Engine electric control oil supply device for model airplane and unmanned aerial vehicle

Abstract

The utility model discloses an engine electronic control oil supply device for model airplanes and unmanned aerial vehicles, which comprises an oil tank, an oil supply pipeline and an oil supply device, the oil supply device comprises a micro gear pump, the liquid outlet end of the micro gear pump is connected with a buffer cavity, an adjusting pipe is arranged in the buffer cavity, a movable block is movably arranged in the adjusting pipe, and the movable block is connected with the micro gear pump. The fuel tank, the fuel supply pipeline and the fuel supply device are arranged, the fuel supply device comprises the buffering cavity, fuel enters the buffering cavity and then enters an engine, bubbles in the fuel are effectively eliminated, the fuel can be effectively prevented from entering the engine through the adjusting pipe and the movable block, and the fuel can be effectively prevented from entering the engine through the adjusting pipe and the movable block. The movable block slides in the adjusting pipe to control the staggered area of the through hole and the through groove, the oil supply pressure is adjusted, the stable oil supply pressure is guaranteed, oil is supplied through the micro gear pump, and the oil supply pipeline can generate large negative pressure to suck fuel oil.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle equipment, in particular to an electronically controlled oil supply device for an engine of a model aircraft and a unmanned aerial vehicle. Background Art

[0002] Currently, the fuel supply system for model aircraft or drones typically consists of a fuel tank, fuel pipe, carburetor, and weight. The fuel pipe, which extends into the fuel tank, is connected to the weight at one end and directly to the carburetor's oil inlet at the other. The negative pressure generated within the cylinder during engine operation drives the carburetor's diaphragm to pump oil, forming a so-called mechanical fuel supply system. However, this mechanical fuel supply system has several drawbacks. First, bubbles easily form in the fuel tank during flight, and the carburetor can easily inhale these bubbles, causing the engine to stall. Second, when the fuel tank is low, large pitch movements of the aircraft or drone can easily expose the weight above the fuel level, preventing the carburetor from drawing fuel, which can also cause the engine to stall and potentially cause the aircraft or drone to fall and be damaged. Third, this fuel supply system cannot maintain stable fuel pressure, making it impossible to accurately control the fuel supply volume and fuel atomization. Therefore, an electronically controlled fuel supply device for engine models and drones is proposed. Utility Model Content

[0003] The purpose of the present invention is to provide an electronically controlled oil supply device for an engine of a model aircraft and a UAV, so as to solve the problems raised in the above-mentioned background technology.

[0004] In order to solve the above technical problems, the utility model provides the following technical solutions: an electronically controlled oil supply device for an engine of a model aircraft and an unmanned aerial vehicle, comprising a fuel tank, an oil supply pipeline, and an oil supply device, wherein one end of the oil supply pipeline is connected to a heavy hammer and is arranged inside the fuel tank, and the other end of the oil supply pipeline is connected to the oil supply device, and the oil supply device comprises a micro gear pump, which is driven by a drive motor, and the liquid inlet end of the micro gear pump is connected to the oil supply pipeline, and the liquid outlet end of the micro gear pump is connected to a buffer cavity, an adjusting tube is provided inside the buffer cavity, and a movable block is provided inside the adjusting tube for movement, and a through groove is provided through the end surface of the movable block, and a through hole is provided through the side wall of the adjusting tube corresponding to the through groove, and one end of the oil outlet pipe is connected to the outer surface of the adjusting tube corresponding to the through hole, and the other end of the oil outlet pipe passes through the side wall of the buffer cavity and is connected to the engine.

[0005] According to the above technical solution, one end of the adjusting tube passes through the side wall of the buffer cavity, the inner circumference of one end of the adjusting tube away from the side wall of the buffer cavity is fixedly connected to the limiting ring, and an elastic element is provided between the adjusting tube and the movable block.

[0006] According to the above technical solution, a sliding groove is provided on the outer circumference of the movable block, and a sliding block is provided on the inner circumference of the regulating tube in sliding connection with the sliding groove.

[0007] According to the above technical solution, a sealing ring is provided on the outer peripheral surface of the movable block.

[0008] According to the above technical solution, an adjusting block is movably provided at one end of the adjusting tube away from the movable block, an elastic element is provided between the adjusting block and the movable block, the adjusting block is screwed to the adjusting tube, a sealing cover is fixedly connected to the outer surface of the adjusting tube, a rotating rod is penetrated and rotatably provided on the end surface of the sealing cover, the rotating rod penetrates the end surface of the adjusting block and is movably connected to the adjusting block, a worm gear connected to the rotating rod is rotatably provided on the surface of the sealing cover, the outer surface of the sealing cover is fixedly connected to the outer shell, the outer surface of the outer shell is fixedly connected to the motor, and the motor is connected to a worm gear meshing with the worm gear.

[0009] According to the above technical solution, a one-way valve is provided at the liquid outlet of the micro gear pump.

[0010] Compared with the prior art, the beneficial effects achieved by the present invention are as follows: the present invention is provided with a fuel tank, a fuel supply pipeline and a fuel supply device, the fuel supply device includes a buffer chamber, and the fuel enters the buffer chamber and then enters the engine, thereby effectively eliminating bubbles in the fuel; by providing a regulating tube and a movable block, the movable block slides inside the regulating tube to control the area of the intersection of the through hole and the through groove, and adjusts the fuel supply pressure to ensure a stable fuel supply pressure; the fuel is supplied by a micro gear pump, and the fuel supply pipeline can generate a large negative pressure to absorb the fuel, so that even if there is not much fuel in the fuel tank, sufficient fuel can be sucked in. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0012] Figure 1 This is a schematic diagram of the main cross-sectional structure of the utility model;

[0013] Figure 2 This is a structural diagram of the oil supply device of the utility model;

[0014] Figure 3 This is a schematic diagram of the internal split structure of the regulating tube of the utility model;

[0015] In the figure: 1- oil tank, 2- oil supply pipeline, 3- weight, 4- micro gear pump, 5- drive motor, 6- buffer chamber, 7- adjusting tube, 8- movable block, 9- through groove, 10- through hole, 11- oil outlet pipe, 12- limiting ring, 13- slide groove, 14- worm, 15- sealing ring, 16- adjusting block, 17- cover, 18- rotating rod, 19- worm gear, 20- housing, 21- motor. DETAILED DESCRIPTION

[0016] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0017] See also Figure 1-3 The utility model provides a technical solution: an electronically controlled fuel supply device for an engine of a model aircraft and a UAV, comprising a fuel tank 1, a fuel supply pipeline 2, and a fuel supply device, such as Figure 1 As shown, one end of the oil supply line 2 is connected to a weight 3 and is arranged inside the fuel tank 1 to ensure that the oil supply line is located at the bottom of the fuel to ensure the oil supply effect. The other end of the oil supply line 2 is connected to the oil supply device, and the oil supply device includes a micro gear pump 4. The micro gear pump 4 is driven by a drive motor 5. The liquid inlet end of the micro gear pump 4 is connected to the oil supply line 2, as shown in FIG. Figure 1 As shown, the liquid outlet end of the micro gear pump 4 is connected with a buffer chamber 6, and the fuel is first pumped into the buffer chamber 6 to reduce the bubbles in the fuel from being pumped into the engine. An adjusting tube 7 is provided inside the buffer chamber 6, and a movable block 8 is provided inside the adjusting tube 7. The outer peripheral surface of the movable block 8 fits the inner wall of the adjusting tube 7, and the movable block 8 can slide along the axial direction of the adjusting tube 7. A through groove 9 is provided through the end surface of the movable block 8, and a through hole 10 is provided through the side wall of the adjusting tube 7 corresponding to the through groove 9. One end of an oil outlet pipe 11 is connected to the outer surface of the adjusting tube 7 corresponding to the through hole 10, and the other end of the oil outlet pipe 11 penetrates the side wall of the buffer chamber 6 and is connected to the engine. The fuel pumped into the buffer chamber 6 flows into the oil outlet pipe 11 through the through hole 10 and the through groove 9. By controlling the position of the movable block 8 inside the adjusting tube 7 and the cross-sectional area of the through hole 10 and the through groove 9, the oil supply pressure is adjusted.

[0018] Specifically, one end of the regulating tube 7 passes through the side wall of the buffer chamber 6, and the inner circumference of the end of the regulating tube 7 away from the side wall of the buffer chamber 6 is fixedly connected to the limit ring 12. An elastic element is provided between the regulating tube 7 and the movable block 8. The elastic element can be a spring. Under the action of the elastic element, the movable block 8 is tightly attached to the limit ring 12. The fuel rushes into the buffer chamber 6 to generate pressure. Under the action of the pressure, the movable block 8 overcomes the movement of the elastic element, thereby realizing adaptive adjustment of the fuel supply pressure.

[0019] Specifically, the outer circumference of the movable block 8 is provided with a slide groove 13, and the inner circumference of the adjustment tube 7 is provided with a slider slidably connected to the slide groove 13 to prevent the movable block 8 from rotating inside the adjustment tube 7 and ensure that the through groove 9 corresponds to the through hole 10;

[0020] Specifically, a sealing ring 15 is provided on the outer circumference of the movable block 8 to ensure a sealing effect, so that the movable block 8 can move inside the regulating tube 7 as the pressure changes;

[0021] Specifically, an adjusting block 16 is movably provided at one end of the adjusting tube 7 away from the movable block 8, an elastic element is provided between the adjusting block 16 and the movable block 8, the adjusting block 16 is screwed to the adjusting tube 7, a cover 17 is fixedly connected to the outer surface of the adjusting tube 7, and a rotating rod 18 is provided on the end surface of the cover 17 and is rotatably provided. The rotating rod 18 passes through the end surface of the adjusting block 16 and is movably connected to the adjusting block 16, as shown in FIG. Figure 3 As shown, the rotating rod 18 is spline-shaped. The rotating rod 18 can drive the adjusting block 16 to rotate, and the adjusting block 16 can slide along the length direction of the rotating rod 18. When the adjusting block 16 rotates, it moves under the action of the threaded fitting to adjust the preload force of the elastic element, thereby adjusting the movement of the movable block 8 to achieve manual adjustment of the oil supply pressure. A worm gear 19 connected to the rotating rod 18 is provided on the surface of the cover 17 for rotation. The outer surface of the cover 17 is fixedly connected to a housing 20. The outer surface of the housing 20 is fixedly connected to a motor 21. The motor 21 is connected to a worm 22 meshing with the worm gear 19. The oil supply pressure is adjusted by the motor 21.

[0022] Specifically, a one-way valve 23 is provided at the outlet of the micro gear pump 4 to prevent the fuel from flowing back.

[0023] When the utility model is used, the driving motor 5 drives the micro gear pump 4 to pump fuel into the buffer chamber 6. The fuel pumped into the buffer chamber 6 generates pressure, so that the movable block 8 overcomes the elastic element and moves inside the regulating tube 7. When the pressure is too large, the area of the intersection of the through groove 9 and the through hole 10 is reduced, thereby reducing the oil supply. When the pressure is too small, the area of the intersection of the through groove 9 and the through hole 10 is increased, increasing the oil supply, realizing the regulation of the oil supply pressure, and stabilizing the oil supply pressure. The motor 21 can drive the worm 22 to rotate, and the worm 22 drives the worm wheel 19 to rotate. The worm wheel 19 controls the rotation of the regulating block 16 through the rotating rod 18, so that the regulating block 16 slides under the action of the threaded fit, and the preload force of the elastic element is adjusted to regulate the oil supply pressure while ensuring the stability of the fuel supply pressure.

[0024] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0025] Finally, it should be noted that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art will be able to modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein with equivalents. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. An electronically controlled fuel supply device for an engine of a model aircraft or a drone, comprising a fuel tank (1), a fuel supply pipeline (2), and a fuel supply device, characterized in that: One end of the oil supply pipeline (2) is connected to a weight (3) and is arranged inside the oil tank (1); the other end of the oil supply pipeline (2) is connected to an oil supply device, and the oil supply device includes a micro gear pump (4). The micro gear pump (4) is driven by a drive motor (5); the liquid inlet end of the micro gear pump (4) is connected to the oil supply pipeline (2); the liquid outlet end of the micro gear pump (4) is connected to a buffer chamber (6); an adjusting tube (7) is provided inside the buffer chamber (6); a movable block (8) is provided inside the adjusting tube (7); a through groove (9) is provided through the end surface of the movable block (8); a through hole (10) is provided through the side wall of the adjusting tube (7) corresponding to the through groove (9); one end of an oil outlet pipe (11) is connected to the outer surface of the adjusting tube (7) corresponding to the through hole (10); the other end of the oil outlet pipe (11) passes through the side wall of the buffer chamber (6) and is connected to the engine.

2. The electronically controlled oil supply device for an engine of a model aircraft or a UAV according to claim 1, characterized in that: One end of the regulating tube (7) passes through the side wall of the buffer cavity (6); the inner circumference of one end of the regulating tube (7) away from the side wall of the buffer cavity (6) is fixedly connected to a limiting ring (12); and an elastic element is provided between the regulating tube (7) and the movable block (8).

3. The electronically controlled oil supply device for an engine of a model aircraft or a UAV according to claim 2, characterized in that: The outer peripheral surface of the movable block (8) is provided with a sliding groove (13), and the inner peripheral surface of the regulating tube (7) is provided with a sliding block slidably connected to the sliding groove (13).

4. The electronically controlled oil supply device for an engine of a model aircraft or a UAV according to claim 3, characterized in that: The outer peripheral surface of the movable block (8) is sleeved with a sealing ring (15).

5. The electronically controlled oil supply device for an engine of a model aircraft or a UAV according to claim 4, characterized in that: An adjusting block (16) is movably provided at one end of the adjusting tube (7) away from the movable block (8), an elastic element is provided between the adjusting block (16) and the movable block (8), the adjusting block (16) is screwed to the adjusting tube (7), a cover (17) is fixedly connected to the outer surface of the adjusting tube (7), a rotating rod (18) is rotatably provided on the end surface of the cover (17), the rotating rod (18) penetrates the end surface of the adjusting block (16) and is movably connected to the adjusting block (16), a worm gear (19) connected to the rotating rod (18) is rotatably provided on the surface of the cover (17), an outer surface of the cover (17) is fixedly connected to the outer surface of the outer shell (20), and an electric motor (21) is fixedly connected to the outer surface of the outer shell (20), and the electric motor (21) is connected to a worm gear (22) meshing with the worm gear (19).

6. The electronically controlled oil supply device for an engine of a model aircraft or a UAV according to claim 5, characterized in that: A one-way valve (23) is provided at the liquid outlet end of the micro gear pump (4).

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