Large unmanned aerial vehicle flight control device

Abstract

The utility model discloses a large unmanned aerial vehicle flight control device which comprises an installation plate, an installation shell fixedly installed on the installation plate, a flight control element fixedly installed in the installation shell through an installation frame, and a shell cover fixedly connected with the installation shell, a heat dissipation cylinder is integrally formed on the shell cover, and an upper port of the heat dissipation cylinder is communicated with the interior of the installation shell. Wherein a first heat dissipation part is installed in the heat dissipation cylinder, and the first heat dissipation part is located at an upper end opening of the heat dissipation cylinder; a second heat dissipation component is mounted on the mounting shell; wherein the mounting plate is provided with a protection part, the protection part is located on the periphery of the mounting shell, the first heat dissipation part and the second heat dissipation part are used in cooperation, heat dissipation treatment can be effectively conducted on the flight control element, the use stability of the flight control element is guaranteed, the use performance of the flight control element is improved, and the service life of the flight control element is prolonged; physical protection can be provided for the flight control device through the protection component, and damage of collision to internal flight control elements is reduced.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically a large-scale UAV flight control device. Background Technology

[0002] The flight control unit of a large unmanned aerial vehicle (UAV) is the core control component of a large UAV. It is equivalent to the "brain" of the UAV. Its main function is to comprehensively control and manage the UAV's flight attitude, flight trajectory and flight mission. By receiving data from various sensors and performing complex calculations and processing, it outputs control commands to manipulate the various actuators of the UAV, ensuring that the UAV can fly stably and safely according to the predetermined plan.

[0003] Chinese patent publication number CN219770174U discloses a drone flight control device, including a mounting base plate connected to the drone fuselage, a protective shell detachably connected to the upper side of the mounting base plate, a mounting cavity formed inside the protective shell, and an opening formed on the side of the protective shell near the mounting base plate; a circuit board is suspended and fixed inside the protective shell, a flight control housing is provided on the side of the circuit board away from the mounting base plate, and a flight control module is provided inside the flight control housing; a shock-absorbing component is provided between the flight control housing and the circuit board, and the flight control module is connected to the circuit board via wires; a data plug-in component is provided between the circuit board and the mounting base plate.

[0004] The aforementioned patent can solve the corresponding technical problems and provide effective shock absorption for the flight control module. However, the above-mentioned UAV flight control device has poor heat dissipation during use. The entire flight control module is in a sealed state. During long-term operation, the electronic components inside the flight control device will generate a lot of heat, which will cause the performance of the flight control module to decline or even be damaged, thereby affecting the normal operation and use of the UAV. Utility Model Content

[0005] The purpose of this invention is to provide a large-scale UAV flight control device to solve the problem that existing UAV flight control devices have poor heat dissipation during use. The entire flight control module is in a sealed state, and during long-term operation, the electronic components inside the flight control device will generate a lot of heat, which will lead to a decrease in the performance of the flight control module or even damage, thereby affecting the normal operation and use of the UAV.

[0006] To achieve the above objectives, the main technical solution adopted by this utility model includes: a large unmanned aerial vehicle (UAV) flight control device, comprising: a mounting plate fixedly installed on the bottom of the large UAV; a mounting shell fixedly installed on the mounting plate; flight control components fixedly installed inside the mounting shell via a mounting bracket; a shell cover fixedly connected to the mounting shell by a first bolt; a heat dissipation cylinder integrally formed on the shell cover; the upper port of the heat dissipation cylinder communicating with the interior of the mounting shell; wherein a first heat dissipation component is installed inside the heat dissipation cylinder, and the first heat dissipation component is located at the upper port of the heat dissipation cylinder; wherein a second heat dissipation component is installed on the mounting shell; and wherein a protective component is installed on the mounting plate, and the protective component is located on the periphery of the mounting shell.

[0007] As a preferred technical solution, the first heat dissipation component includes a heat dissipation fan fixedly installed at the upper port of the heat dissipation cylinder, and a plurality of partitions fixedly installed on the inner wall of the heat dissipation cylinder in an alternating manner, the partitions being located below the heat dissipation fan;

[0008] A temperature sensor is fixedly installed on the top of the inner wall of the mounting housing, and a controller is fixedly installed on one side of the inner wall of the mounting housing. The controller is electrically connected to the temperature sensor and the cooling fan respectively.

[0009] A moisture-absorbing cotton layer is fixedly installed at the lower port of the heat sink, and the moisture-absorbing cotton layer is located below the partition.

[0010] As a preferred technical solution, a protective net is fixedly installed at the lower port of the heat dissipation cylinder, and the moisture-absorbing cotton layer is located above the protective net.

[0011] As a preferred technical solution, the second heat dissipation component includes multiple heat dissipation fins, which are evenly distributed on the outer side wall of the mounting housing.

[0012] As a preferred technical solution, the protective component includes a protective cover, which is fixedly connected to the mounting plate by a second bolt. The protective cover is fitted around the mounting shell and the heat dissipation cylinder, and the protective cover has a hollow structure.

[0013] As a preferred technical solution, a protective pad is fixedly installed on the outer wall of the protective cover.

[0014] As a preferred technical solution, a shock-absorbing pad is installed between the mounting plate and the bottom of the large drone.

[0015] This utility model has at least the following beneficial effects:

[0016] This utility model provides a large-scale UAV flight control device. The controller automatically starts the cooling fan, which draws out hot air from the mounting shell and discharges it through the heat dissipation cylinder. The hot air exchanges heat with the partition and cylinder wall inside the heat dissipation cylinder, reducing the temperature. At the same time, the moisture-absorbing cotton layer absorbs moisture from the air, preventing moisture from entering the mounting shell and causing corrosion or short circuits to the flight control components. In addition, multiple heat dissipation fins evenly distributed on the outer wall of the mounting shell further increase the contact area with the outside air. During the flight of the UAV, even without the active cooling of the cooling fan, the heat dissipation fins can conduct heat from the mounting shell to the outside air through natural air convection. By using the first and second heat dissipation components in combination, the heat dissipation of the flight control components can be effectively treated, ensuring the stability of the flight control components and improving their performance and lifespan.

[0017] The protective cover with a hollow structure is placed around the mounting shell and heat sink. Its main function is to provide physical protection for the flight control device when the UAV encounters an accidental collision or is in a complex flight environment, reducing damage to the internal flight control components. At the same time, the hollow design does not affect the heat dissipation function of the heat sink and heat sink fins to a certain extent, and can also play a certain role in electromagnetic shielding, reducing the impact of external electromagnetic interference on the flight control device, and further ensuring the normal operation of the flight control device. Attached Figure Description

[0018] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0019] Figure 1 This is a three-dimensional first-view diagram of the large-scale UAV flight control device of this utility model;

[0020] Figure 2 This is a three-dimensional second-view diagram of the large-scale UAV flight control device of this utility model;

[0021] Figure 3 This is a schematic diagram of the protective cover structure of the large unmanned aerial vehicle (UAV) flight control device of this utility model;

[0022] Figure 4 This is a schematic diagram of the heat dissipation fins installation of the large unmanned aerial vehicle flight control device of this utility model;

[0023] Figure 5 This is a cross-sectional view of the large-scale unmanned aerial vehicle (UAV) flight control device of this utility model.

[0024] Explanation of icon numbers:

[0025] 1. Mounting plate; 101. Shock-absorbing pad; 2. Mounting shell; 201. First bolt; 202. Temperature sensor; 203. Controller; 3. Shell cover; 4. Mounting bracket; 401. Flight control components; 5. Heat sink; 501. Partition plate; 502. Moisture-absorbing cotton layer; 503. Protective net; 504. Cooling fan; 6. Heat dissipation fins; 7. Protective cover; 701. Second bolt; 702. Protective pad. Detailed Implementation

[0026] The following will describe in detail the implementation of this application with reference to the accompanying drawings and embodiments, so that the implementation process of how this application uses technical means to solve technical problems and achieve technical effects can be fully understood and implemented accordingly.

[0027] Example

[0028] Please refer to Figures 1 to 5 As shown, this embodiment provides a large unmanned aerial vehicle (UAV) flight control device, including: a mounting plate 1 fixedly installed on the bottom of a large UAV, the large UAV being an unmanned aerial vehicle with a maximum takeoff weight exceeding 150 kg; a mounting shell 2 fixedly installed on the mounting plate 1; a flight control element 401 fixedly installed inside the mounting shell 2 via a mounting bracket 4; a shell cover 3 fixedly connected to the mounting shell 2 via a first bolt 201; a heat dissipation cylinder 5 integrally formed on the shell cover 3; the upper port of the heat dissipation cylinder 5 communicating with the interior of the mounting shell 2; a first heat dissipation component installed inside the heat dissipation cylinder 5, located at the upper port of the heat dissipation cylinder 5; a second heat dissipation component installed on the mounting shell 2; and a protective component installed on the mounting plate 1, located on the periphery of the mounting shell 2. The first and second heat dissipation components work together to effectively dissipate heat from the flight control element 401, ensuring the stability of the flight control element 401, improving its performance and lifespan. The protective component provides physical protection for the flight control device, reducing damage to the internal flight control element 401 from collisions.

[0029] The first heat dissipation component includes a cooling fan 504 fixedly installed at the upper port of the heat dissipation cylinder 5, and multiple staggered partitions 501 fixedly installed on the inner wall of the heat dissipation cylinder 5, with the partitions 501 located below the cooling fan 504. A temperature sensor 202 is fixedly installed on the top of the inner wall of the mounting shell 2, and a controller 203 is fixedly installed on one side of the inner wall of the mounting shell 2. The controller 203 is electrically connected to the temperature sensor 202 and the cooling fan 504, respectively. A moisture-absorbing cotton layer 502 is fixedly installed at the lower port of the heat dissipation cylinder 5, located below the partitions 501. Under the intelligent control of the controller 203, the cooling fan 504 located at the upper port of the heat dissipation cylinder 5 can be activated in a timely manner based on the temperature information inside the mounting shell 2 fed back by the temperature sensor 202. When the flight control element 401 works and generates heat, causing the temperature inside the shell to rise to a set threshold, the fan 504 can be activated. When the temperature is high, the cooling fan 504 rotates, accelerating airflow and quickly expelling the high-temperature gas inside the mounting shell 2 from the heat sink 5. The staggered baffles 501 on the inner wall of the heat sink 5 effectively extend the residence time and flow path of the air inside the sink. When the air passes through the baffles 501, it forms complex turbulence, thereby enhancing the heat exchange with the inner wall of the heat sink 5 and the baffles 501 themselves. This allows the heat to be carried away more fully, greatly improving the heat dissipation efficiency and preventing the flight control component 401 from experiencing performance degradation or even damage due to overheating. This ensures the stable operation of the flight control device and improves the safety and reliability of the UAV flight. In addition, the moisture-absorbing cotton layer 502 at the lower end of the heat sink 5 can effectively absorb the moisture in the air entering the heat sink 5, preventing moisture from entering the mounting shell 2 and causing corrosion or short circuits to the flight control component 401.

[0030] A protective net 503 is fixedly installed at the lower port of the heat sink 5. The moisture-absorbing cotton layer 502 is located above the protective net 503. The protective net 503 can block external debris from entering the heat sink 5, so as to avoid the heat dissipation effect or other malfunctions caused by the accumulation of foreign objects.

[0031] The second heat dissipation component includes multiple heat dissipation fins 6, which are evenly distributed on the outer wall of the mounting shell 2. The multiple heat dissipation fins 6 evenly distributed on the outer wall of the mounting shell 2 further increase the contact area with the outside air. During the flight of the UAV, even without the active heat dissipation of the cooling fan 504, the heat dissipation fins 6 can conduct the heat inside the mounting shell 2 to the outside air by means of natural air convection. This passive heat dissipation method works in conjunction with the active heat dissipation in the heat dissipation cylinder 5 to form a comprehensive heat dissipation system, ensuring that the flight control component 401 is always in a suitable operating temperature environment.

[0032] The protective components include a protective cover 7, which is fixedly connected to the mounting plate 1 by a second bolt 701. The protective cover 7 is fitted around the mounting shell 2 and the heat sink 5, and has a hollow structure. The main function of the protective cover 7, which is fitted around the mounting shell 2 and the heat sink 5, is to provide physical protection for the flight control device when the UAV encounters an accidental collision or is in a complex flight environment, thereby reducing damage to the internal flight control components 401. At the same time, the hollow design does not affect the heat dissipation function of the heat sink 5 and the heat dissipation fins 6 to a certain extent, and can also play a certain electromagnetic shielding role, reducing the impact of external electromagnetic interference on the flight control device, and further ensuring the normal operation of the flight control device.

[0033] The protective cover 7 has a protective pad 702 fixedly installed on its outer wall. The protective pad 702 can reduce the damage to the internal flight control components 401 during a collision, which is helpful for the use of this device.

[0034] Among them, a shock-absorbing pad 101 is installed between the mounting plate 1 and the bottom of the large UAV. The shock-absorbing pad 101 can effectively absorb the vibration generated by the UAV during flight due to engine vibration, airflow disturbance and take-off and landing, ensuring the integrity of the internal structure of the flight control device and the stability of the electrical connection.

[0035] It is worth noting that the mounting shell 2, shell cover 3, heat sink 5, partition 501, heat sink fins 6, and protective cover 7 are all made of aluminum alloy.

[0036] The temperature sensor 202 is model pt100, and the controller 203 is a PLC, model 6ES72350KD220XA8;

[0037] The flight control element 401 is the flight control module disclosed in Chinese Patent Publication No. CN219770174U, and its principle and specific structure will not be described in detail here.

[0038] Working principle: When a large UAV is in operation, the temperature inside the mounting shell 2 gradually rises due to the heat generated by the flight control component 401. When the temperature sensor 202 detects that the temperature has reached the set threshold, the controller 203 automatically starts the cooling fan 504. The cooling fan 504 rotates to draw out the hot air inside the mounting shell 2 and discharge it through the heat dissipation cylinder 5. The hot air exchanges heat with the partition 501 and the cylinder wall inside the heat dissipation cylinder 5 to reduce the temperature. At the same time, the moisture-absorbing cotton layer 502 absorbs moisture in the air to prevent moisture from entering the mounting shell 2 and causing corrosion or short circuit damage to the flight control component 401. The protective net 503 can block external debris from entering the heat dissipation cylinder 5, avoiding the accumulation of foreign objects from affecting the heat dissipation effect or causing other malfunctions. The protective cover 7 provides physical protection for the flight control device at all times during flight, resisting threats such as collisions and scratches from the outside.

[0039] The foregoing description illustrates and describes several preferred embodiments of the present invention. However, as previously stated, it should be understood that the present invention is not limited to the forms disclosed herein and should not be construed as excluding other embodiments. It can be used in various other combinations, modifications, and environments, and can be altered within the scope of the inventive concept described herein through the foregoing teachings or techniques or knowledge in related fields. Any modifications and variations made by those skilled in the art that do not depart from the spirit and scope of the present invention should be within the protection scope of the appended claims.

Claims

1. A flight control device for a large unmanned aerial vehicle (UAV), comprising a mounting plate (1) fixedly mounted on the bottom of the large UAV, wherein a mounting shell (2) is fixedly mounted on the mounting plate (1), and a flight control element (401) is fixedly mounted inside the mounting shell (2) via a mounting bracket (4), characterized in that: It also includes a cover (3), which is fixedly connected to the mounting shell (2) by a first bolt (201). A heat dissipation cylinder (5) is integrally formed on the cover (3), and the upper port of the heat dissipation cylinder (5) is connected to the interior of the mounting shell (2). A first heat dissipation component is installed inside the heat dissipation cylinder (5), and the first heat dissipation component is located at the upper port of the heat dissipation cylinder (5). A second heat dissipation component is installed on the mounting shell (2). A protective component is installed on the mounting plate (1), and the protective component is located on the periphery of the mounting shell (2). The first heat dissipation component includes a cooling fan (504) fixedly installed at the upper port of the heat dissipation cylinder (5), and a plurality of staggered partitions (501) fixedly installed on the inner wall of the heat dissipation cylinder (5), the partitions (501) being located below the cooling fan (504); a temperature sensor (202) is fixedly installed on the top of the inner wall of the mounting shell (2), and a controller (203) is fixedly installed on one side of the inner wall of the mounting shell (2), the controller (203) being electrically connected to the temperature sensor (202) and the cooling fan (504); a moisture-absorbing cotton layer (502) is fixedly installed at the lower port of the heat dissipation cylinder (5), the moisture-absorbing cotton layer (502) being located below the partitions (501); The second heat dissipation component includes multiple heat dissipation fins (6), which are evenly distributed on the outer side wall of the mounting shell (2); the protective component includes a protective cover (7), which is fixedly connected to the mounting plate (1) by a second bolt (701), and the protective cover (7) is fitted around the mounting shell (2) and the heat dissipation cylinder (5), and the protective cover (7) has a hollow structure.

2. The large unmanned aerial vehicle (UAV) flight control device according to claim 1, characterized in that: A protective net (503) is fixedly installed at the lower port of the heat dissipation cylinder (5), and the moisture-absorbing cotton layer (502) is located above the protective net (503).

3. The large unmanned aerial vehicle (UAV) flight control device according to claim 1, characterized in that: A protective pad (702) is fixedly installed on the outer wall of the protective cover (7).

4. A large unmanned aerial vehicle (UAV) flight control device according to any one of claims 1-3, characterized in that: A shock-absorbing pad (101) is installed between the mounting plate (1) and the bottom of the large UAV.

Images