Weight-reducing oil cooler for unmanned aerial vehicle

Abstract

The utility model discloses a weight reduction oil cooler for unmanned plane belongs to cooler technical field, include: core, oil cooling lower end socket, oil cooling upper end socket, the core is cooler main part, oil cooling lower end socket sets up in the core one end, oil cooling upper end socket sets up in the core other end, and the oil cooling upper end socket is provided with temperature control valve, and oil cooling upper end socket one side sets up back pressure valve, back pressure valve is connected with temperature control valve, and when pressure is too big, opens back pressure valve, reduces pressure, prevents the core pressure too big and explodes and opens, when temperature is too high, opens temperature control valve, reduces temperature, prevents temperature too high and burns down engine. The utility model discloses cooler adopts U - flow form design, and back pressure valve and temperature control valve are set up in oil cooling upper end socket together, significantly reduce the volume of cooler, and set up a circle sealing strip on the outside of core, guarantee the air volume not to lose, obtain the maximum utilization, to guarantee the heat dissipation performance, and need not external joint or support foot, and the weight of end socket is reduced.

Description

Technical Field

[0001] This utility model relates to the field of cooler technology, specifically to a weight-reducing oil cooler for unmanned aerial vehicles (UAVs). Background Technology

[0002] With the widespread application of advanced technologies in military transport equipment, the development of unmanned aerial vehicles (UAVs) has also made groundbreaking progress.

[0003] Simplifying the design structure is one of the effective methods for reducing the weight of drones. Typically, drone designs contain many redundant components; modifying these components can make the drone lighter. Coolers are usually regulated by an external one-way valve connected to the outside of the end cap, but this structure increases the cooler's weight, failing to achieve weight reduction while ensuring heat dissipation and safety performance. Utility Model Content

[0004] The purpose of this invention is to provide a weight-reducing oil cooler for drones to solve the above problems, reducing the volume and weight of the cooler while ensuring performance and safety.

[0005] Technical Solution: This utility model provides a weight-reducing oil cooler for unmanned aerial vehicles (UAVs), comprising: a core, a lower oil-cooled end cap, and an upper oil-cooled end cap. The core is the main body of the cooler. The lower oil-cooled end cap is located at one end of the core. The upper oil-cooled end cap is located at the other end of the core. A temperature control valve is installed inside the upper oil-cooled end cap, and a back pressure valve is installed on one side of the upper oil-cooled end cap. The back pressure valve is connected to the temperature control valve. When the pressure is too high, the back pressure valve is opened to reduce the pressure and prevent the core from bursting due to excessive pressure. When the temperature is too high, the temperature control valve is opened to reduce the temperature and prevent the engine from burning out due to excessive temperature.

[0006] Furthermore, in the aforementioned weight-reducing oil cooler for drones, the core adopts a U-flow design.

[0007] Furthermore, in the aforementioned drone weight-reducing oil cooler, a connecting plate is provided on one side of the core, and a sealing strip is provided on the other side.

[0008] Furthermore, in the aforementioned weight-reducing oil cooler for unmanned aerial vehicles, an intermediate partition is provided inside the upper oil cooling head. The intermediate partition is welded inside the upper oil cooling head, and the core is provided with a corresponding slot. The lower part of the intermediate partition is engaged in the slot on the core.

[0009] Furthermore, in the aforementioned unmanned aerial vehicle (UAV) weight-reducing oil cooler, a temperature control valve is installed on the intermediate partition.

[0010] Furthermore, in the aforementioned unmanned aerial vehicle (UAV) weight-reducing oil cooler, a connector is sleeved on the outside of the back pressure valve. The connector is designed according to the size of the back pressure valve, and a contact welding surface is provided at the bottom of the connector.

[0011] Furthermore, in the aforementioned unmanned aerial vehicle (UAV) weight-reducing oil cooler, the inner part of the connector connected to the back pressure valve is cylindrical, while the outer end is tapered.

[0012] As can be seen from the above technical solution, this utility model has the following beneficial effects: The weight-reducing oil cooler for UAVs described in this utility model adopts a U-flow design, with the back pressure valve and temperature control valve jointly set inside the oil cooling head, significantly reducing the volume of the cooler. At the same time, a sealing strip is set on the outside of the core to ensure that the airflow is not lost, achieving maximum utilization and thus ensuring heat dissipation performance. Moreover, no external connectors or feet are required, reducing the weight of the head. The connector has a cylindrical end and a tapered outer end design, with a reserved contact welding surface, which satisfies both strength and weight reduction. The temperature control valve is fixed to the middle partition plate of the cooler itself, without adding extra components, while improving structural strength and without increasing weight. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the structure of a weight-reducing oil cooler for unmanned aerial vehicles according to this utility model;

[0014] Figure 2 This is a side view of a weight-reducing oil cooler for unmanned aerial vehicles according to this utility model;

[0015] Figure 3 This is a perspective view of a weight-reducing oil cooler for unmanned aerial vehicles according to this utility model.

[0016] In the diagram: Core 1, Oil-cooled lower end cap 2, Oil-cooled upper end cap 3, Temperature control valve 31, Back pressure valve 32, Intermediate partition 33, Joint 34, Contact welding surface 341, Connecting plate 11, Sealing strip 12. Detailed Implementation Example

[0017] like Figures 1-3 The image shows a weight-reducing oil cooler for unmanned aerial vehicles (UAVs), comprising: a core 1, a lower oil-cooled end cap 2, and an upper oil-cooled end cap 3. The core 1 is the main body of the cooler and adopts a U-flow design. The lower oil-cooled end cap 2 is located at one end of the core 1, and the upper oil-cooled end cap 3 is located at the other end of the core 1. A temperature control valve 31 is installed inside the upper oil-cooled end cap 3, and a back pressure valve 32 is installed on one side of the upper oil-cooled end cap 3. The back pressure valve 32 is connected to the temperature control valve 31. When the pressure is too high, the back pressure valve 32 opens to reduce the pressure and prevent the core 1 from bursting due to excessive pressure. When the temperature is too high, the temperature control valve 31 opens to reduce the temperature and prevent the engine from burning out due to excessive temperature. The core adopts a U-flow design, sharing two one-way valves, the temperature control valve 31 and the back pressure valve 32, inside the upper oil-cooled end cap 3. This structure of two one-way valves inside one end cap significantly reduces the size of the cooler, eliminates external structures, and greatly reduces weight.

[0018] In this embodiment, a connecting plate 11 is provided on one side of the core 1, and a sealing strip 12 is provided on the other side. This ensures that airflow is not lost, achieving maximum utilization and thus guaranteeing heat dissipation performance.

[0019] like Figure 3 The illustrated weight-reducing oil cooler for unmanned aerial vehicles (UAVs) includes an intermediate partition plate 33 inside the upper oil cooling head 3. The intermediate partition plate 33 is welded to the upper oil cooling head 3. A corresponding slot is provided on the core 1, and the lower part of the intermediate partition plate 33 is secured within this slot. A temperature control valve 31 is installed on the intermediate partition plate 33. By utilizing the intermediate partition plate 33 of the cooler itself, the temperature control valve 31 is fixed to it, improving structural strength without adding extra components and without increasing weight.

[0020] like Figure 2 The illustrated weight-reducing oil cooler for drones features a connector 34 fitted around the outside of the back pressure valve 32. The connector 34 is designed to fit the size of the back pressure valve 32, and its bottom has a contact welding surface 341. The inner part of the connector 34 connecting to the back pressure valve 32 is cylindrical, while the outer end is tapered. This design balances strength requirements with reduced weight of the connector 34, while also meeting customer installation needs, thus improving the overall weight of the cooler.

[0021] It should be noted that the above description is merely a technical solution of the utility model and not a limitation. Although the present utility model has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solution of the utility model without departing from the scope of the present utility model, and all such modifications and substitutions should be covered within the scope of the claims of the present utility model.

Claims

1. A weight-reducing oil cooler for unmanned aerial vehicles (UAVs), characterized in that: include: Core (1), wherein the core (1) is the main body of the cooler; Oil-cooled lower end cap (2), the oil-cooled lower end cap (2) is disposed at one end of the core (1); An oil-cooled upper end cap (3) is provided at the other end of the core (1). A temperature control valve (31) is provided inside the oil-cooled upper end cap (3). A back pressure valve (32) is provided on one side of the oil-cooled upper end cap (3). The back pressure valve (32) is connected to the temperature control valve (31). When the pressure is too high, the back pressure valve (32) is opened to reduce the pressure and prevent the core (1) from bursting due to excessive pressure. When the temperature is too high, the temperature control valve (31) is opened to reduce the temperature and prevent the engine from burning out due to excessive temperature.

2. The weight-reducing oil cooler for unmanned aerial vehicles according to claim 1, characterized in that: The core (1) is designed in a U-flow form.

3. The weight-reducing oil cooler for unmanned aerial vehicles according to claim 2, characterized in that: The core (1) has a connecting plate (11) on one side and a sealing strip (12) on the other side.

4. A weight-reducing oil cooler for unmanned aerial vehicles according to claim 1, characterized in that: The oil-cooled upper end cap (3) is provided with a middle partition plate (33), which is welded inside the oil-cooled upper end cap (3). The core (1) is provided with a corresponding slot, and the lower part of the middle partition plate (33) is locked in the slot on the core (1).

5. A weight-reducing oil cooler for unmanned aerial vehicles according to claim 4, characterized in that: A temperature control valve (31) is installed on the intermediate partition (33).

6. A weight-reducing oil cooler for unmanned aerial vehicles according to claim 1, characterized in that: The back pressure valve (32) is fitted with a connector (34) on the outside. The connector (34) is designed according to the size of the back pressure valve (32), and the bottom of the connector (34) is provided with a contact welding surface (341).

7. A weight-reducing oil cooler for unmanned aerial vehicles according to claim 6, characterized in that: The inner part of the connector (34) that connects to the back pressure valve (32) is cylindrical, while the outer end is tapered.

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