Computer vented enclosure structure based on a drone

Abstract

The utility model discloses a computer ventilation shell structure based on unmanned plane belongs to unmanned plane technical field, and its technical scheme main points include flight control unmanned plane, the rear side fixed coupling of flight control unmanned plane top has flight control calculation module, both sides of flight control calculation module all swing joint have ventilation heat dissipation mechanism, the outside swing joint of ventilation heat dissipation mechanism has dustproof mechanism, can be by the opening of fixed frame, support frame etc.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a computer ventilation shell structure based on UAVs. Background Technology

[0002] To adapt to the operational needs of UAVs in complex flight environments such as high altitude, high humidity, dust, and high-speed airflow, and to solve problems such as low heat dissipation efficiency, poor hardware stability, and shortened lifespan caused by environmental interference due to heat generated during operation, a computer ventilation shell structure with dustproof, waterproof, airflow impact resistance, and efficient heat dissipation functions has become a key research and development direction, based on the limited payload and space constraints of UAVs, aiming to ensure the stable and reliable operation of airborne computing systems.

[0003] In the existing technology, in the practical application of UAV flight control computers, the existing shells mostly adopt a single-direction passive heat dissipation or simple ventilation structure, which is prone to heat accumulation, leading to a decline in computer performance or even failure. In addition, external dust can easily enter the interior, affecting the lifespan of the equipment, and the screen is inconvenient to maintain and replace.

[0004] To address this, a computer ventilation shell structure based on unmanned aerial vehicles (UAVs) is proposed. Utility Model Content

[0005] The purpose of this invention is to provide a computer ventilation shell structure based on unmanned aerial vehicles (UAVs) that can solve existing heat dissipation and dust prevention problems.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a computer ventilation shell structure based on a drone, including a flight control drone. A flight control computing module is fixedly connected to the rear side of the top of the flight control drone. Ventilation and heat dissipation mechanisms are movably connected to both sides of the flight control computing module. A dustproof mechanism is movably connected to the outer side of the ventilation and heat dissipation mechanism. The ventilation and heat dissipation mechanism includes two support frames, which are respectively fixedly connected to both sides of the flight control computing module. A DC axial flow fan is movably connected to the inner side of the support frame. A fixed frame is fixedly connected to the opposite side of the two support frames. A linkage louver is rotatably connected to the inner side of the fixed frame. An adjustment component is movably connected to the outer side of the linkage louver, and the adjustment component is movably connected to the inner side of the support frame.

[0007] Preferably, the dustproof mechanism includes two mounting frames, which are fixedly connected to opposite sides of two support frames. Two fixing rods are slidably connected to the inner side of the mounting frames, and the two fixing rods are respectively located on the front and rear sides of the inner side of the mounting frames.

[0008] Preferably, the front and rear sides of the mounting frame are fixedly connected to limit blocks, and the opposite sides of the two fixed clamps are fixedly connected to limit slide rods. The limit slide rods are slidably connected to the inner side of the limit blocks. A tension spring is fixedly connected to the side of the limit block away from the fixed clamps, and the other end of the tension spring is fixedly connected to the outer side of the limit slide rod. The tension spring is sleeved on the outer side of the limit slide rod.

[0009] Preferably, a screen is provided on the inner side of the mounting frame, and the fixing rods are provided on both sides of the screen.

[0010] Preferably, the adjustment component includes a small drive motor, which is fixedly connected to the top of the inner side of the support frame. The output end of the small drive motor is fixedly connected to a drive gear, which is disposed on the top of the support frame. A toothed plate is meshed with the front side of the drive gear, and a linkage frame is fixedly connected to the front side of the toothed plate. The linkage frame is slidably connected to the inner side of the support frame.

[0011] Preferably, the top and bottom of the front side of the linkage frame are rotatably connected to connecting rods, and the two sets of connecting rods are respectively rotatably connected to the outer sides of the top and bottom of the linkage louver.

[0012] Preferably, a fixing block is fixedly connected to one side of the two fixing clamps.

[0013] Preferably, the screen has fixing grooves on both sides, and the fixing block is inserted into the inside of the fixing groove.

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

[0015] 1. This application solves the problem of decreased flight control performance and malfunctions caused by heat accumulation in traditional passive cooling or simple ventilation structures by setting up a ventilation and heat dissipation mechanism. The opening is composed of a fixed frame and a support frame on the non-installation side of the flight control computing module shell. The internal airflow is actively drawn and discharged by a straight axial flow fan in the fixed frame. The support frame can be driven by a small drive motor to adjust the angle and spacing of the linkage frame and linkage louvers. This can not only adapt to the flight mode to adjust the airflow direction and block dust intrusion, solving the problem of external dust affecting the life of the equipment, but also eliminate the need for frequent screen replacement, avoiding the inconvenience of screen maintenance and replacement, and achieving optimization of heat dissipation, dust prevention and maintenance.

[0016] 2. This application incorporates a dustproof mechanism, allowing the installation of a fine-mesh screen within the outermost mounting frame. This effectively intercepts dust and fine particulate impurities, and the screen is easy to replace. It can be easily operated before and after drone use. The installation principle is as follows: The two sets of fixed clamping rods that slide together within the support frame are disengaged, causing the outer limit sliding rods of the clamping rods to slide within the limit blocks. This stretches and stores force in the tension spring between the limit blocks and the sliding rods. At this point, the screen is inserted into the mounting frame. After releasing the clamping rods, the tension springs pull back, driving the clamping rods to approach the screen from both sides, allowing the outer fixing blocks of the clamping rods to engage with the fixing grooves on both sides of the screen, achieving a flexible and quick fixation. Disassembly is performed by reversing the operation, thus balancing dustproof performance with ease of maintenance. Attached Figure Description

[0017] Figure 1 This is an overall structural diagram of the computer ventilation shell structure based on the UAV of this utility model;

[0018] Figure 2 This is an overall structural diagram of the flight control computing module of this utility model;

[0019] Figure 3 This is an overall structural diagram of the ventilation and heat dissipation mechanism of this utility model;

[0020] Figure 4 This is an overall structural diagram of the adjustment component of this utility model;

[0021] Figure 5 This is an overall structural diagram of the dustproof mechanism of this utility model.

[0022] In the diagram, 1. Flight control drone; 2. Flight control computing module; 3. Ventilation and heat dissipation mechanism; 31. Fixing frame; 32. Support frame; 33. DC axial flow fan; 34. Linked louvers; 35. Adjustment component; 3501. Small drive motor; 3502. Drive gear; 3503. Gear plate; 3504. Linked frame; 3505. Connecting rod; 4. Dustproof mechanism; 41. Mounting frame; 42. Fixing clamp; 43. Limiting block; 44. Limiting slide bar; 45. Tension spring; 46. Screen; 5. Fixing block; 6. Fixing groove. Detailed Implementation

[0023] 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.

[0024] Please see Figure 1-5 The present invention provides the following technical solution:

[0025] The computer ventilation shell structure based on the UAV includes a flight control UAV 1. A flight control computing module 2 is fixedly connected to the rear of the top of the flight control UAV 1. Ventilation and heat dissipation mechanisms 3 are movably connected to both sides of the flight control computing module 2. A dustproof mechanism 4 is movably connected to the outer side of the ventilation and heat dissipation mechanism 3. The ventilation and heat dissipation mechanism 3 includes two support frames 32, which are fixedly connected to both sides of the flight control computing module 2. A DC axial flow fan 33 is movably connected to the inner side of the support frame 32. A fixed frame 31 is fixedly connected to the opposite side of the two support frames 32. A linkage louver 34 is rotatably connected to the inner side of the fixed frame 31. An adjustment component 35 is movably connected to the outer side of the linkage louver 34. The adjustment component 35 is movably connected to the inner side of the support frame 32.

[0026] In this embodiment: On the outside of the flight control computing module 2 mounted on the top of the flight control drone 1, i.e. the non-installation side of the flight control computer shell, there are outwardly extending openings. The opening is composed of a longer fixed frame 31, a shorter support frame 32, and a mounting frame 41. The three are connected in pairs by welding or bolting. The fixed frame 31 is equipped with a small DC axial flow fan 33 driven by a built-in motor, which can pull the airflow inside the flight control computing module 2 and blow it outward to achieve heat dissipation through airflow. The airflow will pass through the middle support frame 32. Multiple sets of linked louvers 34 are rotatably connected inside the support frame 32. The angle and spacing of the linked louvers 34 can be adjusted by means of the adjustment component 35, so as to adapt to the dynamic flight state of the drone and adjust its blocking ability.

[0027] Specifically, such as Figure 1 , Figure 2 , Figure 5 As shown, the dustproof mechanism 4 includes two mounting frames 41, which are fixedly connected to opposite sides of two support frames 32. Two fixing rods 42 are slidably connected to the inner side of the mounting frame 41, and the two fixing rods 42 are respectively arranged on the front and rear sides of the inner side of the mounting frame 41.

[0028] Specifically, such as Figure 1 , Figure 2 , Figure 5 As shown, limiting blocks 43 are fixedly connected to the front and rear sides of the mounting frame 41, and limiting slide rods 44 are fixedly connected to opposite sides of the two fixing clamps 42. The limiting slide rods 44 are slidably connected to the inner side of the limiting block 43. A tension spring 45 is fixedly connected to the side of the limiting block 43 away from the fixing clamps 42, and the other end of the tension spring 45 is fixedly connected to the outer side of the limiting slide rod 44. The tension spring 45 is sleeved on the outer side of the limiting slide rod 44.

[0029] Specifically, such as Figure 1 , Figure 2 , Figure 5As shown, a screen 46 is provided on the inner side of the mounting frame 41, and fixing rods 42 are provided on both sides of the screen 46.

[0030] In this embodiment: a fine-mesh screen 46 is installed in the outermost mounting frame 41 to intercept dust and small particulate impurities. The screen 46 is easy to replace before and after use of the flight control drone 1. When replacing, firstly, the two sets of fixed clamps 42 that are slidably connected in the support frame 32 are simultaneously opened, allowing the limiting slide rod 44 on the outside of the fixed clamp 42 to slide in the limiting block 43, so that the tension spring 45 between the limiting block 43 and the limiting slide rod 44 is stretched and stored away from the outer wall of the fixed clamp 42. Then, the screen 46 is inserted into the mounting frame 41, and the fixed clamps 42 are released. The tension spring 45 pulls back and drives the two sets of fixed clamps 42 to approach the screen 46 from both sides, so that the fixing blocks 5 on the outside of the fixed clamps 42 are engaged in the fixing grooves 6 on both sides of the screen 46, thereby achieving elastic and quick fixation of the screen 46. The screen can be easily removed by reversing the operation.

[0031] Specifically, such as Figure 3 , Figure 4 As shown, the adjustment component 35 includes a small drive motor 3501, which is fixedly connected to the top of the inner side of the support frame 32. The output end of the small drive motor 3501 is fixedly connected to a drive gear 3502, which is located on the top of the support frame 32. A toothed plate 3503 is meshed with the front side of the drive gear 3502, and a linkage frame 3504 is fixedly connected to the front side of the toothed plate 3503. The linkage frame 3504 is slidably connected to the inner side of the support frame 32.

[0032] Specifically, such as Figure 3 , Figure 4 As shown, the top and bottom of the front side of the linkage frame 3504 are rotatably connected to the connecting rods 3505, and the two sets of connecting rods 3505 are respectively rotatably connected to the outer sides of the top and bottom of the linkage louver 34.

[0033] In this embodiment: by activating a single small drive motor 3501 inside the support frame 32, the drive gear 3502 located at its output end on the top wall of the fixed frame 31 can be rotated. The drive gear 3502 meshes with the toothed plate 3503 on the rear side of the linkage frame 3504, which can drive the linkage frame 3504 to slide left and right within the fixed frame 31. When sliding to the inner wall of the fixed frame 31, the drive gear 3502 is still meshed with the toothed plate 3503. When the linkage frame 3504 slides, the two sets of arrayed connecting rods 3505 rotatably connected at its top and bottom will synchronously twist the rotating shafts of their respective linkage louvers 34, so that all linkage louvers 34 rotate together. When all linkage louvers 34 are in the maximum orientation, the distance between them is the smallest, and when they are in the minimum orientation, the distance between them is the largest.

[0034] Specifically, such as Figure 5As shown, a fixing block 5 is fixedly connected to one side of the two fixed clamping rods 42 facing each other.

[0035] Specifically, such as Figure 5 As shown, both sides of the screen 46 are provided with fixing grooves 6, and fixing blocks 5 are inserted into the inside of the fixing grooves 6.

[0036] In this embodiment, the installation stability can be further improved by using the fixing block 5 and the fixing groove 6.

[0037] Working Principle: In practical applications of UAV flight control computers, existing casings often employ passive heat dissipation in one direction or simple ventilation structures. This can easily lead to heat buildup, causing a decline in computer performance or even malfunction. Furthermore, external dust can easily penetrate the interior, affecting the equipment's lifespan. Additionally, the screen 46 is inconvenient to maintain and replace. To avoid these issues, outwardly extending openings are now fixedly connected to the outer side of the flight control computing module 2 mounted on the top of the UAV 1, i.e., the non-installation side of the flight control computer casing. These openings are mainly composed of a longer fixed frame 31 and a shorter support frame 32 connected to the mounting frame 41, with each pair connected by welding or bolting. The connection is as follows: Inside the fixed frame 31, a small DC axial fan 33 is installed. Driven by a built-in motor, it primarily draws and blows air outward from the flight control computing module 2, achieving heat dissipation through airflow. During airflow guidance, the air passes through the support frame 32 located in the middle section. Multiple sets of linked louvers 34 are rotatably connected inside the support frame 32. These linked louvers 34 can adjust the direction of the outgoing airflow to adapt to the flight mode of the flight control drone 1, prevent foreign object intrusion, and enable dynamic adjustment based on the computing power of the flight control computing module 2. The tilt angle of leaf 34 and the openings between each pair can be achieved by a single small drive motor 3501. By activating the small drive motor 3501 located inside the support frame 32, the drive gear 3502 located at its output end and on the top wall of the fixed frame 31 can rotate. The drive gear 3502 meshes with the toothed plate 3503 on the rear side of the linkage frame 3504. When the drive gear 3502 rotates, it guides the linkage frame 3504 to one side. When the linkage frame 3504 slides to the inner wall of the fixed frame 31 to complete the adjustment, the drive gear 3502 is still meshed with the toothed plate 3503. Similarly, when the drive gear 3502 rotates in the opposite direction... When rotated, the linkage frame 3504 can be made to fit against the inner wall of the other side of the fixed frame 31. By moving the linkage frame 3504 left and right, during its movement, the top and bottom of the linkage frame 3504 are rotatably connected to two sets of arrayed connecting rods 3505. Each connecting rod 3505 is rotatably connected to the shaft of its corresponding linkage louver 34. Therefore, when the position of the linkage frame 3504 changes, the shaft of the linkage louver 34 will be twisted simultaneously through the arrayed connecting rods 3505, causing the linkage louver 34 to rotate simultaneously. Thus, when the linkage louvers 34 are all facing the maximum surface, they are in the state of minimum spacing between each other.When the blades are at their minimum position, the spacing is at its maximum. This allows for adjustment of the angle and spacing of the linked louvers 34, adapting to the dynamic flight state of the drone and adjusting its blocking capability. Furthermore, to further prevent dust from entering, a fine-mesh screen 46 is installed inside the outermost mounting frame 41, greatly intercepting dust and small particulate impurities. The screen 46 can be easily replaced before and after use of the flight control drone 1, achieving convenient installation. The main installation method is to simultaneously open the two sets of fixed clamps that are slidably connected inside the support frame 32. 42, causing the limiting slide bar 44 on the outer side of the fixed clamp 42 to slide inside the limiting block 43, while the tension spring 45 between the outer wall of the limiting block 43 away from the fixed clamp 42 and the limiting slide bar 44 is stretched and accumulates elastic potential energy. At this time, after the screen 46 is directly inserted into the mounting frame 41, the pressure on the two fixed clamps 42 is released, allowing them to quickly approach the screen 46 from both sides under the pull of the tension spring 45, and causing the outer fixing block 5 to snap into the fixing groove 6 on both sides of the screen 46, thus achieving elastic and quick fixing, and conversely, convenient removal. In summary, this achieves the optimization of the computer ventilation shell structure of the UAV.

[0038] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, and improvements 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 computer ventilation shell structure based on an unmanned aerial vehicle (UAV), including a flight control UAV (1), characterized in that: The flight control drone (1) is fixedly connected to the rear side of the top of the flight control computing module (2). Both sides of the flight control computing module (2) are movably connected to the ventilation and heat dissipation mechanism (3). The outer side of the ventilation and heat dissipation mechanism (3) is movably connected to the dustproof mechanism (4). The ventilation and heat dissipation mechanism (3) includes two support frames (32). The two support frames (32) are fixedly connected to both sides of the flight control computing module (2). The inner side of the support frame (32) is movably connected to the DC axial flow fan (33). The opposite sides of the two support frames (32) are fixedly connected to the fixed frame (31). The inner side of the fixed frame (31) is rotatably connected to the linkage louver (34). The outer side of the linkage louver (34) is movably connected to the adjustment component (35). The adjustment component (35) is movably connected to the inner side of the support frame (32).

2. The computer ventilation shell structure based on a drone according to claim 1, characterized in that: The dustproof mechanism (4) includes two mounting frames (41), which are fixedly connected to opposite sides of two support frames (32). Two fixed clamps (42) are slidably connected to the inner side of the mounting frame (41), and the two fixed clamps (42) are respectively set on the front and rear sides of the inner side of the mounting frame (41).

3. The computer ventilation shell structure based on a drone according to claim 2, characterized in that: Limiting blocks (43) are fixedly connected to the front and rear sides of the mounting frame (41). Limiting slide rods (44) are fixedly connected to opposite sides of the two fixing clamps (42). The limiting slide rods (44) are slidably connected to the inner side of the limiting block (43). A tension spring (45) is fixedly connected to the side of the limiting block (43) away from the fixing clamps (42), and the other end of the tension spring (45) is fixedly connected to the outer side of the limiting slide rod (44). The tension spring (45) is sleeved on the outer side of the limiting slide rod (44).

4. The computer ventilation shell structure based on a drone according to claim 2, characterized in that: A screen (46) is provided on the inner side of the mounting frame (41), and the fixing rods (42) are provided on both sides of the screen (46).

5. The computer ventilation shell structure based on a drone according to claim 1, characterized in that: The adjustment component (35) includes a small drive motor (3501), which is fixedly connected to the top of the inner side of the support frame (32). The output end of the small drive motor (3501) is fixedly connected to a drive gear (3502), which is located on the top of the support frame (32). The front side of the drive gear (3502) is meshed with a toothed plate (3503), and the front side of the toothed plate (3503) is fixedly connected to a linkage frame (3504). The linkage frame (3504) is slidably connected to the inner side of the support frame (32).

6. The computer ventilation shell structure based on a drone according to claim 5, characterized in that: The top and bottom of the front side of the linkage frame (3504) are rotatably connected to connecting rods (3505), and the two sets of connecting rods (3505) are respectively rotatably connected to the outer sides of the top and bottom of the linkage louver (34).

7. The computer ventilation shell structure based on a drone according to claim 4, characterized in that: Two fixed clamps (42) are fixedly connected to a fixed block (5) on opposite sides.

8. The computer ventilation housing structure based on a drone according to claim 7, characterized in that: The screen (46) has a fixing groove (6) on both sides, and the fixing block (5) is inserted into the inside of the fixing groove (6).

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