A UAV fuel pump

Abstract

The present invention relates to the field of drone technology, and in particular to a drone fuel pump. By designing the side of the flow channel as a curved surface to replace the traditional right-angled surface, and forming an axial inward angle and an axial outward angle on the curved surface, the axial inward angle and the axial outward angle are both smooth curved surfaces, which can effectively avoid the generation of eddy currents caused by right angles, reduce the energy loss at right angles, and achieve lower noise. At the same time, the designed flow channel and impeller meet a specific conversion relationship, so that under the condition of meeting the same head and flow rate, the diameter of the overall structure can be reduced from 80mm to 60mm, and the weight can be reduced by 65% to 75%, that is, lighter weight and smaller volume are achieved. If the volume size is not changed, a higher pump pressure can be achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a fuel pump for UAVs. Background Art

[0002] With the development of multi-rotor drone technology, researchers are exploring its agricultural applications. To achieve these diverse functions, multi-rotor drones are equipped with a wide range of equipment, including fuel pumps. However, the unique characteristics of multi-rotor drones require fuel pumps that are lighter, have higher pump pressures, are smaller, and quieter. Current fuel pumps fail to meet these requirements. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a UAV fuel pump with the advantages of lighter weight, higher pump pressure, smaller size and lower noise.

[0004] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0005] A fuel pump for an unmanned aerial vehicle (UAV) includes a UAV body, a fuel tank and a fuel pump, each of which is provided on the UAV body. The fuel tank is connected to the fuel pump. The fuel pump includes a pump body and an impeller provided within the pump body. The pump body is provided with a flow channel distributed along the circumference of the impeller and corresponding to the edge of the impeller. Both side surfaces of the flow channel in the axial direction of the impeller are arcuate surfaces. The arcuate surfaces form an axial inward angle and an axial outward angle. The flow channel and the impeller meet the following conditions:

[0006] h=K1*m;

[0007] a=K2*m;

[0008] R1=K3*(a+m);

[0009] R2=K4*m;

[0010] Among them, the value range of K1 is 0.35~0.45; the value range of K2 is 0.18~0.3; the value range of K3 is 0.75~1; the value range of K4 is 0.75~0.8;

[0011] Among them, m is the thickness of the impeller; h is the distance from the flow channel to the impeller blades in the axial direction of the impeller; a is the distance from the flow channel to the impeller blades in the radial direction of the impeller; R1 is the distance from the axial inward angle of the flow channel to the impeller blades; R2 is the distance from the axial outward angle of the flow channel to the impeller blades.

[0012] The beneficial effects of the present invention are:

[0013] The present invention provides a UAV fuel pump, in which the side of the flow channel is designed to be a curved surface to replace the traditional right-angled surface, and the curved surface forms an axial inward angle and an axial outward angle. The axial inward angle and the axial outward angle are both smooth curved surfaces, which can effectively avoid the generation of eddy currents caused by right angles and reduce the energy loss at right angles, that is, achieve lower noise. At the same time, the designed flow channel and impeller meet a specific conversion relationship, so that under the condition of meeting the same head and flow rate, the diameter of the overall structure can be reduced from 80mm to 60mm, and the weight can be reduced by 65% to 75%, that is, lighter weight and smaller volume are achieved. If the volume does not change, a higher pump pressure can be achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic structural diagram of an end cover of a UAV fuel pump according to the present invention;

[0015] Figure 2 This is a schematic structural diagram of a bottom shell of a UAV fuel pump according to the present invention;

[0016] Figure 3 This is a schematic structural diagram of an impeller of a UAV fuel pump according to the present invention;

[0017] Figure 4 A partial cross-sectional view of a UAV fuel pump according to the present invention;

[0018] Description of labels:

[0019] 1. End cover; 11. Second annular groove; 2. Bottom shell; 21. First annular groove; 3. Impeller; 31. Impeller edge; 4. Flow channel; 5. Liquid inlet; 6. Liquid outlet. Implementation Method

[0020] To illustrate the technical content, achieved objectives and effects of the present invention in detail, the following description is given in conjunction with the embodiments and accompanying drawings.

[0021] Please refer to Figures 1-4 A fuel pump for an unmanned aerial vehicle (UAV) includes a UAV body, a fuel tank and a fuel pump respectively provided on the UAV body, the fuel tank being connected to the fuel pump, the fuel pump including a pump body and an impeller provided in the pump body, the pump body being provided with a flow channel distributed along the circumference of the impeller and corresponding to the edge position of the impeller, the two side surfaces of the flow channel in the axial direction of the impeller being arcuate surfaces, the arcuate surfaces forming an axial inward angle and an axial outward angle, and the flow channel and the impeller satisfying the following conditions:

[0022] h=K1*m;

[0023] a=K2*m;

[0024] R1=K3*(a+m);

[0025] R2=K4*m;

[0026] Among them, the value range of K1 is 0.35~0.45; the value range of K2 is 0.18~0.3; the value range of K3 is 0.75~1; the value range of K4 is 0.75~0.8;

[0027] Among them, m is the thickness of the impeller; h is the distance from the flow channel to the impeller blades in the axial direction of the impeller; a is the distance from the flow channel to the impeller blades in the radial direction of the impeller; R1 is the distance from the axial inward angle of the flow channel to the impeller blades; R2 is the distance from the axial outward angle of the flow channel to the impeller blades.

[0028] From the above description, it can be seen that the beneficial effects of the present invention are: the UAV fuel pump provided by the present invention designs the side of the flow channel as a curved surface to replace the traditional right-angled surface, and forms an axial inward angle and an axial outward angle on the curved surface. The axial inward angle and the axial outward angle are both smooth curved surfaces, which can effectively avoid the generation of eddy currents caused by right angles and reduce the energy loss at right angles, that is, achieve lower noise. At the same time, the designed flow channel and impeller meet a specific conversion relationship, so that under the condition of meeting the same head and flow rate, the diameter of the overall structure can be reduced from 80mm to 60mm, and the weight can be reduced by 65%~75%, that is, lighter weight and smaller volume are achieved. If the volume size is not changed, a higher pump pressure can be achieved.

[0029] Furthermore, the thickness m of the impeller is 4 mm, the distance h from the flow channel to the impeller blades in the axial direction of the impeller is 1.65 mm, the distance a from the flow channel to the impeller blades in the radial direction of the impeller is 1.05 mm, the distance R1 from the axial inward angle of the flow channel to the impeller blades is 3.79 mm, and the distance R2 from the axial outward angle of the flow channel to the impeller blades is 3.2 mm.

[0030] From the above description, it can be seen that by adopting the above specific parameters, the weight can be reduced from 0.8kg to 0.23kg under the condition of the same head and flow rate, which is a weight reduction of 65%~75%.

[0031] Furthermore, the thickness m of the impeller is 4 mm, the distance h from the flow channel to the impeller blades in the axial direction of the impeller is 1.76 mm, the distance a from the flow channel to the impeller blades in the radial direction of the impeller is 1.16 mm, the distance R1 from the axial inward angle of the flow channel to the impeller blades is 4.64 mm, and the distance R2 from the axial outward angle of the flow channel to the impeller blades is 3.16 mm.

[0032] From the above description, it can be seen that by adopting the above specific parameters, the lift can be increased from 50m to 100m under the condition of the same weight and flow rate.

[0033] Furthermore, the fuel pump is made of non-metallic material.

[0034] From the above description, it can be seen that the use of non-metallic materials can further reduce the overall weight.

[0035] Furthermore, the pump body is formed by a bottom shell and an end cover covering each other, and the opposite surfaces of the bottom shell and the end cover are provided with annular grooves distributed along the circumference of the impeller and corresponding to the edge position of the impeller, and the two annular grooves are symmetrically arranged with the plane where the impeller is located as the symmetry plane.

[0036] It can be seen from the above description that the annular groove and the side wall formed by the connection between the bottom shell and the end cover together form the above-mentioned flow channel.

[0037] Furthermore, the pump body is provided with a liquid inlet and a liquid outlet, and the liquid inlet and the liquid outlet are respectively communicated with the two ends of the annular groove.

[0038] Please refer to Figures 1 to 4 , embodiment 1 of the present invention is:

[0039] A drone fuel pump includes a drone body, a fuel tank, and a fuel pump, each mounted on the drone body. The fuel tank is connected to the fuel pump, and the fuel pump is made of a non-metallic material. Using non-metallic materials can further reduce the overall weight. Specifically, the pump is injection molded using a plastic material.

[0040] The fuel pump includes a pump body and an impeller 3 disposed therein. The pump body is formed by a bottom shell 2 and an end cover 1 that overlap each other. The bottom shell 2 and end cover 1 have opposing surfaces each provided with a first annular groove 21 and a second annular groove 11, respectively, distributed along the circumference of the impeller 3 and corresponding to the impeller edge 31. The first and second annular grooves are symmetrically arranged about the impeller's radial plane. The pump body is provided with a liquid inlet 5 and a liquid outlet 6, respectively communicating with the ends of the flow channel 4.

[0041] The pump body is provided with a flow channel 4 distributed along the circumference of the impeller and corresponding to the edge position of the impeller. The flow channel is formed by the annular groove and the side wall formed by the connection between the bottom shell and the end cover.

[0042] Both sides of the flow channel in the axial direction of the impeller are arc-shaped surfaces, and the arc-shaped surfaces form an axial inward angle and an axial outward angle. The flow channel and the impeller meet the following conditions:

[0043] h=K1*m;

[0044] a=K2*m;

[0045] R1=K3*(a+m);

[0046] R2=K4*m;

[0047] Among them, the value range of K1 is 0.35~0.45; the value range of K2 is 0.18~0.3; the value range of K3 is 0.75~1; the value range of K4 is 0.75~0.8;

[0048] Among them, m is the thickness of the impeller; h is the distance from the flow channel to the impeller blades in the axial direction of the impeller; a is the distance from the flow channel to the impeller blades in the radial direction of the impeller; R1 is the distance from the axial inward angle of the flow channel to the impeller blades; R2 is the distance from the axial outward angle of the flow channel to the impeller blades.

[0049] Please refer to Figures 1 to 4 , the second embodiment of the present invention is:

[0050] Based on the above embodiment 1, the thickness m of the impeller is 4 mm, the distance h from the flow channel to the impeller blades in the axial direction of the impeller is 1.65 mm, the distance a from the flow channel to the impeller blades in the radial direction of the impeller is 1.05 mm, the distance R1 from the axial inward angle of the flow channel to the impeller blades is 3.79 mm, and the distance R2 from the axial outward angle of the flow channel to the impeller blades is 3.2 mm.

[0051] And compared with the existing product with a right-angled flow channel (before improvement), the details are as follows:

[0052] Before improvement After improvement m 4mm 4mm a 2.3mm 1.05mm h 3.5mm 1.65mm R1 0 3.79mm R2 0 3.2mm Lift 50 meters 50 meters flow 6 liters 6 liters weight 0.8kg 0.23kg

[0053] Table 1

[0054] It can be seen from Table 1 above that, under the condition that the impeller size remains unchanged, by designing the structure of the flow channel, which is designed as a curved surface and forming an axial inward angle and an axial outward angle on the curved surface, and the axial inward angle and the axial outward angle are both smooth curved surfaces, the diameter of the overall structure can be reduced from 80 mm to 60 mm, and the weight can be reduced from 0.8 kg to 0.23 kg while meeting the same head and flow rate, that is, lighter weight and smaller volume are achieved.

[0055] Please refer to Figures 1 to 4 , the third embodiment of the present invention is:

[0056] Based on the above embodiment 1, the thickness m of the impeller is 4 mm, the distance h from the flow channel to the impeller blades in the axial direction of the impeller is 1.76 mm, the distance a from the flow channel to the impeller blades in the radial direction of the impeller is 1.16 mm, the distance R1 from the axial inward angle of the flow channel to the impeller blades is 4.64 mm, and the distance R2 from the axial outward angle of the flow channel to the impeller blades is 3.16 mm.

[0057] And compared with the existing product with a right-angled flow channel (before improvement), the details are as follows:

[0058] Before improvement After improvement m 4mm 4mm a 2.3mm 1.16mm h 3.5mm 1.76mm R1 0 4.64mm R2 0 3.16mm flow 6 liters 6 liters weight 0.8kg 0.8kg Lift 50 meters 100 meters

[0059] Table 2

[0060] It can be seen from Table 2 above that, under the condition that the impeller size remains unchanged, by designing the structure of the flow channel, which is designed as a curved surface and forming an axial inward angle and an axial outward angle on the curved surface, and the axial inward angle and the axial outward angle are both smooth curved surfaces, the head can be increased from the original 50 meters to 100 meters while meeting the same weight and flow rate, that is, a higher pump pressure can be achieved.

[0061] In summary, the present invention provides a UAV fuel pump, in which the side of the flow channel is designed to be a curved surface to replace the traditional right-angled surface, and the inward angle of the axis and the outward angle of the axis are formed on the curved surface. The inward angle of the axis and the outward angle of the axis are both smooth curved surfaces, which can effectively avoid the generation of eddy currents caused by right angles and reduce the energy loss at right angles, that is, achieve lower noise. At the same time, the designed flow channel and impeller meet a specific conversion relationship, so that under the condition of meeting the same head and flow rate, the diameter of the overall structure can be reduced from 80mm to 60mm, and the weight can be reduced by 65% to 75%, that is, lighter weight and smaller volume are achieved. If the volume size is not changed, a higher pump pressure can be achieved.

[0062] The above descriptions are merely embodiments of the present invention and are not intended to limit the patent scope of the present invention. Any equivalent transformations made using the contents of the present invention's description and drawings, or directly or indirectly applied in related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A UAV fuel pump, comprising a UAV body, a fuel tank and a fuel pump respectively provided on the UAV body, wherein the fuel tank is connected to the fuel pump, and the fuel pump comprises a pump body and an impeller provided in the pump body, characterized in that: The pump body is provided with a flow channel distributed along the circumference of the impeller and corresponding to the edge of the impeller. Both sides of the flow channel in the axial direction of the impeller are arc-shaped surfaces, and the arc-shaped surfaces form an axial inward angle and an axial outward angle. The flow channel and the impeller meet the following conditions: h=K1*m; a=K2*m; R1=K3*(a+m); R2=K4*m; Among them, the value range of K1 is 0.35~0.45; the value range of K2 is 0.18~0.3; the value range of K3 is 0.75~1; the value range of K4 is 0.75~0.8; Among them, m is the thickness of the impeller; h is the distance from the flow channel to the impeller blades in the axial direction of the impeller; a is the distance from the flow channel to the impeller blades in the radial direction of the impeller; R1 is the distance from the axial inward angle of the flow channel to the impeller blades; R2 is the distance from the axial outward angle of the flow channel to the impeller blades.

2. The UAV fuel pump according to claim 1, characterized in that: The thickness m of the impeller is 4 mm, the distance h from the flow channel to the impeller blades in the axial direction of the impeller is 1.65 mm, the distance a from the flow channel to the impeller blades in the radial direction of the impeller is 1.05 mm, the distance R1 from the axial inward angle of the flow channel to the impeller blades is 3.79 mm, and the distance R2 from the axial outward angle of the flow channel to the impeller blades is 3.2 mm.

3. The UAV fuel pump according to claim 1, characterized in that: The thickness m of the impeller is 4 mm, the distance h from the flow channel to the impeller blades in the axial direction of the impeller is 1.76 mm, the distance a from the flow channel to the impeller blades in the radial direction of the impeller is 1.16 mm, the distance R1 from the axial inward angle of the flow channel to the impeller blades is 4.64 mm, and the distance R2 from the axial outward angle of the flow channel to the impeller blades is 3.16 mm.

4. The UAV fuel pump according to claim 1, characterized in that: The fuel pump is made of non-metallic material.

5. The UAV fuel pump according to claim 1, characterized in that: The pump body is composed of a bottom shell and an end cover covering each other. An annular groove is provided on the opposite surfaces of the bottom shell and the end cover along the circumference of the impeller and corresponding to the edge position of the impeller. The two annular grooves are symmetrically arranged with the plane where the impeller is located as the symmetry plane.

6. The UAV fuel pump according to claim 5, characterized in that: The pump body is provided with a liquid inlet and a liquid outlet, and the liquid inlet and the liquid outlet are respectively communicated with the two ends of the annular groove.

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