Unmanned aerial vehicle upper computer protection device

Abstract

The utility model relates to the technical field of unmanned aerial vehicle protection, and discloses an unmanned aerial vehicle upper computer protection device which comprises a base, a supporting frame, a top cover and a hollow cylinder radar supporting seat, the supporting frame is connected to the upper end of the base, the top cover is connected to the upper end of the supporting frame, and the hollow cylinder radar supporting seat is connected to the upper end of the top cover. The technical problems that an existing upper computer protection shell is poor in impact resistance, low in heat dissipation efficiency, tedious to disassemble and assemble and the like are solved. According to the protection device, a carbon fiber composite material shell prepared through a 3D printing forming process is adopted, a base is provided with a positioning hole and an aluminum alloy stud to achieve rapid assembly, a supporting frame is of a concave-convex L-shaped mortise and tenon connection structure, an anti-impact frame is formed through elastic embedment of the mortise and tenon connection structure, and a top cover is integrated with a composite hollow structure such as a conjugate hyperbolic curve and an ellipse. The device has the characteristics of impact resistance, efficient heat dissipation and light weight, is suitable for harsh working environments such as agricultural plant protection and electric power inspection, and ensures stable operation of the upper computer under complex working conditions.

Description

Technical Field

[0001] This utility model relates to the field of drone protection technology, specifically to a drone host computer protection device. Background Technology

[0002] With the rapid development of unmanned aerial vehicle (UAV) technology, it has been widely applied in numerous fields, including agricultural plant protection, power line inspection, surveying and mapping, security monitoring, and logistics transportation. A UAV system mainly consists of key components such as the aircraft platform, power system, flight control system, communication system, mission payload, and host computer. Among these, the host computer, as the decision-making center of the UAV system, undertakes crucial functions such as flight mission planning, flight status monitoring, data processing and transmission, and issuing flight control commands, playing a decisive role in the flight safety and mission execution of the UAV.

[0003] Currently, most protective measures in drone systems target the drone as a whole or specific components, such as wings and propellers. There are few protective devices specifically for the host computer. Some drones only have a simple protective shell installed on the host computer. Such protective shells have poor protective performance and are difficult to effectively resist external impacts. This can easily cause the host computer to fall due to impacts, providing only limited physical protection and making it difficult to ensure the stable operation of the host computer.

[0004] The current design of the protective shell for the host computer in UAV systems is unreasonable. The installation and disassembly operations are cumbersome, which is not conducive to the rapid maintenance and repair of UAVs during missions. Moreover, the heat dissipation effect is poor. The internal electronic components of the host computer are prone to overheating, resulting in problems such as decreased computing performance, data transmission errors, control command failure, and even component damage. This seriously affects the flight safety and mission execution efficiency of UAVs, and reduces the reliability and practicality of UAV systems. Utility Model Content

[0005] The purpose of this invention is to address the shortcomings of existing protection methods for UAV host computers and to propose a new UAV host computer protection device. Its advantages include convenient installation and disassembly, high stability and impact resistance from the mortise and tenon joint connection and stress adjustment grooves, and a well-designed hollow structure that allows for heat dissipation and reduces the weight of the host computer casing, thus improving its endurance.

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

[0007] A protective device for a UAV host computer includes a base, a support frame, a top cover, and a hollow cylindrical radar support base, all made of carbon fiber composite material using 3D printing molding process. The support frame is connected to the upper end of the base, the top cover is connected to the upper end of the support frame, and the hollow cylindrical radar support base is connected to the upper end of the top cover.

[0008] Furthermore, the base includes four protective device mounting and positioning holes at the front and rear, and two host computer fixing holes. The protective device mounting and positioning holes are connected to four aluminum alloy studs through hexagonal socket bolts, washers, and frustum-shaped hole structure rubber buffer pads. The host computer positioning holes are connected to the host computer through hexagonal socket bolts.

[0009] Furthermore, the base includes a curved stress adjustment groove and a hyperbola and rounded triangular hollow structure.

[0010] Furthermore, the support frame includes a concave-convex L-shaped tenon and mortise connection structure. One end of the concave-convex L-shaped tenon and mortise connection structure is a concave L-shaped support frame structure, which is directly connected to the base, and the other end is a convex L-shaped support frame structure, which is directly connected to the top cover.

[0011] Furthermore, the convex L-shaped support frame structure of the concave-convex L-shaped tenon-and-mortise connection structure is vertically spliced ​​and connected to the concave L-shaped support frame structure by tenon-and-mortise fitting.

[0012] Furthermore, the top cover includes a pair of conjugate hyperbolas and an elliptical hollow structure.

[0013] Furthermore, the hollow cylindrical device of the hollow cylindrical radar support base is provided with a hollow cylindrical limiting structure with an inner diameter of 5mm and a depth of 15mm. The inner diameter of the hollow cylindrical limiting structure is the same as the maximum outer diameter of the radar leveling support leg.

[0014] Furthermore, the hollow cylindrical limiting structure and the top cover are manufactured as a single piece.

[0015] Compared with the prior art, the beneficial effects of this utility model are:

[0016] Carbon fiber composite protective shells manufactured using 3D printing technology offer advantages such as convenient and rapid production, high design freedom, and support for customized production. They can adapt to different drone models, effectively enhancing their applicability. During the 3D printing process, the carbon fiber and resin matrix are thoroughly impregnated, significantly reducing defects such as air bubbles and voids within the material. Therefore, upon impact, the material can distribute stress evenly throughout, effectively dispersing localized stress and thus enhancing structural stability and impact resistance. Furthermore, carbon fiber composites are lightweight, corrosion-resistant, and fatigue-resistant, making them suitable for drone systems in various applications.

[0017] The curved stress adjustment groove structure design divides the overall base plate into multiple small rounded triangular regions. Due to the reduced size of each small region, the local bending stress is reduced under load, thereby improving the overall structural stiffness. At the same time, the regional design reduces the impact of fiber orientation differences on the overall mechanical properties, optimizing mechanical performance.

[0018] The support frame employs a L-shaped mortise and tenon joint structure. The interlocking of the tenons and mortises forms a stable frame structure, effectively limiting the displacement and rotation of connecting components in the horizontal direction, thus enhancing the overall structural stability. Vertically, installation and disassembly are simple and quick. When the drone is impacted, this stable structure reduces the shaking and displacement of the host computer. Drawing inspiration from the excellent seismic performance of mortise and tenon joints in traditional wooden structures, the tight contact between the tenons and mortises generates a certain degree of elastic deformation, absorbing and dissipating some of the impact energy. This effectively reduces the direct impact of vibration and shock on the host computer, providing a buffering protection effect and lowering the risk of vibration damage.

[0019] The hollow structure design, with its ingenious mechanical architecture, significantly reduces the overall weight while ensuring structural strength without any compromise, thus greatly improving the drone's endurance. In addition, its unique open space can accelerate air convection, creating an efficient heat dissipation environment for the host computer and effectively ensuring the stable operation of the equipment. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of the UAV host computer protection device;

[0021] Figure 2 Isometric view of the UAV host computer protection device;

[0022] Figure 3 This is a schematic diagram of the base structure of the UAV host computer protection device;

[0023] Figure 4 This is a schematic diagram of the top cover structure of the host computer protection device for unmanned aerial vehicles.

[0024] In the diagram: 1-Hex socket head cap screw; 2-Washer; 3-Frustoconical hole structure rubber buffer pad; 4-Aluminum alloy stud; 5-Curved stress adjustment groove; 6-Rounded triangular hollow structure; 7-Concave L-shaped support frame structure; 8-Convex L-shaped support frame structure; 9-Elliptical hollow structure; 10-Hollow cylindrical radar support base; 11-Upper computer fixing hole; 12-Base; 13-Top cover; 14-Support frame. Detailed Implementation

[0025] To clearly illustrate the technical features of this utility model, the technical solutions in the embodiments of this utility model are described clearly and in detail below through specific implementation methods and in conjunction with the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Therefore, the protection scope of this application is not limited to the specific embodiments disclosed below. All other embodiments obtained by those skilled in the art without creative modifications are within the protection scope of this utility model.

[0026] Furthermore, it should be noted in the description of this application that terms such as "upper end," "lower end," "top," "bottom," "outer diameter," and "inner diameter," used herein, are merely for describing specific embodiments and are not intended to limit the exemplary embodiments according to this application. In all examples shown and discussed herein, any specific value should be interpreted as merely exemplary and not as a limitation. Therefore, other examples of exemplary embodiments may have different values.

[0027] Example 1

[0028] See Figures 1-4 As shown, this embodiment provides a UAV host computer protection device, including a base 12, a support frame 14, a top cover 13, and a hollow cylindrical radar support base 10, all made of carbon fiber composite material using 3D printing molding process. The support frame 14 is connected to the upper end of the base 12, the top cover 13 is connected to the upper end of the support frame 12, and the radar support base 10 is connected to the upper end of the top cover 13. The base 12 includes four front and rear protection device mounting and positioning holes and two host computer fixing holes 11. The protection device mounting and positioning holes are connected to aluminum alloy studs 4 through hexagon socket head cap screws 1, washers 2, and frustum-shaped hole structure rubber buffer pads 3, in the order of hexagon socket head cap screws 1, washers 2, protection device mounting and positioning holes on the base, and frustum-shaped hole structure rubber buffer pads 3. The host computer positioning holes 11 are connected to the host computer through hexagon socket head cap screws. The support frame includes a concave-convex L-shaped tenon-and-mortise connection structure. One end of the concave-convex L-shaped tenon-and-mortise connection structure is a concave L-shaped support frame structure 7, which is directly connected to the base 12 and integrally formed. The other end is a convex L-shaped support frame structure 8, which is directly connected to the top cover 13 and integrally formed. The convex L-shaped support frame structure 8 is vertically spliced ​​and connected to the concave L-shaped support frame structure 7 by tenon-and-mortise fitting. The hollow cylindrical radar support base 10 has a hollow cylindrical limiting structure with an inner diameter of 5mm and a depth of 15mm, which is integrally formed with the top cover 15. The inner diameter of the hollow cylindrical limiting structure is the same as the maximum outer diameter of the radar leveling support leg, and it can be directly embedded and connected.

[0029] Example 2

[0030] This embodiment provides a drone host computer protection device. When installed on a drone, it only needs to be mounted on the drone using aluminum alloy studs 4. The host computer positioning holes are connected to the host computer via hexagonal bolts. The top cover and base are fitted together using a tongue-and-groove L-shaped tenon and mortise joint structure. The radar leveling feet are vertically embedded into the hollow cylindrical radar support base 10 of the top cover. This drone host computer protection device has good compatibility. While maintaining the technical characteristics of the device, its size can be adjusted according to the shape and structure of the host computer using 3D printing molding technology. When the drone is impacted or falls in complex environments, the tongue-and-groove L-shaped tenon and mortise joint structure of the support frame can effectively limit the displacement and rotation of each connecting component in all directions in the horizontal direction. This stable structure can reduce the shaking and displacement of the host computer. The curved stress adjustment groove 5 divides the overall base plate into multiple small rounded triangular areas, breaking through the constraints of the traditional linear through structure and abandoning the inherent pattern of a single straight connection path. When subjected to force, it can reduce local bending stress, absorb and dissipate some impact energy, reduce the risk of shell damage, and mitigate the direct effects of vibration and impact on the host computer, thus playing a buffering and protective role.

[0031] Example 3

[0032] This embodiment provides a host computer protection device for unmanned aerial vehicles (UAVs), including but not limited to devices installed on UAV systems. Following the same installation method as in Embodiments 1 and 2, it can be installed and applied to systems including but not limited to: unmanned vehicles, unmanned boats, robotic dogs, and humanoid robots. Similar to Embodiment 2, this device provides vibration reduction and shock absorption protection for the host computer.

[0033] Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that the present invention is not limited to the details of the above exemplary embodiments, and that the present invention can be implemented in other specific forms, or that some of the technical features can be equivalently replaced. Therefore, any modifications, equivalent replacements, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A kind of unmanned aerial vehicle host computer protection device, it is characterized in that, Including base (12), support frame (14), top cover (13), hollow cylindrical radar support seat (10), the support frame (14) is connected on the upper end of base (12), the top cover (13) is connected on the upper end of support frame, the hollow cylindrical radar support seat (10) is connected on the upper end of top cover.

2. The device according to claim 1, wherein, The base includes four protection device mounting positioning holes, two upper computer fixing holes (11), the protection device mounting positioning hole is connected by the inner hexagonal bolt (1), the gasket (2), the circular table hole structure rubber buffer pad (3) and four aluminum alloy studs (4), the upper computer positioning hole is connected by the inner hexagonal bolt and the upper computer.

3. The device of claim 1, wherein the device is configured to: The base includes a curved stress adjusting groove (5), a double-curved hollow structure and a rounded triangular hollow structure (6).

4. The device of claim 1, wherein the device is configured to: The support frame (14) includes a concave-convex L-shaped mortise and tenon connection structure, one end of the concave-convex L-shaped mortise and tenon connection structure is a concave L-shaped support frame structure (7) directly connected with the base (12), the other end is a convex L-shaped support frame structure (8) directly connected with the top cover (13).

5. The device according to claim 4, wherein the device is configured to: The convex L-shaped support frame structure (8) of the concave-convex L-shaped mortise and tenon connection structure is vertically spliced and connected with the concave L-shaped support frame structure (7) by the mortise and tenon fitting mode.

6. The device according to claim 1, wherein, The top cover includes a pair of conjugate double-curved hollow structures and an elliptical hollow structure (9).

7. The device of claim 1, wherein the device is a drone host protection device. The hollow cylindrical device of the hollow cylindrical radar support seat (10) is provided with a hollow cylindrical limiting structure with an inner diameter of 5mm and a depth of 15mm, and the inner diameter of the hollow cylindrical limiting structure is the same as the maximum outer diameter of the radar leveling foot.

8. The device of claim 7, wherein the device is configured to: The hollow cylindrical limiting structure and the top cover (13) are manufactured by an integral molding structure.

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