] Example

[0032] like Figure 1 and Figure 2 As shown, the integrated mounting device of this utility model includes a radar bracket 14, a mounting compartment 16, and a frame 17 connected and fixed from top to bottom. The radar bracket 14, mounting compartment 16, and frame 17 together form a rigidly connected three-layer main load-bearing frame. The radar bracket 14 is used to mount the radar 18, and the mounting compartment 16 is used to mount the gimbal 19 and the onboard computer. The radar bracket 14, mounting compartment 16, and frame 17 are all integrally cut from high-strength carbon fiber plates, and each of them has hollowed-out weight-reduction areas in non-critical load-bearing areas, ensuring structural strength while minimizing weight.

[0033] like Figure 1 and Figure 2 As shown, the payload bay 16 and the frame 17 are arranged parallel to each other and spaced apart, with four columns 13 evenly distributed between the payload bay 16 and the frame 17. The upper and lower ends of the columns 13 are respectively and tightly fixed to the lower surface of the payload bay 16 and the upper surface of the frame 17 by high-strength bolts, forming a stable middle support structure to ensure the relative position stability of each payload module during flight.

[0034] like Figure 1 and Figure 2As shown, the radar bracket 14 includes a mounting plate 1, a support column 2, and a base plate 3. The base plate 3 is installed on top of the mounting compartment 16. One side of the mounting plate 1 is directly connected and fixed to the base plate 3, and the other side of the mounting plate 1 is connected and fixed to the base plate 3 via the support column 2. The support column 2 enables the mounting plate 1 to be installed at a 30° angle on the base plate 3. The mounting plate 1 is used to install the radar 18. The tilted mounting plate 1 ensures that the radar 18 has a more three-dimensional detection space, increasing the detection range of the radar 18.

[0035] like Figure 1 and Figure 3 As shown, the mounting compartment 16 includes an onboard computer compartment 5 for mounting an onboard computer and a gimbal carrier plate 8 for mounting a gimbal. The top of the onboard computer compartment 5 is connected to the radar bracket 14, and the bottom of the onboard computer compartment 5 is rigidly connected to the frame 17 via a column 13; the gimbal carrier plate 8 is integrally formed on the front end of the onboard computer compartment 5. Dividing the mounting compartment 16 into a gimbal mounting area and an onboard computer mounting area avoids electromagnetic interference and physical collisions between the devices.

[0036] In this embodiment, the airborne computer compartment 5 has a rectangular cavity structure, and strip-shaped ventilation holes 4 are evenly distributed on the side of the airborne computer compartment 5 for heat dissipation when the airborne equipment is working. Furthermore, the length of the ventilation holes 4 is adapted to the side length of the airborne computer compartment 5, which enhances the heat dissipation effect while ensuring the strength of the compartment and achieving weight reduction.

[0037] like Figure 1 and Figure 3 As shown, the frame 17 includes a flight control carrier plate 6, with an integrated arm 7 formed on the side of the flight control carrier plate 6. The arm 7 has a through elliptical groove in its middle for accommodating motor wiring. A motor carrier plate 9 is integrated at the end of the arm 7 for mounting the UAV's power motor.

[0038] like Figure 1 As shown, the arm 7 is also provided with connecting screw holes 10, into which fastening screws are screwed to fix the legs 11 to the bottom of the arm 7. Furthermore, the legs 11 are provided with reinforcing ribs 12, which enhance the structural strength and impact resistance, and improve the stability of the support.

[0039] In this embodiment, a drone is also provided, including the aforementioned integrated mounting device. For example... Figure 3 As shown, a gimbal 19 is installed at the bottom of the gimbal carrier plate 8, a flight controller 20 and a receiver 21 for the remote controller are installed on the flight controller carrier plate 6, and a battery 15 is installed at the bottom of the flight controller carrier plate 6, realizing the centralized and modular arrangement of multiple mission payloads.

[0040] When using the integrated mounting device in this embodiment, the power components are first installed and debugged: the UAV power motor is installed on the motor carrier plate 9 at the end of the arm 7, ensuring that the motor output shafts are aligned, the motor wiring is connected and the wiring route is fixed by clips to prevent the wiring from getting tangled or loose during flight; the motor is started to test the balance of power output, ensuring that the speed of each motor is consistent and there is no abnormal vibration.

[0041] The following steps involve the integration and installation of the mission equipment: The onboard computer is placed in the corresponding isolation compartment of the onboard computer bay 5 and secured with bolts through pre-drilled holes, ensuring a close fit between the computer and the bay body and that the ventilation vents 4 are unobstructed. The gimbal 19 is installed on the bottom of the gimbal carrier plate 8 at the front of the onboard computer bay 5. After adjusting the horizontal angle of the gimbal 19, the fixing bolts are tightened, and the rotational flexibility of the gimbal 19 is tested to ensure there is no jamming. The radar 18 is fixed to the 30° inclined mounting surface of the mounting plate 1 with bolts, and the data transmission lines between the radar and the onboard computer are connected. The connection of the line interfaces is checked to ensure a secure connection without any poor contact. The flight controller 20 and the receiver 21 of the remote controller are installed at both ends of the flight controller carrier plate 6, secured with Velcro, and the orientation of the flight controller is checked. The model aircraft battery 15 is connected to the bottom of the flight controller carrier plate 6 via straps, with the battery 15 aligned with the short side of the flight controller carrier plate 6 to balance the center of gravity shift caused by the gimbal 19.

[0042] Finally, auxiliary components are installed and the entire machine is debugged: the legs 11 are installed on the bottom of the boom 7 through the connecting screw holes 10, and the fixing bolts are tightened. The verticality of the legs 11 is then checked to ensure even force distribution during takeoff and landing. After the entire machine is installed, all connection points are checked to ensure they are secure and free from looseness or wobbling. The center of gravity of the entire machine is adjusted using a level to ensure it is located in the central area. The working status of each device is tested by powering on the machine to verify the radar detection range, the stability of the onboard computer, and the rotation accuracy of the gimbal. Once all equipment is confirmed to be working properly, the machine can be put into actual operation.

[0043] The integrated mounting device in this embodiment utilizes carbon fiber integrated cutting and molding technology and a column interconnection structure, significantly reducing the need for additional adapter plates, brackets, and fasteners in traditional designs. This achieves extreme lightweighting while maintaining structural rigidity, meeting the long-endurance requirements of UAVs. A vertically layered modular layout integrates the radar, onboard computer, and gimbal in an orderly manner, improving space utilization, preventing center-of-gravity shift, and enhancing flight stability. The 30° tilt design of the mounting plate 1 expands the detection range without additional adjustment mechanisms, simplifying the equipment debugging process. The isolation partitions and ventilation holes 4 in the onboard computer compartment 5 ensure equipment operational stability while reducing mutual interference. The reinforcing ribs 12 and symmetrically distributed columns 13 enhance the overall load-bearing capacity and vibration resistance, effectively solving problems such as structural redundancy, low integration, and inconvenient maintenance in existing technologies. The UAV in this embodiment is applicable to multiple application scenarios such as surveying and modeling, precision agriculture, power line inspection, and emergency rescue.

[0044] The above description is merely a preferred embodiment of this utility model. The protection scope of this utility model is not limited to the above embodiments. All technical solutions falling within the scope of this utility model's concept are protected. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principle of this utility model should also be considered within the protection scope of this utility model.

Claims

1. An integrated mounting device, characterized in that, It includes a radar bracket (14), a mounting compartment (16), and a frame (17) connected sequentially from top to bottom; the radar bracket (14) is used to install the radar (18), and the mounting compartment (16) is used to install the gimbal (19) and the onboard computer; the radar bracket (14), the mounting compartment (16), and the frame (17) are all integrally cut from carbon fiber plates, and the radar bracket (14), the mounting compartment (16), and the frame (17) are all provided with hollowed-out weight reduction areas.

2. The integrated mounting device according to claim 1, characterized in that, The mounting compartment (16) and the frame (17) are arranged in parallel and spaced apart, and multiple columns (13) are evenly distributed between the mounting compartment (16) and the frame (17).

3. The integrated mounting device according to claim 2, characterized in that, The radar bracket (14) includes a mounting plate (1) and a base plate (3). The base plate (3) is installed on the top of the mounting compartment (16). The mounting plate (1) is installed at an angle on the base plate (3). The mounting plate (1) is used to install the radar (18).

4. The integrated mounting device according to claim 3, characterized in that, A support column (2) is provided between the mounting plate (1) and the base plate (3).

5. The integrated mounting device according to claim 3, characterized in that, The mounting compartment (16) includes an airborne computer compartment (5) for installing an airborne computer and a gimbal carrier plate (8) for installing a gimbal; the top of the airborne computer compartment (5) is connected to the radar bracket (14), and the bottom of the airborne computer compartment (5) is connected to the frame (17) through a column (13); the gimbal carrier plate (8) is integrally formed on the front end of the airborne computer compartment (5).

6. The integrated mounting device according to claim 5, characterized in that, The airborne computer compartment (5) has a rectangular cavity structure, and strip-shaped ventilation holes (4) are evenly provided on the side of the airborne computer compartment (5).

7. The integrated mounting device according to any one of claims 2 to 6, characterized in that, The frame (17) includes a flight control carrier plate (6), the side of which is integrally formed with an arm (7), and the end of the arm (7) is integrally formed with a motor carrier plate (9).

8. The integrated mounting device according to claim 7, characterized in that, The bottom of the arm (7) is provided with a foot (11).

9. The integrated mounting device according to claim 8, characterized in that, The leg (11) is provided with reinforcing ribs (12).

10. A drone, characterized in that, Includes the integrated mounting device as described in any one of claims 1 to 9.

Images