Wind power heat dissipation system for engine of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle engine wind power heat dissipation system which comprises an engine, a generator and a fan, and the engine is provided with a plurality of cylinder bodies protruding in the radial direction. The engine, the generator and the fan are sequentially arranged along the central axis of the engine from bottom to top, and the generator and the fan are both in driving connection with the engine. The air conditioner further comprises an upper wind scooper and a lower cover plate, the upper wind scooper comprises a first cover body used for jointly covering the fan and the generator and a plurality of second cover bodies used for correspondingly covering the cylinder bodies, the lower cover plate is arranged at the bottom of the generator, and a heat dissipation cavity for containing the fan and the generator is defined by the lower cover plate and the first cover body. A connecting section for communicating the first cover body with the second cover body is arranged between the first cover body and the second cover body; and the connecting section is provided with a slope flow guide surface which is radially outward and downwards inclined. By optimizing the space arrangement of the engine, the generator and the fan and combining the upper wind scooper and the lower cover plate, efficient drainage heat dissipation is achieved, meanwhile, the heat dissipation cooling problem of the engine and the generator is solved, and heat dissipation is enhanced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a wind cooling system for an UAV engine. Background Art

[0002] Drone is the abbreviation of unmanned aerial vehicle. Drones are divided into electric drones and gasoline-powered drones according to their driving methods. Gasoline-powered drones have excellent wind resistance, are relatively stable when working, and have a wider range of applications. Multi-rotor gasoline-powered drones, in particular, have a simple structure, low noise, and are maneuverable, flexible, responsive, and have low operating requirements. They are widely used in tasks such as crop protection, forest fire monitoring, aerial photography, land surveying, and post-disaster loss assessment.

[0003] Current drones on the market typically require an engine and an onboard generator to generate significant power. Over extended periods of operation, the engine can experience elevated temperatures and wear. Unburned fuel and gas in the combustion chamber spontaneously ignite during compression due to the high temperature and pressure. The resulting flame collides with the normally ignited flame, generating extreme pressure that can cause detonation or even cylinder explosion, compromising the drone's flight safety. Existing technologies primarily address heat dissipation from the engine block, often by adding a cooling fan to the engine's base. However, this often overlooks the issue of heat dissipation from the generator. Utility Model Content

[0004] The technical problem to be solved by the present invention is to overcome the above-mentioned problems and provide a wind cooling system for a UAV engine. By optimizing the spatial arrangement of the engine, generator and fan and combining an air guide cover, efficient drainage and heat dissipation from top to bottom can be achieved, which can simultaneously improve the heat dissipation and cooling problems of the engine and generator and enhance the heat dissipation performance.

[0005] The technical solution of the utility model is:

[0006] The utility model discloses a wind cooling system for a UAV engine, comprising an engine, a generator, and a fan. The engine is provided with a plurality of radially protruding cylinders. The utility model is characterized in that the engine, the generator, and the fan are arranged in sequence from bottom to top along the central axis of the engine, and the generator and the fan are both driven and connected to the engine.

[0007] The wind cooling system also includes an upper air guide cover and a lower cover plate. The upper air guide cover includes a first cover body for jointly covering the fan and the generator and multiple second cover bodies for correspondingly covering each cylinder body. The lower cover plate is arranged at the bottom of the generator and is enclosed with the first cover body to form a heat dissipation cavity for accommodating the fan and the generator; a connecting section is provided between the first cover body and the second cover body to connect the two, and the connecting section has a sloped guide surface that is radially outward and inclined downward.

[0008] In the above structure, the engine, generator, and fan are positioned in a rational manner, and an upper air guide hood and lower cover plate structure comprising a first cover body, a second cover body, and a sloped guide surface are designed. The upper and lower sealing of the first cover body and the lower cover plate forms a heat dissipation chamber. The airflow generated by the rotation of the fan not only dissipates heat from the generator below, but also flows obliquely downward into the second cover via the sloped guide surface of the connecting section to dissipate heat from the various cylinders. This prevents airflow from flowing directly out of the bottom of the first cover body, ensuring that sufficient airflow can be introduced into the second cover body. Furthermore, the above structural design can simultaneously cool and dissipate heat for both the generator and the engine, demonstrating superior heat dissipation performance and reducing overall temperature rise.

[0009] Furthermore, in the UAV engine wind cooling system described in this utility model, the upper end surface of the first cover body has a plurality of concentrically spaced annular ribs and a plurality of radial ribs distributed radially. The radial ribs connect the annular ribs to form a plurality of first ventilation slots. By designing the upper end surface of the first cover body and utilizing the staggered annular and radial rib structure, the first cover body not only has excellent ventilation and heat dissipation effects, but also effectively improves its structural strength.

[0010] Furthermore, in the wind cooling system for the UAV engine described in the utility model, a plurality of second ventilation slots are radially distributed on the lower cover plate to enhance the internal and external ventilation and heat exchange effects.

[0011] Furthermore, in the wind cooling system for the UAV engine described in the utility model, the first cover body, the second cover body, and the connecting section are integrally formed.

[0012] Furthermore, in the wind cooling system for the UAV engine described in the present invention, the lower cover plate has a guide plate that corresponds one-to-one to each connecting section and extends radially outward into the connecting section, which guides the airflow flowing out of the first cover body well and ensures that the airflow can smoothly enter the connecting section.

[0013] Furthermore, in the wind cooling system for the UAV engine of the present invention, the first cover is cylindrical, and the connecting section is connected to the outer circumferential wall of the first cover. The first cover adopts a smooth cylindrical design, which effectively reduces the wind resistance of the heat dissipation airflow, makes the airflow smoother, and is conducive to increasing the flow rate of the airflow.

[0014] Furthermore, in the wind cooling system for the UAV engine described in the present invention, the cross section of the second cover is U-shaped, which is easy to process and shape.

[0015] Furthermore, in the UAV engine wind cooling system described in this utility model, the engine's output shaft is coaxially fixed to the generator's rotor, and the fan is coaxially mounted on the generator's rotor. By directly coaxially driving the generator rotor and fan, the engine and fan rotate synchronously, resulting in a simpler structure and a more compact size.

[0016] Furthermore, in the wind cooling system for the UAV engine described in the utility model, the fan includes a fan disk and fan blades radiatingly distributed on the upper end surface of the fan disk, and the outer ends of the fan blades extend outside the fan disk.

[0017] The beneficial effects of the utility model are:

[0018] 1. The utility model has a simple structure and a reasonable design. It adopts a heat dissipation layout in which the fan, generator, and engine are arranged in sequence up and down. Combined with the upper air guide cover and the lower cover plate composed of the first cover body, the second cover body, and the connecting section, effective drainage is achieved, so that the airflow can flow downward to the outer surface of the generator, and at the same time flow obliquely downward from the first cover body into the second cover body to dissipate heat to the cylinder body, the main heat source part of the engine, thereby achieving simultaneous cooling and heat dissipation of the engine and the generator. The airflow will not be blocked by the excessive size of the engine, and the temperature rise is small and the heat dissipation performance is stronger.

[0019] 2. The utility model only makes reasonable optimization and adjustment for each component in the axial direction, and the upper air guide cover and the lower cover plate are designed to be light and thin, basically without adding extra space and power consumption, with low cost and easy installation and maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a structural diagram of the present utility model.

[0021] Figure 2 This is a schematic diagram of the structure of the utility model after the upper air guide cover is removed.

[0022] Figure 3 It is a structural schematic diagram of the upper air guide cover described in the utility model.

[0023] Figure 4 It is a structural schematic diagram of the lower cover plate of the utility model. DETAILED DESCRIPTION

[0024] The present invention will now be further described with reference to the accompanying drawings:

[0025] Reference Figure 1 and Figure 2As shown, the wind cooling system of a UAV engine described in this embodiment includes an engine 1, a generator 2, and a fan 3. The engine 1 has two radially protruding cylinders 1a. The engine 1, generator 2, and fan 3 are arranged in sequence from bottom to top along the central axis of the engine 1, and the generator 2 and fan 3 are all driven and connected to the engine 1. In this embodiment, the engine 1, the generator 2, and the fan 3 are directly connected. The output shaft of the engine 1 is coaxially fixed to the rotor of the generator 2, and the fan 3 is coaxially sleeved on the rotor of the generator 2. The fan 3 includes a fan disk and blades radially distributed on the upper end surface of the fan disk, and the outer ends of the blades extend outside the fan disk.

[0026] Reference Figure 1 、 Figure 3 and Figure 4 The wind heat dissipation system described in this embodiment also includes an upper air guide cover 4 and a lower cover plate 5. The upper air guide cover 4 includes a first cover body 4a for jointly covering the fan 3 and the generator 2, and multiple second cover bodies 4b for correspondingly covering each cylinder 1a. The lower cover plate 5 is arranged at the bottom of the generator 2 and encloses the first cover body 4a to form a heat dissipation cavity for accommodating the fan 3 and the generator 2; a connecting section 4c is provided between the first cover body 4a and the second cover body 4b to connect the two, and the connecting section 4c has a sloped guide surface 4d that is radially outward and inclined downward.

[0027] Specifically, the first housing 4a is cylindrical, and the connecting section 4c is connected to the outer circumferential wall of the first housing 4a. The second housing 4b has a U-shaped cross-section and surrounds the outside of the cylinder 1a to cool and dissipate heat from the cylinder 1a. The first housing 4a, second housing 4b, and connecting section 4c are integrally formed.

[0028] To improve the efficiency of internal and external gas exchange and ensure good ventilation and heat dissipation, the upper end surface of the first cover body 4a has a plurality of concentrically spaced annular ribs 4e and a plurality of radially distributed radial ribs 4f. The radial ribs 4f connect the annular ribs 4e to form a plurality of first ventilation slots 4g. The lower cover plate 5 has a plurality of second ventilation slots 5b distributed radially.

[0029] In order to enhance the airflow guiding effect, the lower cover plate 5 has a guide plate 5a corresponding to each connecting section 4c and extending radially outward into the connecting section 4c, so that the airflow can smoothly enter the connecting section 4c from the first cover body 4a.

[0030] The working principle of this embodiment is: through reasonable optimization, the fan 3 is moved upward to form a heat dissipation layout in which the fan 3, generator 2, and engine 1 are arranged in sequence from top to bottom. The coaxial high-speed rotation of the fan 3, generator 2, and engine 1 is utilized to effectively drive the air flow around, and a specially designed upper air guide cover 4 and lower cover plate 5 are designed to effectively guide the airflow. The first cover body 4a and the lower cover plate 5 are used to induce air and dissipate heat for the generator 2. At the same time, since the main heat of the engine 1 is concentrated in the cylinder body 1a, the second cover body 4b corresponding to each cylinder body 1a is used to achieve induced air and heat dissipation for each cylinder body 1a. During the entire heat dissipation process, the airflow generated by the rotation of the fan 3 can not only be guided downward through the first cover 4a to flow to the outer surface of the generator 2, but can also be divided into two paths, flowing into the connecting section 4c from the outer peripheral wall of the first cover 4a, and flowing into the second cover 4b through the downward guiding effect of the sloped guide surface 4d, and flowing downward to the surface of each cylinder 1a, ensuring that the fan can simultaneously play a heat dissipation role on the engine 1 and the generator 2, avoiding the airflow being blocked due to the excessive size of the engine 1, and significantly enhancing the heat dissipation effect.

[0031] The specific embodiments described herein are merely illustrative of the principles and effects of this utility model and are not intended to limit this utility model. Anyone skilled in the art may modify or alter the above embodiments without departing from the spirit and scope of this utility model. Therefore, any equivalent modifications or alterations made by a person skilled in the art without departing from the spirit and technical concepts disclosed in this utility model are encompassed by the claims of this utility model.

Claims

1. A wind-driven cooling system for a UAV engine, comprising an engine, a generator, and a fan, wherein the engine has a plurality of radially protruding cylinders, characterized in that: The engine, generator, and fan are arranged in sequence from bottom to top along the central axis of the engine, and the generator and fan are both driven and connected to the engine; The wind cooling system also includes an upper air guide cover and a lower cover plate. The upper air guide cover includes a first cover body for jointly covering the fan and the generator and multiple second cover bodies for correspondingly covering each cylinder body. The lower cover plate is arranged at the bottom of the generator and is enclosed with the first cover body to form a heat dissipation cavity for accommodating the fan and the generator; a connecting section is provided between the first cover body and the second cover body to connect the two, and the connecting section has a sloped guide surface that is radially outward and inclined downward.

2. The UAV engine wind cooling system according to claim 1, characterized in that: The upper end surface of the first cover body has a plurality of concentrically spaced annular ribs and a plurality of radial ribs radially distributed. The radial ribs connect the annular ribs into one body and form a plurality of first ventilation slots.

3. The UAV engine wind cooling system according to claim 1, characterized in that: The lower cover plate is provided with a plurality of second ventilation slots distributed radially.

4. The UAV engine wind cooling system according to claim 1, characterized in that: The first cover body, the second cover body and the connecting section are integrally formed.

5. The UAV engine wind cooling system according to claim 1, characterized in that: The lower cover plate is provided with guide plates corresponding to each connecting section one by one and extending radially outward into the connecting section.

6. The UAV engine wind cooling system according to claim 1, characterized in that: The first cover body is cylindrical, and the connecting section is connected to the outer circumferential wall of the first cover body.

7. The UAV engine wind cooling system according to claim 1, characterized in that: The cross section of the second cover is U-shaped.

8. The UAV engine wind cooling system according to claim 1, characterized in that: The output shaft of the engine is coaxially fixed to the rotor of the generator, and the fan is coaxially sleeved on the rotor of the generator.

9. The UAV engine wind cooling system according to claim 1, characterized in that: The fan comprises a fan disk and fan blades radially distributed on the upper end surface of the fan disk, wherein outer ends of the fan blades extend outside the fan disk.

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