A small aircraft refueling device

Abstract

The utility model relates to the technical field of small airplane refueling, disclose a small airplane refueling device, including cart, oil storage device, oil supply device, refueling gun, filter device, exhaust device and flow detection device, oil supply device and oil storage device all are located on the cart, and the oil inlet end of oil supply device is passed through the oil inlet pipeline intercommunication with oil storage device, and its oil outlet end is passed through the oil outlet pipeline intercommunication with refueling gun, and oil supply device is used for extracting the fuel in oil storage device, and is transported to refueling gun, refueling gun is hung and is established on the cart, filter device is located on the oil outlet end of oil storage device, and is used for filtering the fuel that oil storage device exports, exhaust device and flow detection device are located on the oil inlet pipeline in proper order, and flow detection device is used for detecting the fuel flow in oil inlet pipeline, and exhaust device is located in the upstream of flow detection device, and is used for discharging the air in oil inlet pipeline. The utility model can solve how to improve the problem of fuel quality and the precision of fuel flow detection.

Description

Technical Field

[0001] This utility model relates to the field of small aircraft refueling technology, specifically to a small aircraft refueling device. Background Technology

[0002] With the booming development of general aviation, the number of small aircraft is increasing, and their refueling needs are becoming more prominent. However, existing aircraft refueling equipment has revealed many limitations when dealing with small aircraft refueling scenarios. Currently, most mainstream aircraft refueling equipment on the market is fixed or large mobile, which cannot be moved flexibly and cannot meet the refueling needs of small aircraft in different sites and locations. To address this, small aircraft refueling equipment has been developed. For example, utility model patent CN204340836U discloses a helicopter refueling vehicle for ships and airports, including a vehicle body and a refueling device. The vehicle body is equipped with rolling wheels and a grounding wire. The refueling device includes an oil suction pipe, a refueling pump, a first connecting pipe, an oil-water separator, a second connecting pipe, a valve, a third connecting pipe, a refueling pump flow meter, a refueling pipe winding turntable, a refueling pipe, and a refueling nozzle. This refueling vehicle has a simple structure and is suitable not only for refueling aircraft at airports but also for refueling helicopters parked on ships. The refueling location for helicopters is no longer limited, and it is also more suitable for refueling services for small general aviation equipment.

[0003] However, the aforementioned existing technologies still have some problems that urgently need to be solved in practical applications. On the one hand, there is a lack of effective fuel filtration structures. During storage and transportation, fuel inevitably becomes mixed with various impurities, such as dust, rust, and moisture. If these impurities enter the aircraft fuel tank directly without filtration, they will enter the engine along with the fuel, causing wear on the engine's precision components, seriously affecting engine performance, reducing its efficiency, and even potentially leading to engine failure, posing a serious threat to flight safety. On the other hand, existing aircraft refueling devices lack precise fuel flow detection functions and automatic fuel cut-off functions. During refueling, relying solely on the operator's experience and a simple flow meter to control the refueling amount makes it difficult to achieve precise refueling control. Due to potential errors in the operator's judgment of the refueling amount, or the possibility of malfunctions in the refueling equipment itself, excessive fuel may be injected into the aircraft fuel tank. This not only wastes fuel and increases operating costs, but also, if the overflowing fuel comes into contact with an open flame or a high-temperature object, it can easily cause a fire or even an explosion, seriously threatening the lives and property of the operators.

[0004] Therefore, in order to ensure the safe operation of small aircraft, it is necessary to develop a small aircraft refueling device to solve the problems existing in the above-mentioned aircraft refueling devices. Utility Model Content

[0005] (a) Technical problems to be solved This invention provides a small aircraft refueling device, which can at least solve the technical problem of how to improve fuel quality and the accuracy of fuel flow detection.

[0006] (II) Technical Solution To solve the above-mentioned technical problems, this utility model provides the following technical solution: a small aircraft refueling device, comprising: trolley; The system includes a fuel storage device, a fuel supply device, and a refueling nozzle. Both the fuel supply device and the fuel storage device are mounted on a trolley. The fuel storage device is used to hold fuel. The fuel supply device's inlet end is connected to the fuel storage device via an inlet pipe, and its outlet end is connected to the refueling nozzle via an outlet pipe. The fuel supply device is used to extract fuel from the fuel storage device and deliver it to the refueling nozzle. The refueling nozzle is mounted on the trolley and is used to connect to the aircraft fuel tank to deliver fuel to the aircraft fuel tank. A filter device is installed at the oil outlet of the oil storage device and is used to filter the fuel output by the oil storage device. An exhaust device and a flow detection device are sequentially installed on the fuel inlet line. The flow detection device is used to detect the fuel flow rate in the fuel inlet line, and the exhaust device is located upstream of the flow detection device and is used to expel air from the fuel inlet line.

[0007] Further details regarding the aforementioned refueling nozzle include: The gun body includes the gun body and the oil inlet pipe and oil outlet pipe provided on the gun body. The gun body is provided with a Venturi chamber, a diaphragm chamber and a sensing channel. The oil inlet pipe, the Venturi chamber and the oil outlet pipe are connected in sequence. The air outlet of the sensing channel is connected to the diaphragm chamber and the oil outlet pipe respectively. The air inlet of the sensing channel is opened on the inner wall of the oil outlet of the oil outlet pipe and is used to communicate with the outside air. The gun body is also provided with a connecting rod through hole. One end of the connecting rod through hole is coaxially arranged and connected to the diaphragm chamber, and the other end is connected to the outside air. The trigger handle and valve core are located between the oil inlet pipe and the Venturi chamber. The trigger handle is connected to the valve core and is used to drive the valve core to connect or disconnect the oil inlet pipe and the Venturi chamber. A diaphragm is movably disposed within the diaphragm cavity along the axial direction of the diaphragm cavity, dividing the diaphragm cavity into a first cavity and a second cavity. The first cavity is connected to the air outlet of the sensing channel, and the second cavity is connected to the connecting rod through hole. The linkage mechanism is located at the linkage through hole of the gun body. One end of the linkage mechanism is connected to the side of the diaphragm facing the second cavity, and the other end is rotatably connected to the trigger handle. The linkage mechanism has a spring force that drives the diaphragm to move away from the linkage through hole, so as to drive the trigger handle and valve core to shut off the oil inlet pipe and the Venturi chamber.

[0008] Furthermore, the opening of the aforementioned diaphragm cavity near the connecting rod through hole is conical, and its diameter gradually decreases toward the connecting rod through hole; The linkage mechanism includes a push rod and a second elastic element. One end of the push rod is slidably disposed in the connecting rod through hole and connected to the side of the diaphragm facing the second cavity. The other end extends out of the connecting rod through hole and is rotatably connected to the trigger handle. The second elastic element is disposed in the connecting rod through hole. One end of the second elastic element is fixedly connected to the gun body, and the other end is fixedly connected to the push rod. The second elastic element has a spring force that drives the push rod to move towards the diaphragm, so as to drive the diaphragm to move away from the connecting rod through hole, and to drive the trigger handle and valve core to shut off the oil inlet pipe and the Venturi chamber.

[0009] Furthermore, the inlet of the aforementioned oil outlet pipe is conical, with its diameter gradually increasing along the oil outlet direction; The fuel nozzle also includes a third elastic element and a check piston adapted to the inlet of the fuel outlet pipe. The check piston is movably located inside the fuel outlet pipe. One end of the third elastic element is fixedly connected to the nozzle body, and the other end is fixedly connected to the check piston. The third elastic element has a spring force that drives the check piston to move toward the inlet of the fuel outlet pipe, so as to restrict the fuel from flowing unidirectionally from the Venturi chamber into the fuel outlet pipe.

[0010] Furthermore, the inlet end of the aforementioned oil outlet pipe is screwed onto the gun body, and a filter screen is installed at the outlet end of the oil outlet pipe.

[0011] Further configuration: the aforementioned fuel supply device includes a fuel pump and a mobile power supply, both of which are mounted on a trolley. The fuel pump's inlet is connected to the fuel storage device via an inlet pipe, and its outlet is connected to the fuel nozzle via an outlet pipe. The fuel pump is also electrically connected to the power supply or mobile power supply of the small aircraft to be refueled.

[0012] Furthermore, the aforementioned oil supply device also includes a rain cover, which is mounted on the trolley and covers the power bank.

[0013] Furthermore, the aforementioned small aircraft refueling device also includes an equipotential bonding device, which includes a winch and alligator clips. The winch and the mobile power supply are positioned opposite each other on both sides of the trolley, and cables are wound on the winch. During refueling, the cable is connected to the round end of the alligator clip, which in turn is connected to the small aircraft to be refueled.

[0014] (III) Beneficial Effects Compared with the prior art, the small aircraft refueling device provided by this utility model has the following advantages: When using the small aircraft refueling device provided by this utility model, firstly, the outlet end of the refueling nozzle is inserted into the fuel tank of the aircraft to be refueled; then, the fuel supply device is activated and the refueling nozzle is opened. The fuel supply device draws fuel from the fuel storage device, and the fuel flows sequentially through the inlet and outlet lines to the refueling nozzle, which then pumps the fuel into the aircraft's fuel tank. It can be seen that this utility model has a compact overall structure, is easy to move using a trolley, and can adapt to the refueling needs of small aircraft in different locations and sites. Furthermore, during the refueling process, the filtration device effectively removes impurities from the fuel, improving fuel quality and protecting the aircraft engine; the exhaust device removes air from the inlet line, effectively preventing air from entering the flow detection device along with the fuel, thus ensuring the accuracy of fuel delivery and flow detection. The combination of the flow detection device and the exhaust device effectively prevents air from affecting fuel delivery and measurement accuracy, thereby improving the accuracy of fuel flow detection, accurately controlling the refueling amount, preventing excessive fuel from being injected into the aircraft's fuel tank, and improving the accuracy and reliability of refueling operations. Attached Figure Description

[0015] Figure 1 This is a perspective view of the small aircraft refueling device in the embodiment; Figure 2 This is a perspective view of the small aircraft refueling device in the embodiment after the rain cover has been removed; Figure 3 This is a schematic diagram of the structure of the refueling nozzle after it has been cut open in the embodiment.

[0016] Icon labels: 1. Trolley; 11. Handrail; 12. Base frame; 13. Casters; 2. Oil storage device; 3. Oil supply device; 31. Oil pump; 32. Portable power supply; 33. Rain cover; 4. Fuel nozzle; 41. Nozzle body; 411. Venturi chamber; 412. Diaphragm chamber; 4121. First chamber; 4122. Second chamber; 413. Sensor channel; 414. Connecting rod through hole; 42. Oil inlet pipe; 43. Oil outlet pipe; 431. Filter screen; 44. Trigger handle; 45. Valve core; 451. Switch piston; 452. Linkage rod; 453. First elastic element; 46. Diaphragm; 47. Linkage mechanism; 471. Push rod; 472. Second elastic element; 48. Third elastic element; 49. Check piston; 5. Filtering device; 6. Exhaust device; 7. Flow detection device; 8. Oil inlet pipe; 9. Oil outlet pipe; 10. Equipotential bonding device; 101. Winch; 102. Alligator clip; 103. Cable. Detailed Implementation

[0017] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0018] This invention provides a small aircraft refueling device to address the problems of improving fuel quality and the accuracy of fuel flow detection.

[0019] See Figure 1 and Figure 2 As shown, Figure 1 This is a perspective view of the small aircraft refueling device in the embodiment. Figure 2 The image shown is a perspective view of the small aircraft refueling device in the embodiment after the rain cover has been removed. The small aircraft refueling device includes a trolley 1, an oil storage device 2, an oil supply device 3, a refueling nozzle 4, a filter device 5, an exhaust device 6, and a flow detection device 7.

[0020] Both the fuel supply device 3 and the fuel storage device 2 are mounted on the trolley 1 by means of screws or welding. The fuel storage device 2 is used to hold fuel. The fuel inlet of the fuel supply device 3 is connected to the fuel storage device 2 via the fuel inlet pipe 8, and its outlet is connected to the refueling nozzle 4 via the fuel outlet pipe 9. The fuel supply device 3 is used to extract fuel from the fuel storage device 2 and deliver it to the refueling nozzle 4. The refueling nozzle 4 is attached to the trolley 1 and is used to connect to the aircraft fuel tank to deliver fuel to the aircraft fuel tank.

[0021] The filter device 5 is installed on the oil outlet end of the oil storage device 2 and is used to filter the fuel output by the oil storage device 2.

[0022] The exhaust device 6 and the flow detection device 7 are sequentially installed on the fuel inlet line 8. The flow detection device 7 is used to detect the fuel flow rate in the fuel inlet line 8. The exhaust device 6 is located upstream of the flow detection device 7 and is used to expel air from the fuel inlet line 8.

[0023] When using the small aircraft refueling device described above, firstly, the outlet end of the refueling nozzle 4 is inserted into the fuel tank of the aircraft to be refueled; then, the fuel supply device 3 is activated and the refueling nozzle 4 is opened. The fuel supply device 3 draws fuel from the fuel storage device 2, and the fuel flows sequentially through the inlet pipe 8 and the outlet pipe 9 to the refueling nozzle 4, which then pumps the fuel into the aircraft fuel tank. It can be seen that this utility model has a compact overall structure, is easily moved by the trolley 1, and can adapt to the refueling needs of small aircraft in different locations and sites. Furthermore, during the refueling process, the filter device 5 effectively removes impurities from the fuel, improving fuel quality and protecting the aircraft engine; the exhaust device 6 expels air from the inlet pipe 8, effectively preventing air from entering the flow detection device 7 along with the fuel, thus affecting the accuracy of fuel delivery and the metering of the flow detection device 7; the combination of the flow detection device 7 and the exhaust device 6 effectively prevents air from affecting fuel delivery and metering accuracy, thereby effectively improving the accuracy of fuel flow detection, accurately controlling the refueling amount, avoiding excessive fuel injection into the aircraft fuel tank, and improving the accuracy and reliability of refueling operations.

[0024] The aforementioned filter device 5 can use existing cartridge filters or similar filters. The flow detection device 7 can use existing gear flow meters (such as AK-LC-A cast iron oval gear flow meters), which are suitable for flow detection of various oils. The venting device 6 can use existing venting valves.

[0025] See Figure 1 and Figure 2 As shown, in one embodiment of the trolley 1, the trolley 1 includes a handle 11, a base frame 12, and casters 13. The base plate supports the oil storage device 2. The handle 11 is fixed to one side of the base frame 12 by welding or integral connection. The casters 13 are rotatably connected to the bottom of the base frame 12. In this way, the casters 13 and the handle 11 work together to facilitate the user to drag the entire refueling device in any direction, thereby improving the ease of use and flexibility of the device.

[0026] The trolley 1 mentioned above can be made of aluminum alloy, which greatly reduces the weight of the device and improves its portability.

[0027] See Figure 1 , Figure 2 and Figure 3 As shown, Figure 3This is a schematic diagram of the cross-section of the refueling nozzle in one embodiment. The refueling nozzle 4 includes a nozzle body 41, an inlet pipe 42, an outlet pipe 43, a trigger handle 44, a valve core 45, a diaphragm 46, and a connecting rod mechanism 47. The inlet pipe 42 and the outlet pipe 43 are integrally connected or screwed onto the nozzle body 41. The nozzle body 41 contains a Venturi chamber 411, a diaphragm chamber 412, and a sensing channel 413. The inlet pipe 42, the Venturi chamber 411, and the outlet pipe 43 are sequentially connected. The air outlet of the sensing channel 413 is connected to both the diaphragm chamber 412 and the outlet pipe 43. The air inlet of the sensing channel 413 is located on the inner wall of the outlet of the outlet pipe 43 and is used to communicate with external air. The nozzle body 41 also has a connecting rod through hole 414. One end of the connecting rod through-hole 414 is coaxially connected to and communicates with the diaphragm cavity 412, while the other end communicates with external air. A valve core 45 is installed between the oil inlet pipe 42 and the venturi chamber 411. A trigger handle 44 is connected to the valve core 45 and is used to connect or disconnect the oil inlet pipe 42 and the venturi chamber 411. A diaphragm 46 is axially connected within the diaphragm cavity 412, dividing it into a first cavity 4121 and a second cavity 4122. The first cavity 4121 communicates with the air outlet of the sensing channel 413, and the second cavity 4122 communicates with the connecting rod through-hole 414. A connecting rod mechanism 47 is installed at the connecting rod through-hole 414 of the gun body 41. One end of the connecting rod mechanism 47 is connected to the side of the diaphragm 46 facing the second cavity 4122, and the other end is rotatably connected to the trigger handle 44. The linkage mechanism 47 has a spring force that drives the diaphragm 46 to move away from the linkage through-hole 414, thereby causing the trigger handle 44 and valve core 45 to shut off the fuel inlet pipe 42 and the venturi chamber 411. Thus, when the refueling nozzle 4 is not refueling, the valve core 45 defaults to shutting off the fuel inlet pipe 42 and the fuel outlet pipe 43, preventing fuel from flowing out of the refueling nozzle 4, and the pressure on both sides of the diaphragm 46 is balanced (both at atmospheric pressure), so the diaphragm 46 remains stationary. When the trigger handle 44 is pulled to refuel the aircraft fuel tank, the trigger handle 44 drives the valve core 45 to connect the fuel inlet pipe 42 and the venturi chamber 411, and the fuel flows along... Figure 3The fuel flows sequentially through the inlet pipe 42, the venturi chamber 411, and the outlet pipe 43 in the direction of the middle arrow, and finally flows into the aircraft fuel tank. During this fuel delivery process, the high-speed flowing fuel generates negative pressure in the venturi chamber 411, which drives external air to flow into the diaphragm chamber 412 through the sensing channel 413. Under the action of the air pressure in the first chamber 4121, the diaphragm 46 compresses the elastic force of the linkage mechanism 47 and moves toward the linkage through hole 414. The linkage mechanism 47 drives the trigger handle 44 and the valve core 45 to remain in the position connecting the inlet pipe 42 and the venturi chamber 411. As the fuel level in the aircraft fuel tank rises, when it submerges the air inlet of the sensing channel 413, the sensing channel 413 stops drawing in outside air and begins to draw in fuel. Since the density and viscosity of fuel are much greater than air, it cannot flow through the sensing channel 413 as quickly. At this point, the diaphragm chamber 412 can no longer draw in enough fluid through the sensing channel 413 to maintain the previous negative pressure state, causing the negative pressure to disappear. Under the pressure of the second chamber 4122 and the elastic force of the linkage mechanism 47, the diaphragm 46 displaces away from the linkage through-hole 414, returning to its initial position. Simultaneously, the linkage mechanism 47 drives the trigger handle 44 and valve core 45 to quickly shut off the fuel inlet pipe 42 and the venturi chamber 411, cutting off fuel flow and maintaining it in the closed position, making it impossible to pull the trigger handle. If it is necessary to pull the trigger handle 44, simply remove the refueling nozzle 4 from the aircraft fuel tank, exposing the air inlet of the sensing channel 413 back to the air, and then pull the trigger handle 44 again to refuel. As can be seen, the refueling nozzle 4, through the coordinated action of components such as the trigger handle 44, valve core 45, diaphragm 46, and linkage mechanism 47, can automatically and quickly cut off fuel delivery when the fuel in the aircraft fuel tank reaches the preset level or when an abnormality occurs (the fuel in the aircraft fuel tank submerges the air inlet of the sensing channel 413), effectively preventing excessive fuel from being injected into the aircraft fuel tank. In conjunction with the exhaust device 6 and flow detection device 7, it achieves precise control of fuel delivery, improving the safety and convenience of refueling operations.

[0028] The diaphragm 46 can be integrally molded from rubber materials such as nitrile rubber (NBR), and the thickness of the diaphragm 46 ranges from 0.2 to 0.5 mm.

[0029] See Figure 3As shown, in one embodiment of the valve core 45, the valve core 45 includes a switching piston 451, a linkage rod 452, and a first elastic element 453. The linkage rod 452 is slidably connected between the oil inlet pipe 42 and the Venturi chamber 411. One end of the linkage rod 452 is integrally connected to the switching piston 451, and the other end extends out of the gun body 41 and is connected to the trigger handle 44 by means of abutment or rotation. The linkage rod 452 is used to drive the switching piston 451 to connect or disconnect the oil inlet pipe 42 and the Venturi chamber 411. One end of the first elastic element 453 is fixedly connected to the gun body 41 by means of adhesion or hanging, and the other end is fixedly connected to the switching piston 451 by means of adhesion or hanging. The first elastic element 453 has a spring force that drives the switching piston 451 toward the position displacement of disconnecting the oil inlet pipe 42 and the Venturi chamber 411. Thus, when the refueling nozzle 4 is not refueling, the switching piston 451, under the elastic force of the first elastic element 453, moves to the position of cutting off the fuel inlet pipe 42 and the venturi chamber 411, preventing fuel from flowing out of the refueling nozzle 4. When the trigger handle 44 is pulled to refuel the aircraft fuel tank, the trigger handle 44 drives the linkage rod 452 to compress the first elastic element 453, causing the switching piston 451 to connect the fuel inlet pipe 42 and the venturi chamber 411. It can be seen that the valve core 45, through the cooperation of the switching piston 451, the linkage rod 452, and the first elastic element 453, can realize the delivery and cut-off of fuel.

[0030] The aforementioned switch piston 451 can be made of rubber material, and the first elastic element 453 can be a compression spring or a tension spring.

[0031] See Figure 3As shown, in one embodiment of the linkage mechanism 47, the linkage mechanism 47 includes a push rod 471 and a second elastic member 472. The diaphragm cavity 412 has a conical opening near the connecting rod through hole 414, with its diameter gradually decreasing towards the connecting rod through hole 414. One end of the push rod 471 is slidably connected within the connecting rod through hole 414 and is connected to the side of the diaphragm 46 facing the second cavity 4122 by abutment or hooking. The other end of the push rod 471 extends out of the connecting rod through hole 414 and is rotatably connected to the trigger handle 44. The second elastic member 472 is located within the connecting rod through hole 414. One end of the second elastic member 472 is fixed to the gun body 41 by adhesion or hooking, and the other end is fixed to the push rod 471 by adhesion or tight abutment. The second elastic element 472 has a spring force that drives the push rod 471 to move towards the diaphragm 46, thereby causing the diaphragm 46 to move away from the connecting rod through hole 414, and causing the trigger handle 44 and valve core 45 to shut off the oil inlet pipe 42 and the Venturi chamber 411. Thus, when the trigger handle 44 is pulled to refuel the aircraft fuel tank, the diaphragm 46 compresses the spring force of the second elastic element 472 under the air pressure of the first cavity 4121, causing the push rod 471 to move towards the connecting rod through hole 414 together. During this process, the conical design of the opening of the diaphragm cavity 412 gradually increases the resistance to the movement of the diaphragm 46 towards the connecting rod through hole 414, effectively limiting the movement position of the diaphragm 46. When the liquid level submerges the air inlet of the sensing channel 413, the diaphragm 46, under the action of the air pressure in the second chamber 4122 and the elastic force of the second elastic element 472, moves away from the connecting rod through hole 414 together with the push rod 471 and quickly returns to the initial position. The push rod 471 drives the trigger handle 44 to remain in the closed position and cannot be pulled. The trigger handle 44 drives the valve core 45 to quickly cut off the oil inlet pipe 42 and the venturi chamber 411, cutting off the fuel flow.

[0032] The second elastic element 472 mentioned above can be a compression spring or a tension spring.

[0033] See Figure 3As shown, in one embodiment of the linkage mechanism 47, the fuel nozzle 4 further includes a third elastic element 48 and a check piston 49. The inlet of the fuel outlet pipe 43 is conical, with its diameter gradually increasing along the fuel outlet direction. The check piston 49 is adapted to the inlet of the fuel outlet pipe 43. The check piston 49 is movably connected inside the fuel outlet pipe 43. One end of the third elastic element 48 is fixedly connected to the nozzle body 41 by bonding or hanging, and the other end is fixedly connected to the check piston 49 by bonding or hanging. The third elastic element 48 has a spring force that drives the check piston 49 to move towards the inlet of the fuel outlet pipe 43, thereby restricting the unidirectional flow of fuel from the Venturi chamber 411 into the fuel outlet pipe 43. Thus, the check piston 49 and the third elastic element 48 combine to form a one-way valve structure, which, in conjunction with the oil inlet of the oil outlet pipe 43, ensures that fuel can only flow from the Venturi chamber 411 into the oil inlet of the oil outlet pipe 43 in one direction, effectively preventing fuel backflow, ensuring the stability and safety of the refueling process, and avoiding equipment failure and fuel waste caused by fuel backflow.

[0034] The aforementioned check piston 49 can be made of rubber material, and the third elastic element 48 can be a compression spring or a tension spring.

[0035] See Figure 2 and Figure 3 As shown, in one embodiment of the fuel outlet pipe 43, the inlet end of the fuel outlet pipe 43 is screwed onto the nozzle body 41, and the outlet end of the fuel outlet pipe 43 is equipped with a filter screen 431. Thus, the fuel outlet pipe 43 can be easily installed and removed by a simple rotation. This detachable design facilitates quick replacement of the fuel outlet pipe 43 according to the type of aircraft fuel tank, adapting to different aircraft refueling ports, thereby effectively improving the adaptability of the device and achieving the effect of reducing time and increasing efficiency. The filter screen 431 at the outlet end of the fuel outlet pipe 43 can further filter out tiny impurities in the fuel, further improving the quality of the fuel entering the aircraft fuel tank, thereby further protecting the aircraft engine and extending its service life.

[0036] See Figure 2As shown, in one embodiment of the fuel supply device 3, the fuel supply device 3 includes a fuel pump 31 and a mobile power supply 32. Both the fuel pump 31 and the mobile power supply 32 are screwed onto the trolley 1. The fuel inlet of the fuel pump 31 is connected to the fuel storage device 2 via a fuel inlet pipe 8, and its outlet is connected to the refueling nozzle 4 via a fuel outlet pipe 9. The fuel pump 31 is also electrically connected to the power supply of the small aircraft to be refueled or to the mobile power supply 32. Thus, the fuel supply device 3, using a combination of the fuel pump 31 and the mobile power supply 32, provides a flexible power supply method, adapting to the power supply needs of different scenarios, ensuring the normal operation of the fuel pump 31, achieving stable fuel delivery, and improving the versatility and practicality of the refueling device. Specifically, in most cases, the fuel pump 31 is externally powered by the power supply on the small aircraft to be refueled, providing the power required for the fuel pump 31 during operation. When encountering field operations or situations where the small aircraft to be refueled has no available power, the fuel pump 31 is electrically connected to the mobile power supply 32 built into the device to ensure the normal operation of the refueling work.

[0037] The aforementioned oil pump 31 can use a combination of an existing small electric motor (such as a GAMAK 90S MOTOR DC motor) and a cycloidal gear pump to draw fuel from the oil storage device 2 and deliver it to the refueling nozzle 4. This embodiment is smaller in size and power, making the refueling device more flexible in outdoor working environments.

[0038] See Figure 1 As shown, based on the above embodiment, the fuel supply device 3 also includes a rain cover 33. The rain cover 33 is installed on the trolley 1 by means of screws or welding, and covers the mobile power supply 32. In this way, the rain cover 33 can shield the mobile power supply 32 from rain and dust, effectively protecting the mobile power supply 32 and preventing damage to the mobile power supply 32 in severe weather during field operations, thereby further ensuring the safety of the fuel refueling process.

[0039] The aforementioned rain cover 33 can be made of 304 stainless steel, which can effectively protect the internal power bank 32.

[0040] See Figure 1 and Figure 2As shown, based on any of the above embodiments, the small aircraft refueling device further includes an equipotential bonding device 10. The equipotential bonding device 10 includes a winch 101 and an alligator clip 102. The winch 101 is mounted on the trolley 1 by welding or screwing, and the winch 101 and the mobile power supply 32 are located opposite each other on opposite sides of the trolley 1. A cable 103 is wound around the winch 101. During refueling, the cable 103 is connected to the round end of the alligator clip 102, and the alligator clip 102 is connected to the small aircraft to be refueled. Thus, during refueling, the cable 103 is connected to the small aircraft to be refueled through the alligator clip 102 to form an equipotential bond, which can eliminate the potential difference between the device and the small aircraft to be refueled, effectively preventing fires or explosions caused by static electricity buildup, thereby further ensuring the safety of the fuel refueling process. The winch 101 facilitates the storage of the cable 103.

[0041] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A small aircraft refueling device, characterized in that, include: trolley; The system includes a fuel storage device, a fuel supply device, and a refueling nozzle. Both the fuel supply device and the fuel storage device are mounted on the trolley. The fuel storage device is used to hold fuel. The fuel supply device's inlet end is connected to the fuel storage device via an inlet pipe, and its outlet end is connected to the refueling nozzle via an outlet pipe. The fuel supply device is used to extract fuel from the fuel storage device and deliver it to the refueling nozzle. The refueling nozzle is mounted on the trolley and is used to connect to the aircraft fuel tank to deliver fuel to the aircraft fuel tank. A filter device is provided at the oil outlet of the oil storage device and is used to filter the fuel output by the oil storage device. An exhaust device and a flow detection device are sequentially installed on the fuel inlet pipe. The flow detection device is used to detect the fuel flow rate in the fuel inlet pipe, and the exhaust device is located upstream of the flow detection device and is used to exhaust the air in the fuel inlet pipe.

2. The small aircraft refueling device according to claim 1, characterized in that, The refueling nozzle includes: The gun body includes a gun body and an oil inlet pipe and an oil outlet pipe disposed on the gun body. The gun body is provided with a Venturi chamber, a diaphragm chamber and a sensing channel. The oil inlet pipe, the Venturi chamber and the oil outlet pipe are connected in sequence. The air outlet of the sensing channel is connected to the diaphragm chamber and the oil outlet pipe respectively. The air inlet of the sensing channel is opened on the inner wall of the oil outlet of the oil outlet pipe and is used to communicate with the outside air. The gun body is also provided with a connecting rod through hole. One end of the connecting rod through hole is coaxially arranged and connected to the diaphragm chamber, and the other end is connected to the outside air. A trigger handle and a valve core, wherein the valve core is located between the oil inlet pipe and the Venturi chamber, and the trigger handle is connected to the valve core and is used to drive the valve core to connect or disconnect the oil inlet pipe and the Venturi chamber; A diaphragm is movably disposed within the diaphragm cavity along the axial direction of the diaphragm cavity, dividing the diaphragm cavity into a first cavity and a second cavity. The first cavity is connected to the air outlet of the sensing channel, and the second cavity is connected to the connecting rod through hole. A linkage mechanism is provided at the linkage through hole of the gun body. One end of the linkage mechanism is connected to the side of the diaphragm facing the second cavity, and the other end is rotatably connected to the trigger handle. The linkage mechanism has an elastic force that drives the diaphragm to move away from the linkage through hole, so as to drive the trigger handle and the valve core to shut off the oil inlet pipe and the Venturi chamber.

3. The small aircraft refueling device according to claim 2, characterized in that, The opening of the diaphragm cavity near the connecting rod through hole is conical, and its diameter gradually decreases toward the connecting rod through hole. The linkage mechanism includes a push rod and a second elastic element. One end of the push rod is slidably disposed in the connecting rod through hole and connected to the side of the diaphragm facing the second cavity. The other end extends out of the connecting rod through hole and is rotatably connected to the trigger handle. The second elastic element is disposed in the connecting rod through hole. One end of the second elastic element is fixedly connected to the gun body, and the other end is fixedly connected to the push rod. The second elastic element has a spring force that drives the push rod to move towards the diaphragm, so as to drive the diaphragm to move away from the connecting rod through hole, and to drive the trigger handle and the valve core to shut off the oil inlet pipe and the Venturi chamber.

4. The small aircraft refueling device according to claim 2 or 3, characterized in that, The oil inlet of the oil outlet pipe is conical, and its diameter gradually increases along the oil outlet direction; The fuel nozzle also includes a third elastic element and a check piston adapted to the inlet of the fuel outlet pipe. The check piston is movably disposed inside the fuel outlet pipe. One end of the third elastic element is fixedly connected to the nozzle body, and the other end is fixedly connected to the check piston. The third elastic element has a spring force that drives the check piston to move toward the inlet of the fuel outlet pipe, so as to restrict fuel from flowing unidirectionally from the Venturi chamber into the fuel outlet pipe.

5. The small aircraft refueling device according to claim 2 or 3, characterized in that, The oil inlet end of the oil outlet pipe is screwed onto the gun body, and the oil outlet end of the oil outlet pipe is equipped with a filter screen.

6. The small aircraft refueling device according to any one of claims 1-3, characterized in that, The fuel supply device includes a fuel pump and a mobile power supply, both of which are mounted on the trolley. The fuel pump's inlet is connected to the fuel storage device via the fuel inlet pipe, and its outlet is connected to the fuel nozzle via the fuel outlet pipe. The fuel pump is also electrically connected to the power supply of the small aircraft to be refueled or the mobile power supply.

7. The small aircraft refueling device according to claim 6, characterized in that, The oil supply device also includes a rain cover, which is mounted on the trolley and covers the portable power source.

8. The small aircraft refueling device according to claim 6, characterized in that, The small aircraft refueling device also includes an equipotential bonding device, which includes a winch and alligator clips. The winch is positioned opposite to the mobile power supply on both sides of the trolley, and a cable is wound around the winch. During refueling, the cable is connected to the round end of the alligator clip, and the alligator clip is connected to the small aircraft to be refueled.

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