Fuel oil filling device

Abstract

The aviation fuel refueling device comprises a tray frame and a pumping device. The tray frame is used for carrying an aviation fuel drum. The pumping device is arranged on the tray frame and comprises an oil pump assembly, a filter separator, a flow meter, a hose reel and a refueling gun. The oil pump assembly is detachably assembled on the aviation fuel drum. When the oil pump assembly is assembled on the aviation fuel drum, an oil inlet end of the oil pump assembly extends into the aviation fuel drum and contacts oil in the aviation fuel drum. An oil inlet end of the filter separator is communicated with an oil outlet end of the oil pump assembly. An oil inlet end of the flow meter is communicated with an oil outlet end of the filter separator. An oil inlet end of the hose reel is communicated with an oil outlet end of the flow meter. An oil inlet end of the refueling gun is communicated with an oil outlet end of the hose reel. When the oil pump assembly is not assembled on the aviation fuel drum, the oil pump assembly is placed on the tray frame. In this way, the oil in the aviation fuel drum can be conveniently added to aviation equipment, and the operation mode is flexible and convenient to use.

Description

Technical Field

[0001] The present application relates to the technical field of aviation fuel refueling, and in particular to an aviation fuel refueling device. Background Art

[0002] With my country's rapid economic growth, the aviation industry has also experienced significant development. In recent years, as the country has gradually liberalized low-altitude airspace and implemented policies encouraging the development of general aviation, there is an urgent need to strengthen refueling services for general aviation equipment. However, existing aviation fuel refueling equipment is inflexible and inconvenient to use. Summary of the Invention

[0003] The present application provides an aviation fuel refueling device with flexible operation mode and convenient use.

[0004] The present application provides an aviation fuel refueling device, comprising:

[0005] Pallet frames for carrying aviation fuel drums; and

[0006] The oil pumping device is arranged on the pallet frame, and includes an oil pump assembly, a filter separator, a flow meter, a hose reel and a refueling gun; wherein,

[0007] The oil pump assembly can be detachably assembled to the aviation fuel barrel, wherein when the oil pump assembly is assembled to the aviation fuel barrel, the oil inlet end of the oil pump assembly extends into the aviation fuel barrel and contacts the oil in the aviation fuel barrel; the oil inlet end of the filter separator is connected to the oil outlet end of the oil pump assembly; the oil inlet end of the flow meter is connected to the oil outlet end of the filter separator; the oil inlet end of the hose reel is connected to the oil outlet end of the flow meter; the oil inlet end of the refueling gun is connected to the oil outlet end of the hose reel; when the oil pump assembly is not assembled to the aviation fuel barrel, it is placed on the pallet frame.

[0008] Optionally, the oil pump assembly includes an oil pump and a motor driven by the oil pump; wherein the oil pump includes a pump rod and blades arranged in the pump rod, and the blades are arranged at an end of the pump rod away from the motor. When the oil pump assembly is assembled in the aviation fuel barrel, the pump rod extends into the aviation fuel barrel, so that the blades are immersed in the oil in the aviation fuel barrel.

[0009] Optionally, the oil pump and the motor are assembled through a quick-release structure.

[0010] Optionally, the oil pump includes an explosion-proof oil pump.

[0011] Optionally, the motor includes an explosion-proof motor.

[0012] Optionally, the aviation fuel refueling device further includes a transport vehicle, the transport vehicle including a front and a fork extending from the front to the rear, the fork supporting the pallet frame.

[0013] Optionally, the aviation fuel refueling device includes a power supply device and a control box; the power supply device includes a battery, which is assembled on the front of the vehicle, and the control box is assembled on the tray frame. The control box is pluggable and electrically connected to the battery. The control box includes an inverter, and the oil pump assembly is pluggable and electrically connected to the inverter. The inverter converts the direct current output of the battery into alternating current and outputs it to power the oil pump assembly.

[0014] Optionally, the control box includes an explosion-proof control box.

[0015] Optionally, the transport truck includes a liftable fork, and the fork includes a raised state and a lowered state; the pallet frame is provided with a plurality of supporting feet, and the plurality of supporting feet extend downward from the lower surface of the pallet frame; when the fork is in the raised state, the pallet frame is lifted by the fork, and the plurality of supporting feet are off the ground; when the fork is in the lowered state, the pallet frame descends, and the plurality of supporting feet touch the ground.

[0016] Optionally, the pallet frame is provided with a retractable first roller, which includes an extended state and a retracted state. When the fork is in the raised state, the first roller is in the retracted state, and the first roller is off the ground. When the fork is in the lowered state, the first roller is in the extended state, and the first roller is on the ground.

[0017] Optionally, the transport vehicle and the pallet frame can be assembled separately.

[0018] Optionally, the aviation fuel refueling device includes a positioning assembly, which includes a positioning pin and a positioning ring corresponding to the position of the positioning pin, the positioning pin is provided on the side of the pallet frame facing the front of the vehicle and extends in a horizontal direction; the positioning ring is provided on one side of the front of the vehicle, and the opening of the positioning ring faces the pallet frame; when the pallet frame is assembled on the transport vehicle, the positioning pin is correspondingly inserted into the positioning ring, and when the pallet frame is separated from the transport vehicle, the positioning pin is separated from the positioning ring.

[0019] Optionally, the transport vehicle includes an explosion-proof electric transport vehicle.

[0020] Optionally, the pallet frame is provided with a plurality of second rollers and a plurality of brake members corresponding to the positions of the plurality of second rollers, the second rollers are fixed to the bottom of the pallet frame and in contact with the ground, the brake members include a braking position and a non-braking position, wherein when the brake member is in the braking position, the second rollers are braked, and when the brake member is in the non-braking position, the second rollers are released from the brake and can move.

[0021] Optionally, the pallet frame is provided with a plurality of lifting rings, which extend upward from the upper surface of the pallet frame and are used for assembly with external lifting tooling.

[0022] Optionally, the tray frame comprises a stainless steel plate.

[0023] The fuel pump assembly of the aviation fuel refueling device provided in the embodiment of the present application is detachably assembled to the aviation fuel drum. When the fuel pump assembly is assembled to the aviation fuel drum, the oil inlet end of the fuel pump assembly extends into the aviation fuel drum and contacts the fuel inside the drum. When the fuel pump assembly is not assembled to the aviation fuel drum, the fuel pump assembly is placed on the pallet frame. This arrangement facilitates the refueling of aviation equipment from the aviation fuel drum, providing flexible operation and ease of use. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 FIG2 is a structural schematic diagram of an embodiment of an aviation fuel refueling device of the present application in which an oil pump assembly is assembled to an aviation fuel barrel;

[0025] Figure 2 Shown Figure 1 The schematic structural diagram of the aviation fuel refueling device from another perspective is shown;

[0026] Figure 3 Shown Figure 1 The structure diagram of the aviation fuel refueling device shown is another perspective;

[0027] Figure 4 Shown Figure 1 A structural schematic diagram of the aviation fuel refueling device from another perspective;

[0028] Figure 5 Shown Figure 1 A schematic structural diagram of the aviation fuel refueling device from another perspective;

[0029] Figure 6 FIG2 is a structural schematic diagram of an embodiment of the aviation fuel refueling device of the present application in which the oil pump assembly is not assembled in the aviation fuel barrel;

[0030] Figure 7 The figure shows a schematic structural diagram of an embodiment of the aviation fuel refueling device of the present application, wherein the transport vehicle and the pallet structure are separated, wherein the oil pump assembly is not assembled with the aviation fuel barrel;

[0031] Figure 8 Shown is a structural schematic diagram of another embodiment of the tray structure of the aviation fuel refueling device of the present application;

[0032] Figure 9 FIG2 is a cross-sectional view of an embodiment of the quick-release assembly of the aviation fuel refueling device of the present application assembled to an aviation fuel barrel, wherein the oil pump assembly is not assembled to the aviation fuel barrel;

[0033] Figure 10 Shown is a structural schematic diagram of an embodiment of a quick-release assembly of an aviation fuel refueling device of the present application;

[0034] Figure 11 Shown Figure 10 A cross-sectional view of the quick-release assembly of the aviation fuel refueling device shown;

[0035] Figure 12 Shown Figure 10 A schematic cross-sectional view of a quick-release assembly of an aviation fuel refueling device from one perspective is shown;

[0036] Figure 13 Shown Figure 10 A schematic cross-sectional view of the quick-release assembly of the aviation fuel refueling device from another perspective;

[0037] Figure 14 Shown Figure 10 A structural schematic diagram of an embodiment of a fixing seat of a quick-release assembly of an aviation fuel refueling device is shown;

[0038] Figure 15 Shown Figure 14 A front view structural diagram of a fixing seat of a quick-release assembly of an aviation fuel refueling device is shown;

[0039] Figure 16 Shown Figure 14 A schematic cross-sectional view of a fixing seat of a quick-release assembly of an aviation fuel refueling device is shown;

[0040] Figure 17 Shown Figure 10 A schematic structural diagram of a sealing cover of a quick-release assembly of an aviation fuel refueling device is shown;

[0041] Figure 18 Shown Figure 17 A schematic cross-sectional view of a sealing cover of a quick-release assembly of an aviation fuel refueling device is shown;

[0042] Figure 19 Shown Figure 1 A schematic top view of a portion of the structure of the aviation fuel refueling device shown;

[0043] Figure 20 Shown Figure 19 A schematic structural diagram of a partial structure of an aviation fuel refueling device from one perspective is shown;

[0044] Figure 21 Shown Figure 19 A schematic structural diagram of a portion of the aviation fuel refueling device from another perspective;

[0045] Figure 22 Shown Figure 19 A schematic structural diagram of an aviation fuel refueling device in which the oil pump assembly is stored in a storage bracket;

[0046] Figure 23 Shown Figure 22 The schematic diagram of the structure of the receiving bracket A of the aviation fuel refueling device shown;

[0047] Figure 24 Shown Figure 1 The structure diagram of the anti-dumping block of the aviation fuel refueling device shown in FIG.

[0048] Figure 25 Shown Figure 24 A schematic cross-sectional view of an anti-dumping stopper of an aviation fuel refueling device is shown;

[0049] Figure 26 Shown Figure 1 A schematic structural diagram of the anti-dumping block of the aviation fuel refueling device from another perspective is shown;

[0050] Figure 27 Shown Figure 26 A schematic cross-sectional view of an anti-dumping stopper of an aviation fuel refueling device is shown;

[0051] Figure 28 Shown Figure 1 The principle block diagram of the fuel pump power supply circuit of the aviation fuel refueling device shown;

[0052] Figure 29 Shown Figure 28 The principle block diagram of the switch control circuit of the oil pump power supply circuit shown;

[0053] Figure 30 FIG2 is a structural schematic diagram of another embodiment of the anti-dumping stopper of the aviation fuel refueling device of the present application;

[0054] Figure 31 Shown Figure 30 A cross-sectional schematic diagram of another embodiment of an anti-dumping stopper for an aviation fuel refueling device is shown;

[0055] Figure 32 FIG2 is a structural schematic diagram of another embodiment of the anti-dumping stopper of the aviation fuel refueling device of the present application;

[0056] Figure 33 Shown is a structural schematic diagram of yet another embodiment of the anti-dumping block of the aviation fuel refueling device of the present application. DETAILED DESCRIPTION

[0057] Exemplary embodiments will be described in detail herein, with examples illustrated in the accompanying drawings. In the following description, when referring to the drawings, identical numerals in different figures represent identical or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments are not intended to represent all embodiments consistent with the present application. Rather, they are merely examples of devices consistent with certain aspects of the present application, as detailed in the appended claims.

[0058] The terminology used in this application is for the purpose of describing specific embodiments only and is not intended to limit this application. Unless otherwise defined, technical or scientific terms used in this application should have the same ordinary meaning as understood by a person of ordinary skill in the art to which this application belongs. The use of "a," "an," and similar terms in this specification and claims does not indicate a limitation of quantity, but rather indicates the presence of at least one. "A plurality" includes two and is equivalent to at least two. "Includes" or "comprising" and similar terms mean that the elements or objects preceding "includes" or "comprising" include the elements or objects listed after "includes" or "comprising," and their equivalents, and do not exclude other elements or objects. "Connected" or "connected" and similar terms are not limited to physical or mechanical connections and may include electrical connections, whether direct or indirect. As used in this specification and the appended claims, the singular forms "a," "the," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and / or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

[0059] The aviation fuel refueling device of the embodiment of the present application includes a pallet frame and an oil pumping device. The pallet frame is used to carry the aviation fuel barrel. The oil pumping device is arranged on the pallet frame, and the oil pumping device includes an oil pump assembly, a filter separator, a flow meter, a hose reel and a refueling gun. The oil pump assembly can be detachably assembled to the aviation fuel barrel, and when the oil pump assembly is assembled to the aviation fuel barrel, the oil inlet end of the oil pump assembly extends into the aviation fuel barrel and contacts the oil in the aviation fuel barrel; the oil inlet end of the filter separator is connected to the oil outlet end of the oil pump assembly; the oil inlet end of the flow meter is connected to the oil outlet end of the filter separator; the oil inlet end of the hose reel is connected to the oil outlet end of the flow meter; the oil inlet end of the refueling gun is connected to the oil outlet end of the hose reel; when the oil pump assembly is not assembled to the aviation fuel barrel, it is placed on the pallet frame.

[0060] With this arrangement, during the operation, the oil in the aviation fuel barrel can be conveniently added to the aviation equipment. The oil pump assembly can be removed from the aviation fuel barrel, and another barrel of oil can be replaced when the oil in the aviation fuel barrel is used up or almost used up. The operation method is flexible and easy to use, and the entire aviation fuel refueling device allows for refueling using aviation fuel barrels. This makes it suitable for refueling general aviation equipment. The aviation fuel refueling device can be relatively small and can adapt to some relatively harsh geographical environments. For example, it can be used for refueling general aviation equipment in rescue environments.

[0061] The present application provides an aviation fuel refueling device. The aviation fuel refueling device of the present application is described in detail below with reference to the accompanying drawings. The features of the following embodiments and implementations may be combined with each other unless they conflict.

[0062] The aviation fuel refueling device 10 can provide aviation fuel refueling services for general aviation equipment parked on runways and / or aprons, and can also provide aviation fuel refueling services for general aviation equipment parked in earthquake-prone areas, mountainous areas, and other areas with relatively harsh geographical environments. The aviation fuel can be aviation gasoline or aviation kerosene, referred to as "aviation fuel".

[0063] Combine Figures 1 to 6 As shown, the aviation fuel refueling device 10 includes a transport vehicle 100 , a pallet frame 200 , an oil pumping device 300 , a storage bracket 500 , and an anti-dumping block 600 .

[0064] Specifically, the transport truck 100 includes a front end 101 and a fork 102. The fork 102 is connected to the front end 101 and extends from the front end 101 to the rear end of the vehicle. The fork 102 is used to support the pallet frame 200. The rear end refers to the portion opposite the front end 101 and extending away from the front end 101. In some embodiments, the front end 101 is also provided with a handlebar 103 for a worker to control the direction of movement of the transport truck 100, making it convenient for the worker to use the handlebar 103.

[0065] In some embodiments, the pallet frame 200 includes an oil drum support portion 201 for carrying the aviation fuel drum 20. The aviation fuel drum 20 can be manually loaded, unloaded and replaced by an external oil drum transporter, which is simple, easy to operate, and economical. The oil pumping device 300, the storage bracket 500 and the anti-dumping block 600 are provided on (assembled on) the pallet frame 200, and the upper surface of the pallet frame 200 carries the oil pumping device 300, the storage bracket 500 and the anti-dumping block 600. In some embodiments, the pallet frame 200 extends along a first direction X and a second direction Y, wherein the first direction X and the second direction Y are in the same horizontal plane, and the second direction Y is a direction perpendicular to the first direction X (such as Figure 1 shown). Figure 1In the illustrated embodiment, the tray frame 200 may be a rectangular plate, the first direction X may be an extending direction of a long side of the rectangular plate, and the second direction Y may be an extending direction of a short side of the rectangular plate.

[0066] In some embodiments, the pallet frame 200 includes a first side X1 and a second side X2 that are opposite each other in a first direction X. The first side X1 faces the vehicle head 101, while the second side X2 is away from the vehicle head 101. The fuel drum support 201 is positioned closer to the second side X2 relative to the first side X1. In some embodiments, the fork 102 extends from the vehicle head 101 along the first direction X, with the vehicle head 101 located on the first side X1. This arrangement allows the aviation fuel drum 20 placed on the fuel drum support 201 to be separated from the vehicle head 101 and away from it, enhancing safety.

[0067] The aviation fuel refueling device 10 refuels general aviation equipment using gravity refueling. Gravity refueling relies on the weight of the fuel flowing from the fuel outlet of the aviation fuel tank 20 into the general aviation equipment. Refueling efficiency can be improved by using a fuel pumping device 300. In some embodiments, the fuel pumping device 300 includes an oil pump assembly 301, a filter separator 302, a flow meter 303, a hose reel 304, a refueling gun 305, and an oil sight glass 306. The oil pump assembly 301 is detachably assembled to the aviation fuel tank 20 and is used to extract fuel from the tank 20. The oil inlet of the filter separator 302 is connected to the oil outlet of the oil pump assembly 301. The oil inlet of the flow meter 303 is connected to the oil outlet of the filter separator 302. The oil inlet of the hose reel 304 is connected to the oil outlet of the flow meter 303. The oil inlet of the refueling gun 305 is connected to the oil outlet of the hose reel 304. The oil inlet of the oil sight glass 306 is connected to the oil outlet of the oil pump assembly 301. When the aviation fuel flows through the filter separator 302, solid particles and impurities are filtered out by the filter element, and water is separated. The water that sinks to the bottom of the filter separator 302 can be manually drained. The filter separator 302 meets the filtration accuracy of 5μm or complies with the requirements of GB / T 21358-2008, "General Technical Specifications for Jet Fuel Filter Separators." Before each use of the oil pumping device 300, the filter separator 302 must be inspected to ensure safety. The flow meter 303 records and displays the flow rate of the added aviation fuel. The flow meter 303 has a metering accuracy of ±0.2%, providing relatively accurate measurement.

[0068] In some embodiments, the hose reel 304 includes a reel bracket 307, a refueling coil 308 mounted on the reel bracket 307, and a coil handle 309. The refueling nozzle 305 is connected to the flow meter 303 via the refueling coil 308. By operating the coil handle 309, the reel bracket 307 rotates, thereby reeling the refueling coil 308 out of the reel bracket 307 or retracting the refueling coil 308 back into the refueling coil bracket 307. This ensures that the entire oil pumping device 300 has a compact structure and minimizes its footprint. In some embodiments, the refueling coil 308 can be reeled manually or with a spring. In some embodiments, the refueling coil 308 has a rated flow rate of up to 25 L / min for gravity refueling. The thickness of the refueling coil 308 is 20 mm to 40 mm, preferably 30 mm, and the length of the refueling coil 308 can reach 15 m. In some embodiments, the oil sight glass 306 can observe whether the oil (pure or contaminated) in the refueling line passes through the refueling coil 308 and reaches the refueling gun 305 to ensure smooth refueling.

[0069] In some embodiments, the coil handle 309 is located on the side of the reel support 307 facing away from the oil drum support 201 in the first direction X. During refueling, the coil handle 309 is operated to unwind the refueling coil 308. The coil handle 309 is located on the side of the reel support 307 facing the vehicle front 101, with at least a portion of the handle positioned directly above the vehicle front 101. This facilitates operator operation. Furthermore, the lowest point of rotation of the coil handle 309 is higher than the top surface of the vehicle front 101. This prevents the top surface of the vehicle front 101 from being touched during operation, facilitating ease of use. In some embodiments, the refueling gun 305 is located on the side of the reel support 307 facing away from the coil handle 309 in the first direction X. The refueling gun 305 and coil handle 309 are located on either side of the reel support 307. This effectively utilizes the side space of the reel support 307, making the aviation fuel refueling device 10 compact, and also facilitates operator operation.

[0070] exist Figures 1 to 5 In the embodiment shown, when the oil pump assembly 301 is assembled in the aviation fuel barrel 20, the oil inlet end of the oil pump assembly 301 extends into the aviation fuel barrel 20 and contacts the oil in the aviation fuel barrel 20. Since aviation gasoline is a low-flashpoint fuel, the oil inlet end of the oil pump assembly 301 is extended into the aviation fuel barrel 20 and is in full contact with the aviation fuel. This method can prevent the oil inlet end of the oil pump assembly 301 from contacting the air, avoid sparks, and provide higher safety. Compared with related technologies using self-priming oil pumps, the embodiments of the present application can avoid the generation of oil and gas due to air pressure, which can cause air blockage and cavitation of the oil pump assembly 301. Figure 6In the illustrated embodiment, when the oil pump assembly 301 is not assembled with the aviation fuel drum 20, it is placed on the pallet frame 200. When refueling is required, the oil pump assembly 301 is assembled with the aviation fuel drum 20; when refueling is not required, the oil pump assembly 301 is placed on the pallet frame 200. This facilitates the refueling of aviation equipment from the aviation fuel drum 20 during operation. The oil pump assembly can be removed from the aviation fuel drum, allowing replacement with another drum of fuel when the fuel in the drum is depleted or nearly depleted. This provides a flexible and convenient operation method, and the entire aviation fuel refueling device allows refueling from aviation fuel drums. This makes it suitable for refueling general aviation equipment. The aviation fuel refueling device can be relatively compact and adaptable to harsh geographical environments, such as for refueling general aviation equipment in disaster relief environments.

[0071] Furthermore, when refueling is not required, placing the oil pump assembly 301 on the pallet frame 200 provides greater safety during transportation. Since the oil pump assembly 301 has a certain weight and volume, if it is assembled into the aviation fuel drum 20 and cannot be removed, it will add a certain amount of weight to the top of the aviation fuel drum 20, shifting the center of gravity upward and making it prone to tipping during transportation, potentially creating a safety hazard. Furthermore, leaving the oil pump assembly 301 inserted into the aviation fuel drum 20 for an extended period of time could also affect the oil content within the drum 20.

[0072] Combine Figure 22 and Figure 23In the illustrated embodiment, the oil pump assembly 301 includes an oil pump 310 and a motor 311 drivingly connected to the oil pump 310. The motor 311 can provide power to the oil pump 310 to drive the oil pump 310 to operate. The oil pump 310 includes a pump rod 312, a blade 313 disposed within the pump rod 312, a support seat 314, and an oil inlet end 315 disposed on the pump rod 312 away from the oil pump 310 and an oil outlet end 316 disposed near the oil pump 310. The blade 313 is disposed at the end of the pump rod 312 away from the motor 311 and closer to the oil inlet end 315 relative to the oil outlet end 316. The support seat 314 is disposed between the oil inlet end 315 and the oil outlet end 316 of the oil pump 310 and is disposed closer to the oil outlet end 316 relative to the oil inlet end 315. When the oil pump assembly 301 is assembled in the aviation fuel barrel 20, the pump rod 312 is inserted into the aviation fuel barrel 20, the oil inlet end 315 is inserted into the aviation fuel barrel 20, the blades 313 are immersed in the oil in the aviation fuel barrel 20, and the oil outlet end 316 is exposed to the aviation fuel barrel 20 and connected to the external pipeline. Since aviation gasoline is a low-flashpoint fuel, the blades 313 are fully in contact with the oil in the aviation fuel barrel 20. This method can prevent the oil inlet end 315 of the oil pump 310 from coming into contact with the air, avoid the generation of sparks, and provide higher safety. In addition, during this oil pumping process, the tube wall of the pump rod 312 is clamped with the oil outlet of the aviation fuel barrel 20, and the support seat 314 is in contact with the oil outlet of the aviation fuel barrel 20, ensuring that it is not easy to detach during the oil pumping process, and has better stability.

[0073] In some embodiments, the oil pump 310 can be a vane-type liquid pump. This pump 310 does not require priming and can run dry for up to 30 minutes, completely preventing damage from running dry. The oil pump 310 and motor 311 feature infinitely variable speeds, enabling adjustable flow rates to meet varying refueling requirements. The maximum flow rate can reach 50L, allowing personnel to flexibly configure the pump based on actual needs. Furthermore, the motor 311 is equipped with an overheating protection device to prevent burnout due to overload.

[0074] In some embodiments, the aviation fuel refueling system 10 further includes a flame arrester vent valve 317, which is assembled at the air inlet of the aviation fuel tank 20. This allows the tank 20 to communicate with the outside world. This valve balances the air pressure within the tank 20 and prevents external flames from entering the tank 20, providing a high level of safety. In some embodiments, the aviation fuel refueling system further includes a pressure monitoring assembly (not shown) that monitors system pressure in real time to ensure safe operation and maintenance.

[0075] In some embodiments, the oil pump 310 and the motor 311 are assembled through a quick-disassembly structure. The quick-disassembly structure assembly has the advantages of compact structure, convenient docking and installation, and no need for auxiliary tools; on the other hand, it is easy to disassemble and clean, and convenient for maintenance. In some embodiments, the oil pump 310 includes an explosion-proof oil pump, and its power consumption can reach 880W. In some embodiments, the motor 311 includes an explosion-proof motor. By providing an explosion-proof oil pump and an explosion-proof motor, explosions are prevented and safety is high. In some embodiments, the overall weight range of the oil pump 310 and the motor 311 is 4kg to 8kg. Compared with the related oil pump assembly 301, it is lighter and easier to carry and maintain. In some embodiments, the model of the oil pump assembly 301 can be HD-E2-V+SS304-1000HP or a German FLUX barrel pump.

[0076] In some embodiments, the transporter 100 comprises an electric transporter. In some embodiments, the transporter 100 comprises an explosion-proof electric transporter. The explosion-proof electric transporter has electronic steering and an explosion-proof rating of IIB T4 Gb. Since the transporter 100 transports aviation gasoline, a low-flashpoint fuel, which has higher safety requirements, the use of the explosion-proof electric transporter is safer. In some embodiments, the heavy-load dimensions of the transporter 100 are 2300mm*1000mm*2100mm, and the empty-load dimensions are 2300mm*1000mm*1200mm. In some embodiments, the maximum allowable gross mass of the transporter 100 can reach 1.5t, and its carrying capacity is relatively large. The maximum speed of the transporter 100 can reach 4km / h.

[0077] In some embodiments, the transport vehicle 100 includes a power supply device 104 and a cable storage box 105. The power supply device 104 includes a battery 801 (such as Figure 28 As shown), a power output line (not shown) and a power output interface 106, a battery 801 is provided on the front of the vehicle 101, and the power output line connects the battery 801 and the power output interface 106. A cable storage box 105 is provided on the front of the vehicle 101, and the cable storage box 105 is used to store the power output line, and the power output interface 106 is provided on one side of the cable storage box 105. By providing the cable storage box 105 to store the power output line, the space occupied by the power output line is reduced, and the layout of the front of the vehicle 100 is made more compact and the appearance is more beautiful. And the external interface is connected through the power output interface, which has a higher safety factor. It should be noted that since the power output line is located in the cable storage box 105, it is not shown in the accompanying drawings.

[0078] In some embodiments, the battery 801 can be an explosion-proof battery that does not support removal for charging. In some embodiments, the battery 801 is a rechargeable battery. In some embodiments, the battery 801 can output 24VDC, the charging time is 4 to 6 hours, and the maximum load capacity is 1.5t. The minimum ground clearance of the battery 801 is 20mm to 40mm, and the preferred value is 30mm. In some embodiments, the battery capacity of the battery 801 includes 85AH (ampere hours) or 210AH (ampere hours). In this embodiment, the battery capacity of the battery 801 is 85AH, which can support the transport vehicle 100 to move about 12km, or support the loading and refueling operation for about 2 hours. In some other embodiments, the battery capacity of the battery 801 is 210AH, which can support the transport vehicle 100 to move about 25km, or support the loading and refueling operation for about 6 hours.

[0079] exist Figure 2 In the illustrated embodiment, the power supply device 104 includes a main power switch 107 and an on / off indicator light 108. The main power switch 107 and the on / off indicator light 108 are located on the top surface of the vehicle head 101 and are electrically connected to the battery 801. The main power switch 107 is used to control the on / off of the battery 801, thereby shutting off the power in an emergency to protect operational safety. The on / off indicator light 108 indicates the operating status of the main power switch 107. For example, when the main power switch 107 is on, the on / off indicator light 108 illuminates; when the main power switch 107 is off, the on / off indicator light 108 does not illuminate. Furthermore, the main power switch 107 and the on / off indicator light 108 are located on the top surface of the vehicle head 101 to facilitate operation by the operator.

[0080] In some embodiments, the cable storage box 105 is located on the front side of the truck 101, facing away from the forks 102. Because the oil pumping device 300 is placed on the pallet frame 200 on the side of the truck 101 facing the forks 102, the oil pumping device 300 is close to the truck 101, resulting in limited space. However, the front side of the truck 101, facing away from the forks 102, faces the handlebars 103, providing ample space. Placing the cable storage box 105 on this side effectively utilizes space and makes the overall layout of the truck 100 more compact. In some embodiments, the cable storage box 105 includes a first storage box side 109 extending in the direction of the forks 102 and a second storage box side 110 opposite the first storage box side 109. The power output port 106 is located on the first storage box side 109. The first storage box side 109 and the oil drum support 201 are located on different sides. Placing the power output port 106 on this first storage box side 109 facilitates connecting an external power cord.

[0081] In some embodiments, the transport vehicle 100 also includes a driving warning light 111 and a charging port 112, electrically connected to the battery 801. The driving warning light 111 is located on one side of the vehicle's front 101. Specifically, it is located on the side 110 of the second storage box. The driving warning light 111 serves to alert nearby vehicles to avoid traffic while the transport vehicle 100 is in motion. Since the power output cable of the battery 801 is stored in the cable storage box 105, the driving warning light 111 is located on the side 110 of the second storage box to facilitate connection to the power output cable. Furthermore, the power output port 106 and the driving warning light 111 are symmetrically located on the sides 109 and 110 of the first and second storage boxes. This reduces power output cable wiring while effectively utilizing the side of the cable storage box 105, making the transport vehicle 100 compact and aesthetically pleasing. The charging port 112 is located on one side of the vehicle's front 101, next to the power supply unit 104, to facilitate connection to an external power cable. In some embodiments, the charging port 112 includes an explosion-proof socket, which has good explosion-proof performance and high safety.

[0082] In some embodiments, the transport truck 100 is equipped with front wheels 113 and multiple rear wheels 114. The front wheels 113 extend downward from the lower surface of the vehicle's front end 101, while the multiple rear wheels 114 extend downward from the lower surface of the forks 102 and are located in an area away from the forks 102. In this embodiment, the vertical length of the aviation fuel drum 20 is between 850 mm and 900 mm, with a preferred value of 890 mm. When fully filled with fuel, the drum 20 can weigh between 150 kg and 200 kg, with a preferred value of 170 kg. When empty, the drum 20 can weigh between 15 kg and 20 kg, with a preferred value of 19 kg. As can be seen from the above data, the weight of the aviation fuel drum 20 is relatively large, whether fully filled or empty. The multiple rear wheels 114 are located in an area away from the forks 102, away from the vehicle's front end 101, to bear the majority of the weight of the drum 20, making the transportation of the aviation fuel refueling device 10 more stable.

[0083] In some embodiments, the pallet frame 200 is provided with a plurality of lifting rings 202, which extend upward from the upper surface of the pallet frame 200 and are used for assembly with external lifting tooling. In this embodiment, the pallet frame 200 is rectangular, and four lifting rings 202 are provided, which are respectively located at the four corners of the pallet frame 200. For example, in cases where a certain height or special practical scenarios are required, external transport tooling can be connected to multiple lifting rings 202 to ensure normal refueling, which can increase the application scenarios. In some embodiments, the pallet frame 200 includes a stainless steel plate. The stainless steel plate is highly corrosion-resistant, static-conductive, explosion-proof, and highly safe. The stainless steel plate is also relatively hard and strong.

[0084] exist Figure 3 and Figure 7In the embodiment shown, the transport vehicle 100 and the pallet frame 200 can be assembled separately. In some embodiments, the transport vehicle 100 includes a liftable fork 102, and the fork 102 includes a lifting state (such as Figure 3 as shown) and depressed state (as shown Figure 7 (As shown). In some embodiments, the pallet frame 200 is equipped with multiple support legs 203 extending downward from the bottom surface of the pallet frame 200. When the fork 102 is in the raised position, the pallet frame 200 is lifted by the fork, and the multiple support legs 203 are lifted off the ground. The truck 100 can then move the pallet frame 200, the oil pumping device 300, and the aviation fuel drum 20 mounted thereon. When moving to a designated location, the fork 102 switches from the raised position to the lowered position. When the fork 102 is in the lowered position, the pallet frame 200 descends, and the multiple support legs 203 touch the ground. The multiple support legs 203 then provide support and fixation, securing the truck 100, the pallet frame 200, and the oil pumping device 300 mounted thereon. This prevents movement during the refueling process, ensuring safety. In this embodiment, four support legs 203 are provided, each located at the four corners of the pallet frame 200.

[0085] In some embodiments, the aviation fuel refueling device 10 includes a positioning assembly 700, which includes a positioning pin 701 and a positioning ring 702 corresponding to the position of the positioning pin 701. The positioning pin 701 is provided on the side of the tray frame 200 facing the vehicle head 101 and extends in the horizontal direction; the positioning ring 702 is provided on the side of the vehicle head 101, and the opening of the positioning ring 702 faces the tray frame 200. Figures 1 to 5 In the embodiment shown, when the pallet frame 200 is assembled on the transport vehicle 100, the positioning pins 701 are correspondingly inserted into the positioning rings 702. Figure 6 In the illustrated embodiment, when the pallet frame 200 is separated from the transport vehicle 100, the positioning pin 701 separates from the positioning ring 702. The positioning pin 701 and positioning ring 702 enable quick assembly and positioning of the transport vehicle 100 and the pallet frame 200. In other embodiments, the positioning assembly 700 may also be a magnetic assembly, which is not a limitation in this application.

[0086] In some embodiments, the pallet frame 200 is provided with a retractable first roller 204, which extends downward from the lower surface of the pallet frame 200 and is located in the middle region of the pallet frame 200. Due to the heavy weight of the aviation fuel drum 20 and the fuel pumping device 300, the first roller 204 is located in the middle region of the pallet frame 200 to support the weight of the aviation fuel drum 20 and the fuel pumping device 300, thereby locating the center of gravity of the entire aviation fuel refueling device 10 in the middle region of the pallet frame 200, thereby providing greater stability during movement.

[0087] In some embodiments, the first roller 204 includes an extended state and a retracted state, wherein the fork 102 is in an upward state (eg, Figure 3 When the pallet frame 200 is in the retracted position (as shown), the first roller 204 is in the retracted position and the first roller 204 is off the ground. When the fork 102 is in the lowered position, the first roller 204 is in the extended position and the first roller 204 is on the ground (not shown). By providing the retractable first roller 204, the pallet frame 200 can be towed and moved by an external traction tool. This allows for flexible movement when the transport vehicle 100 is not provided, thereby expanding the application scenarios.

[0088] exist Figure 8 In the illustrated embodiment, the pallet frame 200 is equipped with a plurality of second rollers 205 and a plurality of brake members 206 corresponding to the positions of the second rollers 205. The second rollers 205 are fixed to the bottom of the pallet frame 200 and in contact with the ground. The brake members 206 include a braking position 2061 and a non-braking position 2062. When the brake members 206 are in the braking position 2061, the second rollers 205 are braked. When the brake members 206 are in the non-braking position 2062, the second rollers 205 are released and can be moved. By arranging the second rollers 205 and the corresponding brake members 206, the pallet frame 200 can be moved using the second rollers 205 by using the brake members 206. When movement is not required, the brake members 206 can be switched to the braking position 2061 to brake the pallet frame 200, thereby securing the pallet frame 200 and then refueling the pallet frame 200 using the oil pump 300. External traction tools can be used for traction, so that when the transport vehicle 100 is not provided, the transport vehicle can be flexibly moved to expand the application scenarios.

[0089] In some embodiments, multiple rollers 205 and multiple brakes 206 extend downward from the bottom surface of the pallet frame 200 and are located at the four corners of the pallet frame 200. Because the pallet frame 200 carries the aviation fuel drum 20 and the fuel pumping device 300, which are relatively heavy, distributing the multiple rollers 205 and multiple brakes 206 at the four corners of the pallet frame 200 facilitates operator operation of the brakes 206 and also provides greater stability for the entire aviation fuel refueling device during movement.

[0090] It should be noted that, during the switching process of the brake member 206 from the non-brake position 2062 to the brake position 2061 , it can be operated by a staff member or controlled by other automatic components, which is not limited in this application.

[0091] exist Figures 1 to 5In the illustrated embodiment, the flow meter 303, hose reel 304, and refueling gun 305 are all arranged along the first direction X with respect to the fuel drum support 201. The refueling gun 305 is positioned closer to the fuel drum support 201 relative to the flow meter 303 and hose reel 304. The filter separator 302 and refueling gun 305 are arranged side by side along the second direction Y. In actual use, the aviation fuel refueling device 10 is parked near the refueling port of general aviation equipment, and its aviation fuel drum 20 is also near the side of the general aviation equipment. The flow meter 303 and the fuel drum support 201 are located on the same side in the first direction X, making it easier for personnel to observe the specific refueling flow rate. The hose reel 304 and refueling gun 305 are located on the same side in the first direction X, making it easier for personnel to refuel the general aviation equipment. Furthermore, the required refueling coil 308 is shorter, making it easier and more convenient to reel out or retract the refueling coil 308.

[0092] In some embodiments, the aviation fueling system 10 further includes a fixed bracket 318 protruding from the upper surface of the tray frame 200 and positioned at a predetermined height. The fixed bracket 318 is used to secure the flow meter 303, hose reel 304, and fueling gun 305, with the hose reel 304 and fueling gun 305 positioned at the top of the fixed bracket 318. Because the aviation fueling system 10 requires operator operation during refueling, placing the hose reel 304 and fueling gun 305 at the top of the fixed bracket 318 provides a predetermined height for the flow meter 303, hose reel 304, and fueling gun 305, effectively utilizing the space above the fixed bracket 318 and making operation more convenient and labor-saving for operators. The flow meter 303 is positioned on the side of the fixed bracket 318 facing away from the filter separator 302. The display of the flow meter 303 faces the operator, making it easier for the operator to observe the flow rate of the refueled fuel. The above height is based on the upper surface of the tray frame 200 as a reference surface and can be set according to the height or hand-held height of the staff, and is not limited in this application.

[0093] In some embodiments, the fixed bracket 318 and the fuel drum support 201 are arranged along the first direction X and are positioned side by side with the filter separator 302 along the second direction Y. In this embodiment, the maximum diameter of the aviation fuel drum 20 ranges from 550 mm to 600 mm, with a preferred diameter of 580 mm. The aviation fuel drum 20 occupies most of the space in the second direction Y of the pallet frame 200, while the fixed bracket 318 and the flow meter 303, hose reel 304, and fueling nozzle 305 mounted thereon also occupy a certain amount of space. If the structural layout is not compact, the aviation fueling apparatus 10 will be larger, resulting in a larger occupied area and limited usability. Therefore, to ensure a smaller and more compact pallet frame 200 and aviation fueling apparatus 10, the fixed bracket 318 and the fuel drum support 201 are arranged along the first direction X and are positioned side by side with the filter separator 302 along the second direction Y.

[0094] In some embodiments, the bottom of the fixed bracket 318 has a storage space 319. The aviation refueling device 10 includes multiple storage boxes 320, which are located within the storage space 319. The provision of the storage space 319 effectively utilizes the space below the fixed bracket 318. Furthermore, the multiple storage boxes 320 are arranged within the storage space 319 to effectively accommodate various small handheld maintenance tools, thereby enriching the storage function of the aviation refueling device 10.

[0095] In some embodiments, the fixing bracket 318 is provided with a fuel gun limiting groove 321 (such as Figure 1 As shown, a fueling gun retaining groove 321 is provided on the side of the fixing bracket 318 facing away from the filter separator 302. The oil outlet of the fueling gun 305 is engaged with the retaining groove 321. The oil outlet of the fueling gun 305 is the fuel inlet of the fueling gun 305. Engaging the fuel inlet of the fueling gun 305 with the retaining groove 321 facilitates the fixing of the fueling gun 305 to the fixing bracket 318, making it easier for the operator to access the fueling gun 305. It also prevents the fuel inlet of the fueling gun 305 from being exposed to the outside world and contaminating the fuel inlet of the fueling gun 305.

[0096] exist Figure 1 and Figure 4In the illustrated embodiment, the aviation fuel refueling device 10 further includes a static discharge wire reel 322, which is mounted on a fixed bracket 318. During refueling, the static discharge wire reel 322 is removed from the fixed bracket 318. The static discharge wire reel 322 is provided with a static discharge wire for quickly dissipating static electricity from the aviation fuel refueling device. During refueling operations, the static discharge wire must be reliably grounded. A static discharge device is provided on the operating surface of the general aviation equipment. In some embodiments, the static discharge wire reel 322 is located on one side of the hose reel 304 in the first direction X. This effectively utilizes the space above the fixed bracket 318 and makes it easier for staff to access the reel.

[0097] In some embodiments, the oil pumping device 300 further includes a connecting pipe 323 connected to the oil sight glass 306. The oil inlet end of the connecting pipe 323 communicates with the oil outlet end 316 of the oil pump assembly 301. The connecting pipe 323 includes a first oil outlet end 3231 and a second oil outlet end 3232. The oil inlet end of the oil sight glass 306 communicates with the first oil outlet end 3231, and the oil inlet end of the filter separator 302 communicates with the second oil outlet end 3232. Since the oil pump assembly 301 is detachably assembled to the aviation fuel tank 20, the pipeline connecting it to the oil outlet end 316 of the oil pump 310 is also detachably assembled. By providing the connecting pipe 323, at least the connecting pipe 323 connecting the oil pump 310 to the oil sight glass 306 and the filter separator 302 does not need to be disassembled, and only the pipeline connecting the connecting pipe 323 to the oil outlet end 316 of the oil pump 310 can be disassembled. This can reduce assembly time and improve assembly efficiency.

[0098] In some embodiments, a gap exists between the fixed bracket 318 and the oil drum support 201, and the oil sight glass 306 and the connecting pipe 323 are disposed in the gap between the fixed bracket 318 and the oil drum support 201. This effectively utilizes the space between the fixed bracket 318 and the oil drum support 201. The oil sight glass 306 and the connecting pipe 323 are arranged side by side in the second direction Y and are disposed on one side of the oil drum support 201. The filter separator 302 and the connecting pipe 323 are arranged side by side in the second direction Y. This shortens the pipelines connecting the connecting pipe 323 to the oil sight glass 306, the oil pump 310, and the filter separator 302, making the pipeline layout more compact. This makes the aviation fuel refueling device 10 compact, small in size, occupies less space, and is applicable to more scenarios.

[0099] In some embodiments, the aviation fuel refueling device 10 includes a fixing rod 324 disposed on one side of the oil drum support portion 201. The fixing rod 324 protrudes from the upper surface of the pallet frame 200, and the connecting pipe 323 is fixed to the fixing rod 324. The fixing rod 324 is used to fix the connecting pipe 323 to ensure that the connecting pipe 323 has a certain height.

[0100] In some embodiments, the oil inlet of the connecting pipe 323 is positioned higher than the first oil outlet 3231 of the connecting pipe 323, and is also higher than the oil sight glass 306 and the aviation fuel drum 20. This creates a height difference between the oil inlet of the connecting pipe 323, the first oil outlet 3231 of the connecting pipe 323, the oil sight glass 306, and the aviation fuel drum 20. This ensures that the oil in the connecting pipe 323 is the oil pumped from the aviation fuel drum 20 by the oil pump 310 and can flow smoothly into the oil sight glass 306 for easy observation, rather than the oil stored in the pipeline connected to the oil outlet 316 of the oil pump 310, thereby ensuring the normal operation of the oil pumping device 300.

[0101] In some embodiments, the first oil outlet end 3231 is higher than the second oil outlet end 3232. Since oil entering the oil inlet end of the connecting pipe 323 first enters the oil sight glass 306 through the first oil outlet end 3231, the presence of oil in the oil sight glass 306 indicates that the pipeline connected to the oil pump 310 is operating normally. This arrangement facilitates observation and ensures the normal operation of the oil pumping device 300.

[0102] In some embodiments, the aviation fuel refueling system 10 further includes a fire extinguisher 325, which is assembled to the pallet frame 200. The presence of the fire extinguisher 325 enhances safety. In some embodiments, the fire extinguisher 325 is arranged side by side with the oil drum support 201 along the second direction Y and is located on one side of the storage bracket 500. This effectively utilizes the space within the pallet frame 200, resulting in a compact structure for the components mounted thereon, and thus a smaller size for the pallet frame 200. Furthermore, a distance is maintained between the lowest point of the fire extinguisher 325 and the upper surface of the pallet frame 200. The height of the fire extinguisher 325 makes it easily accessible to personnel without requiring significant effort.

[0103] In some embodiments, the oil pump assembly 301 further includes a motor handle 326, which is located on one side of the motor 311. This helps staff members pick up the motor 311, and the motor handle 326 being located on one side of the motor 311 is more ergonomic and easier for staff members to use. In some embodiments, the oil pump assembly 301 further includes a handheld portion 327, which is located on the pump rod 312 and above the oil outlet end 316. When the oil pump assembly 301 needs to be removed from the oil outlet of the aviation fuel tank 20, the handheld portion 327 can be provided to facilitate removal by staff members. In some embodiments, the oil pump assembly 301 further includes a dust cover (not shown), which is located on one side of the motor 311. When the pump rod 312 is stored in the storage tube 502, the motor 311 is located outside the storage tube 502. In this case, the dust cover can be used to cover the motor 311 to prevent the motor 311 from being affected by the external environment.

[0104] In some embodiments, the aviation fuel refueling device 10 includes a quick-release assembly 400. The oil pump assembly 301 is detachably assembled to the aviation fuel tank 20 through the quick-release assembly 400. Figures 1 to 5 、 Figures 9 to 18 As shown, the quick-release assembly 400 includes a fixing seat 401 and a sealing cover 402 detachably assembled to the fixing seat 401. The fixing seat 401 is a ring structure, and the fixing seat 401 is clamped on the oil outlet of the aviation fuel barrel 20. The top surface of the fixing seat 401 is higher than the top surface of the oil outlet. To ensure that when the oil pump assembly 301 is assembled in the aviation fuel barrel 20, the pump rod 312 is inserted from the fixing seat 401, connected to the fixing seat 401, and extends into the aviation fuel barrel 20, and the bottom of the support seat 314 is in contact with the top of the fixing seat 401; when the oil pump assembly 301 is not assembled in the aviation fuel barrel 20, the sealing cover 402 is assembled on the top of the fixing seat 401 to seal the oil outlet of the aviation fuel barrel 20 (such as Figure 9 By providing a fixing base 401 and a sealing cover 402 of the quick-release assembly 400, the fixing base 401 can quickly assemble the oil pump 310 to the oil outlet of the aviation fuel drum 20. When the oil pump 310 is not assembled to the aviation fuel drum 20, the sealing cover 402 can quickly seal the oil outlet of the aviation fuel drum 20. The quick-release structure is simple and the assembly method is simple. When used in conjunction with the oil pump 310 and the aviation fuel drum 20, it can be easily disassembled and assembled, thereby improving assembly efficiency.

[0105] In some embodiments, the fixing base 401 includes a first fixing portion 403 and a second fixing portion 404 connected to the first fixing portion 403, wherein the second fixing portion 404 extends downwardly along the bottom of the first fixing portion 403. The first fixing portion 403 includes a first channel 405 extending vertically therethrough, and the second fixing portion 404 includes a second channel 406 extending vertically therethrough. The second channel 406 communicates with the first channel 405 and forms a downward step 407 with the first channel 405. In some embodiments, a groove 408 is provided between the first fixing portion 403 and the second fixing portion 404, wherein the inner wall of the first channel 405 extends inwardly and forms a step 407 with the groove 408. The groove 408 is recessed inwardly from the inner peripheral wall of the fixing base 401 and communicates with the first channel 405 and the second channel 406. When the fixing seat 401 is assembled to the aviation fuel barrel 20, the oil outlet of the aviation fuel barrel 20 is engaged in the second channel 406, and the edge of the oil outlet of the aviation fuel barrel 20 is limited by the groove 408, and the top of the oil outlet of the aviation fuel barrel 20 abuts against the step 407. This assembly method is simple, and the fixing seat 401 is not easy to detach from the oil outlet of the aviation fuel barrel 20. When the oil pump assembly 301 is assembled to the aviation fuel barrel 20, the pump rod 312 is engaged in the first channel 405, and the outer wall of the pump rod 312 is in contact with the inner wall of the first channel 405. In some embodiments, the first fixing portion 403 and the second fixing portion 404 are integrally formed, and the structure is simple.

[0106] In some embodiments, a first chamfer 409 is provided on a side of the groove 408 that is closer to the second channel 406 than the first channel 405. The first chamfer 409 is inclined downward from the outer wall toward the inner wall of the fixing base 401. The first chamfer 409 serves as a guide, facilitating the installation of the fixing base 401 within the oil outlet of the aviation fuel drum 20. Furthermore, when the fixing base 401 is installed within the oil outlet of the aviation fuel drum 20, it is difficult for the fixing base 401 to disengage from the groove 408.

[0107] In some embodiments, the maximum aperture of the second channel 406 is larger than the maximum aperture of the first channel 405. Since the oil outlet of the aviation fuel drum 20 is engaged within the second channel 406 and the oil outlet itself has thickness, the maximum aperture of the second channel 406 is larger than the maximum aperture of the first channel 405 to ensure that the inner wall of the oil outlet is flush with the inner wall of the first channel 405, ensuring that the pump rod 312 can pass through the first and second channels 405, 406, without getting stuck, and can be smoothly inserted into the aviation fuel drum 20.

[0108] In some embodiments, the outer peripheral wall of the fixing base 401 is provided with a plurality of flanges 410, which extend obliquely along the circumference of the fixing base 401. The upper edge of the flange 410 is located at the first fixing portion 403, and the lower edge of the flange 410 is located at the second fixing portion 404. The sealing cover 402 includes a cover body 411 and a plurality of ear clips 412. The ear clips 412 extend downward from the edge of the cover body 411, and the ends of the ear clips 412 away from the cover body 411 are bent inward. When the oil pump assembly 301 is not assembled in the aviation fuel tank 20, the sealing cover 402 is secured to the fixing base 401 by the restraining engagement of the plurality of flanges 410 and the plurality of ear clips 412. In this embodiment, two flanges 410 are provided, and the two flanges 410 have the same inclination direction. When sealing cover 402 is attached to mounting base 401, its tabs 412 fit over the gap between two adjacent flanges 410 and rotate along the extension direction of flange 410 from the upper end to the lower end (the upper and lower ends can be referenced to the plane of the radial direction of mounting base 401) to engage with flange 410 until the bottom end of flange 410 abuts against the end of tab 412 opposite flange 410, indicating that sealing cover 402 is attached to mounting base 401. To remove sealing cover 402, it can be removed from mounting base 401 by rotating it in the opposite direction. In some embodiments, the horizontal spacing between adjacent flanges 410 is at least greater than the maximum horizontal dimension of tab 412. This arrangement facilitates easier engagement of tab 412 with the gap between adjacent flanges 410, improving assembly efficiency.

[0109] The fixing base 401 is provided with a plurality of flanges 410, which are used to cooperate with the ear buckles 412 of the sealing cover 402 on one hand, and to cooperate with the support base 314 provided on the pump rod 312 on the other hand, so as to facilitate the assembly of the pump rod 312 and ensure the fixing effect of the pump rod 312. In some embodiments, the edge of the support base 314 is provided with a locking member 329 (such as Figure 2 As shown), the locking member 329 can move along the axial direction of the support seat 314. When the support seat 314 is assembled to the fixing seat 401, the locking member 329 is operated from bottom to top along the axial direction of the support seat 314, and the support seat 314 is locked to the flange 410 (as shown). Figure 3 When disassembling the oil pump assembly 301, the locking member 329 is operated in an axial direction from top to bottom along the support base 314, thereby unlocking the support base 314 from the flange 410. This arrangement ensures that the oil pump 310 can be stably assembled to the oil outlet of the aviation fuel tank 20.

[0110] exist Figure 15 In the illustrated embodiment, the radial inclination angle α1 of the flange 410 relative to the fixing base 401 ranges from 2° to 6°. In some embodiments, the radial inclination angle α1 of the flange 410 relative to the fixing base 401 can be 2°, 3°, 4°, 5°, or 6°, with a preferred value of 4°. Setting the flange 410 at a suitable inclination angle ensures better contact between the ear clip 412 and the flange 410, enhancing the sealing performance of the assembly.

[0111] exist Figures 13 to 15 In the embodiment shown, the outer peripheral wall of the fixing seat 401 is further provided with a plurality of limiting ribs 413, which extend along the axial direction of the fixing seat 401 and are located above the flange 410. Figure 18 In the illustrated embodiment, the inner wall of the cover body 411 is provided with a receiving groove 414. When the sealing cover 402 is assembled to the fixing base 401, the limiting ribs 413 engage with the receiving groove 414 to limit the position. The fixing base 401 is provided with multiple limiting ribs 413, on the one hand, to cooperate with the inner wall of the sealing cover 402 to limit the position, and on the other hand, to abut against the receiving groove 414, facilitating the assembly of the sealing cover 402 and ensuring the fixing effect of the sealing cover 402. In some embodiments, the multiple limiting ribs 413 are arranged at intervals along the circumference of the fixing base 401. In this embodiment, four limiting ribs 413 are provided and are symmetrically arranged around the circumference of the first fixing portion 403.

[0112] exist Figure 18In the illustrated embodiment, a buffer groove 415 is provided within the cover body 411. The buffer groove 415 is located at the top of the cover body 411 and communicates with the receiving groove 414. Because the flange 410 is arranged obliquely along the circumference of the fixing seat 401, when the sealing cover 402 is covered on the fixing seat 401, the sealing cover 402 has a certain distance to move in the vertical direction. By providing the buffer groove 415 at the top of the sealing cover 402, the buffer groove 415 provides a buffer space to prevent the top of the first fixing portion 403 from contacting the top wall of the cover body 411. When the sealing cover 402 is assembled to the fixing seat 401, the top of the fixing seat 401 is located within the buffer groove 415. A stopper 416 is provided on the inner wall of the cover body 411, located between the buffer groove 415 and the receiving groove 414. The stopper 416 is used to separate the buffer groove 415 from the receiving groove 414. The outer peripheral wall of the fixing base 401 is provided with a second chamfer 417. The second chamfer 417 is inclined from top to bottom, in the direction from the inner sidewall to the outer sidewall of the fixing base 401. When the sealing cover 402 is assembled to the fixing base 401, the second chamfer 417 abuts against the inner wall of the stop block 416. The fixing base 401 is provided with the second chamfer 417 to prevent collision with the stop block 416.

[0113] In some embodiments, when the oil pump assembly 301 is not assembled to the aviation fuel tank 20, the oil pump assembly 301 is assembled to the storage bracket 500. Figures 19 to 23 As shown, since the aviation fuel drum 20 placed on the drum support 201 occupies a relatively large space and the storage bracket 500 is of a certain length, in order to make the entire aviation fuel refueling device 10 compact and small in size, the storage bracket 500 and the drum support 201 are arranged along the second direction Y, with the storage bracket 500 being located on one side of the aviation fuel drum 20. This effectively utilizes the space of the pallet frame 200 in the first direction X.

[0114] If the oil pump assembly 301 is assembled to the aviation fuel drum 20 and not removed when refueling is not required, the height of the entire aviation fuel refueling device 10 is increased, causing the center of gravity of the entire aviation fuel refueling device 10 to rise, making it unsafe during transportation. Furthermore, since the motor 311 has a certain volume and weight, and the load-bearing weight and volume of the entire oil pump assembly 301 are relatively large, it is unsafe during transportation and can easily become misaligned with the oil outlet of the aviation fuel drum 20, resulting in poor fixing effect. In the present application, when the oil pump assembly 301 is not assembled to the aviation fuel drum 20, the oil pump assembly 301 is assembled to the storage bracket 500, lowering the center of gravity of the aviation fuel refueling device 10 and improving transportation stability.

[0115] exist Figures 19 to 23In the illustrated embodiment, the storage bracket 500 includes a plurality of support rods 501 and a storage tube 502. The support rods 501 extend upward from the upper surface of the pallet frame 200. The support rods 501 are spaced apart from the upper surface of the pallet frame 200. In some embodiments, the storage tube 502 is assembled to the upper ends of the plurality of support rods 501 at an angle relative to the upper surface of the pallet frame 200 and extends from the second side X2 to the first side X1. The storage tube 502 extends from the second side X2 to the first side X1, effectively utilizing the space of the pallet frame 200 in the first direction X. When the oil pump assembly 301 is not assembled to the aviation fuel drum 20, the pump rod 312 is housed within the storage tube 502, and the motor 311 is located outside the storage tube 502. With this arrangement, the storage tube 502 is tilted relative to the upper surface of the pallet frame 200 and spaced apart from it. When the oil pump assembly 301 is assembled on the storage bracket 500, the oil pump assembly 301 is positioned at a distance from the upper surface of the pallet frame 200, making it easier for staff to access the oil. The pump rod 312 is housed within the storage tube 502. Due to long-term accumulation of impurities, some of the oil in the pump rod 312 is collected within the storage tube 502. The tilted arrangement of the storage tube 502 relative to the upper surface of the pallet frame 200 facilitates cleaning or clearing the oil within the storage tube 502. In some embodiments, multiple support rods 501 are spaced apart along the first direction X and the second direction Y, with the multiple support rods 501 spaced apart from the second side X2 toward the first side X1. In the present application, two support rods 501 are provided, and they are positioned in the middle region of the storage tube 502. This arrangement balances the forces acting on the storage tube 502 and improves stability.

[0116] In some embodiments, the storage bracket 500 and the fuel drum support 201 are arranged along the second direction Y, and the storage tube 502 is arranged at an angle relative to the upper surface of the tray frame 200 and the second direction Y. With this arrangement, when the fuel pump assembly 301 is not assembled with the aviation fuel drum 20, the motor 311 is arranged along the second direction Y with the aviation fuel drum 20 placed on the fuel drum support 201, and is located on one side of the aviation fuel drum 20, making it more convenient to remove the fuel pump assembly 301. Because the motor 311 is large and heavy, its location on the same side as the aviation fuel drum 20 reduces the distance required for removal and saves effort.

[0117] In some embodiments, the storage tube 502 includes a first storage end 503 and a second storage end 504, with the first storage end 503 and the fuel drum support portion 201 arranged along the second direction Y. The first storage end 503 is closer to the second side X2 relative to the first side X1, and the second storage end 504 is closer to the first side X1 relative to the second side X2. When the fuel pump assembly 301 is not assembled in the aviation fuel drum 20, the pump rod 312 extends from the first storage end 503 to the second storage end 504, and the motor 311 is located outside the first storage end 503. This arrangement places the motor 311 on the same side of the aviation fuel drum 20 as the fuel drum support portion 201, making it easier to remove.

[0118] exist Figure 19 In the illustrated embodiment, the storage tube 502 extends obliquely from the second side X2 toward the first side X1, and in the second direction Y, toward the fuel drum support portion 201. Because the pump rod 312 is inserted into the aviation fuel drum 20, and the oil inlet end 315 of the pump rod 312 contacts the fuel in the aviation fuel drum 20, the pump rod 312 has a certain length. When not required for assembly with the aviation fuel drum 20, it is housed in the storage tube 502, resulting in a certain length for the storage tube 502. The storage tube 502 extends obliquely from the second side X2 toward the first side X1, and in the second direction Y, toward the fuel drum support portion 201. This effectively utilizes the space diagonally opposite to the pallet frame 200, reducing the size of the pallet frame 200 and, consequently, shortening the length of the aviation fueling apparatus 10. This allows the center of gravity of the aviation fueling apparatus 10 to be closer to the front of the vehicle 101 during transportation. In some embodiments, the storage tube 502 is arranged obliquely relative to the vertical direction and the first direction X.

[0119] If the storage tube 502 is not tilted, the pallet frame 200 will be longer, and the distance from the front 101 of the truck 100 to the forks 102 will be longer, resulting in a longer length and larger volume of the entire aviation fuel refueling device 10. The aviation fuel barrel 20 is heavy and located away from the front 101. When the pallet frame 200 is longer, the weight of the rear of the truck 100 is greater, causing the center of gravity of the entire aviation fuel refueling device 10 to shift to the rear, making it unstable during transportation. Therefore, the tilted storage tube 502 of the present application effectively utilizes the space diagonally opposite the pallet frame 200, reducing the volume of the pallet frame 200 and shortening the length of the aviation fuel refueling device 10. This allows the center of gravity of the aviation fuel refueling device 10 to be closer to the front 101 during transportation.

[0120] exist Figure 20In the illustrated embodiment, the first receiving end 503 is higher than the second receiving end 504. The pump rod 312 is housed in the receiving tube 502. Due to the accumulation of impurities over time, some of the oil in the pump rod 312 is collected in the receiving tube 502. The receiving tube 502 is tilted relative to the upper surface of the tray frame 200, with the first receiving end 503 higher than the second receiving end 504, which facilitates cleaning or clearing the oil in the receiving tube 502.

[0121] exist Figure 21 In the illustrated embodiment, the inclination angle α2 of the storage tube 502 relative to the upper surface of the tray frame 200 ranges from 5° to 15°. In some embodiments, the inclination angle of the storage tube 502 relative to the upper surface of the tray frame 200 is 5°, 7°, 9°, 10°, 13°, or 15°. Setting an appropriate inclination angle of the storage tube 502 relative to the upper surface of the tray frame 200 can make it easier to insert the pump rod 312 into the storage tube 502, making operation more convenient for personnel.

[0122] exist Figure 19 In the illustrated embodiment, the inclination angle α3 of the storage tube 502 relative to the second direction Y ranges from 65° to 85°. In some embodiments, the inclination angle α3 of the storage tube 502 relative to the second direction Y can be 65°, 70°, 75°, 80°, or 85°, with a preferred value of 77°. By setting an appropriate inclination angle of the storage tube 502 relative to the second direction Y, the tray frame 200 can be made smaller while still being able to accommodate the pump rod 312, thereby reducing the volume and footprint of the entire aviation fueling device 10.

[0123] exist Figure 22In the illustrated embodiment, the storage bracket 500 includes a plug 505, which is detachably assembled to the second storage end 504 to seal the second storage end 504. In some embodiments, the plug 505 may be a recessed structure. When the oil in the storage tube 502 needs to be cleaned, the transport vehicle 100 and the pallet structure 200 are separated, and the plug 505 is removed from the second storage end 504, thereby facilitating operation by personnel. In some embodiments, when the oil pump assembly 301 is not assembled in the aviation fuel drum 20, the oil inlet end 315 of the oil pump 310 is located within the storage tube 502, closer to the second storage end 504 relative to the first storage end 503, and spaced apart from the plug 505. Setting a suitable distance between the oil inlet 315 of the oil pump 310 and the plug 505 allows for space between the two, allowing for a certain amount of oil to be stored. This ensures that the oil collected at the second receiving end 504 does not come into contact with the oil inlet 315 of the oil pump 310. This ensures that when the oil pump 310 is used again, less oil is drawn from the oil inlet 315 of the oil pump 310 through the receiving tube 502, thus avoiding waste. In some embodiments, the plug 505 is made of Teflon, which is anti-static and highly corrosion-resistant.

[0124] exist Figure 21 and Figure 22 In the illustrated embodiment, the storage bracket 500 includes an annular support member 506 disposed at the first storage end 503. The annular support member 506 provides support. The inner sidewall of the annular support member 506 supports the outer sidewall of the pump rod 312, and the end surface of the annular support member 506 supports the support seat 314.

[0125] In some embodiments, the annular support 506 is at least attached to the inner wall and end face of the first receiving end 503, and when the pump rod 312 is received in the receiving tube 502, the outer wall of the pump rod 312 fits against the inner wall of the annular support 506. This arrangement allows a gap to exist between the outer wall of the pump rod 312 and the inner wall of the receiving tube 502. By providing the annular support 506, its inner wall can support the pump rod 312, thereby preventing the outer wall of the pump rod 312 from contacting and rubbing with the inner wall of the receiving tube 502 when the pump rod 312 is inserted into or withdrawn from the receiving tube 502, thereby preventing static electricity or sparks from being generated, thereby improving safety. In some embodiments, the cross-section of the annular support 506 is U-shaped, and is clamped to the first receiving end 503 (such as Figure 23(as shown). This arrangement prevents the annular support member 506 from disengaging from the first receiving end 503 when the pump rod 312 is withdrawn from the receiving tube 502. In some embodiments, when the pump rod 312 is received within the receiving tube 502, the bottom of the support seat 314 abuts against the top of the annular support member 506. The bottom end surface of the support seat 314 abuts against the top surface of the annular support member 506 and engages with the inner sidewall of the annular support member 506, further securing the pump rod 312 within the receiving tube 502.

[0126] In some embodiments, the inner diameter of the annular support member 506 ranges from 50 mm to 80 mm. In some embodiments, the inner diameter of the annular support member 506 can be 50 mm, 55 mm, 60 mm, 65 mm, 70 mm, 75 mm, or 80 mm, with 65 mm being the preferred value. Setting the inner diameter of the annular support member 506 appropriately prevents static electricity or sparks from contact friction when the pump rod 312 is inserted into or removed from the storage tube 502, thereby improving safety. In some embodiments, the annular support member 506 is made of Teflon. Teflon is anti-static and highly corrosion-resistant.

[0127] In some embodiments, the storage tube 502 includes a limiting protrusion 507 (e.g., Figure 22 As shown, a limiting protrusion 507 is provided on the inner circumferential wall of the receiving tube 502. The limiting protrusion 507 is arranged closer to the second receiving end 504 than the first receiving end 503. When the pump rod 312 is received in the receiving tube 502, the limiting protrusion 507 abuts against the pump rod 312. When the aviation fuel refueling device 10 is moved, the pump rod 312 disposed in the receiving tube 502 is prone to contact and friction with the receiving tube 502. Therefore, the present application provides a limiting protrusion 507 on the inner side wall of the receiving tube 502 to prevent the pump rod 312 disposed in the receiving tube 502 from shaking, thereby preventing contact and friction with the inner side wall of the receiving tube 502, which may generate static electricity or sparks.

[0128] Combine Figures 1 to 6 、 Figures 24 to 27In the illustrated embodiment, the anti-dump block 600 includes a block body 601 and a protective layer 602 covering the surface of the block body 601. The anti-dump block 600 protrudes upward from the upper surface of the pallet frame 200 and is located at the edge of the oil drum support portion 201. The oil drum support portion 201 is used to support the aviation fuel drum 20. Due to the large size and weight of the aviation fuel drum 20, the aviation fuel drum 20 may lose its center of gravity and tip over during the movement of the aviation fuel refueling device 10. Therefore, the block body 601 of the anti-dump block 600 is provided at the edge of the oil drum support portion 201 to prevent the aviation fuel drum 20 located on the oil drum support portion 201 from tipping over. The protective layer 602 provided on the surface of the block body 601 protects the block body 601 and prevents friction between the aviation fuel drum 20 and the block body 601. Furthermore, when loading and unloading the aviation fuel barrel 20 , the anti-dumping block 600 can play a role in positioning, fixing and buffering protection.

[0129] exist Figures 24 to 27 In the illustrated embodiment, the anti-dump block 600 includes a plurality of columnar anti-dump posts 603 spaced apart along the edge of the drum support 201. In this embodiment, four anti-dump posts 603 are provided, spaced apart along the edge of the drum support 201, to prevent the aviation fuel drum 20 from tipping over in all directions. The anti-dump block 600, configured as a columnar anti-dump post 603, is simple in structure and easy to assemble.

[0130] In some embodiments, when the aviation fuel drum 20 is placed on the drum support 201, the maximum horizontal distance between the anti-dump block 600 and the outer wall of the aviation fuel drum 20 ranges from 10 mm to 20 mm, with a preferred value of 15 mm. Setting an appropriate horizontal distance between the anti-dump block 600 and the aviation fuel drum 20 ensures that the aviation fuel drum 20 is not easily contacted or rubbed against the anti-dump block 600 when placed on the drum support 201, thereby ensuring safety.

[0131] In some embodiments, the height L1 of the block body 601 ranges from 150 mm to 200 mm (e.g. Figure 25As shown). In some embodiments, the height L1 of the block body 601 can be 150mm, 160mm, 170mm, 180mm, 190mm, or 200mm, with a preferred value of 180mm. Due to the large volume and weight of the aviation fuel drum 20, the height of the block body 601 should not be too high or too low. If the height of the block body 601 is too high, it will be too difficult to lift the aviation fuel drum 20 when placing it on the drum support 201. If the height of the block body 601 is too low, the aviation fuel drum 20 placed on the drum support 201 will not be able to prevent it from tipping over. Therefore, setting the height of the block body 601 appropriately can not only prevent it from tipping over, but also ensure that the height of the aviation fuel drum 20 is moderate and effortless. In some embodiments, the ratio of the height of the block body 601 to the height of the aviation fuel drum 20 is in the range of 1 / 5 to 1 / 4.5, with a preferred value of 1 / 4.8. In this way, the height of the block body 601 is appropriately proportional to the height of the aviation fuel barrel 20 , which can achieve the anti-dumping effect on the one hand, and ensure that the aviation fuel barrel 20 is lifted to a moderate height without effort on the other hand.

[0132] In some embodiments, the block body 601 is made of stainless steel, and the tray frame 200 comprises a stainless steel plate, to which the block body 601 is connected. Stainless steel is highly corrosion-resistant, static-conductive, explosion-proof, and highly safe. In some embodiments, the protective layer 602 is made of Teflon. Teflon prevents mechanical friction between the fuel drum 20 and the block body 601, which could easily cause sparks, providing enhanced safety. Teflon is also anti-static and corrosion-resistant.

[0133] exist Figures 24 to 27In the illustrated embodiment, the anti-dump post 603 includes a first end 604 and a second end 605, the second end 605 including a bottom surface. The second end 605 is located proximal to the pallet frame 200 and extends downward from the upper surface of the pallet frame 200 to the bottom surface. Threads 606 are provided circumferentially around the second end 605, and the pallet frame 200 is provided with a threaded hole (not shown) extending vertically and corresponding to the threads 606. The anti-dump post 603 is secured to the pallet frame 200 through the engagement of the threads 606 and the threaded hole. Due to the large size and weight of the aviation fuel drum 20, a high degree of securement is required for the anti-dump block 600. The anti-dump post 603 is secured to the pallet frame 200 through the engagement of the threads 606 and the threaded hole. This simple securing method prevents the anti-dump post 603 from loosening during movement of the aviation fuel refueling apparatus 10, resulting in a highly secure securement. In some embodiments, the length of the second end 605 is greater than or equal to 1 / 6 of the length of the anti-tipping post 603. The length of the second end 605 is appropriately set to ensure that the second end 605 can pass from the upper surface of the pallet frame 200 to the lower surface of the pallet frame 200, providing a sufficient fixed length for a more secure fixation and preventing loosening. In some embodiments, the length L2 of the second end 605 ranges from 25 mm to 35 mm. In some embodiments, the length L2 of the second end 605 can be 25 mm, 27 mm, 29 mm, 31 mm, 33 mm, or 35 mm, with a preferred value of 30 mm.

[0134] In some embodiments, a sidewall of the protective layer 602 is provided with a clearance hole 607, which is located closer to the second end 605 than the first end 604. The stopper body 601 located in the clearance hole 607 is exposed outside the clearance hole 607. The provision of the clearance hole 607 in the protective layer 602 and the exposure of the stopper body 601 located in the clearance hole 607 are intended to facilitate personnel to use external fixing tools to secure the anti-tipping column 603 to the pallet frame 200 using the clearance hole 607 as a fixed support surface.

[0135] In some embodiments, the vertical distance between the upper and lower edges of the clearance hole 607 is greater than or equal to 1 / 9 of the length of the anti-dumping column 603. The vertical distance between the upper and lower edges of the clearance hole 607 is set appropriately to provide a sufficient fixed support surface and sufficient contact with the external fixing tool to ensure that the fixing tool is not easy to slide off the anti-dumping column 603 when fixing the anti-dumping column 603. In some embodiments, the vertical distance L3 between the upper and lower edges of the clearance hole 607 is in the range of 15mm to 25mm (e.g., Figure 25 or Figure 26 As shown), the preferred value is 20mm.

[0136] In some embodiments, the maximum diameter range of the anti-dump column 603 is 28mm to 36mm. In some embodiments, the maximum diameter of the anti-dump column 603 can be 28mm or 30mm or 32mm or 34mm or 36mm, and the preferred value is 32mm. The maximum diameter of the anti-dump column 603 is set appropriately to ensure that the aviation fuel barrel 20 has sufficient hardness when it is dumped and can block the aviation fuel barrel 20. In some embodiments, the ratio of the maximum diameter of the anti-dump column 603 to the maximum outer diameter of the aviation fuel barrel 20 is in the range of 1 / 20 to 1 / 15, and the preferred value is 1 / 18. The ratio of the maximum diameter of the anti-dump column 603 to the maximum outer diameter of the aviation fuel barrel 20 is set appropriately to ensure that the anti-dump column 603 will not cause damage to the aviation fuel barrel 20 when the aviation fuel barrel 20 dumps.

[0137] In some embodiments, the thickness L4 of the protective layer 602 located on the peripheral wall of the block body 601 in the anti-dumping column 603 is in the range of 3 mm to 7 mm (e.g. Figure 25 As shown). In some embodiments, the thickness L4 of the protective layer 602 located on the peripheral wall of the block body 601 can be 3mm or 4mm or 5mm or 6mm or 7mm, and the preferred value is 5mm. Setting the thickness of the protective layer 602 located on the peripheral wall of the block body 601 appropriately can prevent the wall of the aviation fuel barrel 20 from contacting and rubbing with the protective layer 602 on the peripheral wall of the block body 601. In some embodiments, the thickness L5 of the protective layer 602 located on the top wall of the block body 601 in the anti-dumping column 603 ranges from 5mm to 15mm (as shown). Figure 25 As shown). In some embodiments, the thickness L5 of the protective layer 602 located on the top wall of the block body 601 can be 5 mm, 7 mm, 9 mm, 11 mm, 13 mm, or 15 mm, with a preferred value of 10 mm. Due to the large volume and weight of the aviation fuel drum 20, when the aviation fuel drum 20 needs to be placed on the drum support 201 or removed from the drum support 201, the bottom of the aviation fuel drum 20 is likely to contact the top of the anti-tipping column 603 or the number of times the contact is relatively high. Therefore, compared with the protective layer 602 located on the peripheral wall of the block body 601, the thickness of the protective layer 602 located on the top wall of the block body 601 is thicker. By setting the thickness of the protective layer 602 located on the top wall of the block body 601 appropriately, it can ensure that the protective layer 602 located on the top wall of the block body 601 is not easily damaged, prevent the bottom wall of the aviation fuel drum 20 from touching the top of the block body 601, and protect the aviation fuel drum 20.

[0138] In some embodiments, the top of the protective layer 602 is provided with a first protective layer chamfer 608. The first protective layer chamfer 608 is inclined downwardly, away from the central axis of the anti-tipping post 603. The angle of inclination of the first protective layer chamfer 608 relative to the central axis of the anti-tipping post 603 is less than 45°. Due to the large size and weight of the aviation fuel drum 20, the first protective layer chamfer 608 is provided on the top of the protective layer 602 to serve as a guide when the aviation fuel drum 20 needs to be placed on the drum support 201, facilitating quick placement of the aviation fuel drum 20 on the drum support 201. Furthermore, the angle of inclination of the first protective layer chamfer 608 relative to the central axis of the anti-tipping post 603 is less than 45°, which provides a better guide and allows the aviation fuel drum 20 to be placed on the drum support 201 more quickly.

[0139] exist Figures 1 to 6 In the embodiment shown, the aviation fuel refueling device 10 includes a control box 115, which is assembled on the pallet frame 200. The control box 115 is arranged close to the first side X1 relative to the second side X2 and is electrically connected to the battery 801. This arrangement allows the control box 115 to be separated from the aviation fuel drum 20 placed on the drum support 201, which has a high safety factor. In addition, the control box 115 is close to the front of the vehicle 101 and is closer to the battery 801 in the front of the vehicle 101, which facilitates connection with the battery 801, reduces the length of the power cord to the battery 801, and makes the structure of the entire aviation fuel refueling device 10 compact. Figure 28 As shown, the control box 115 is pluggably electrically connected to the battery 801. The control box 115 includes an inverter 804, and the fuel pump assembly 301 is pluggably electrically connected to the inverter 804. The inverter 804 converts the DC power output from the battery 801 into AC power and outputs it to power the fuel pump assembly 301. This configuration eliminates the need for external power supply, making the aviation fuel refueling device 10 more maneuverable and applicable in a wider range of scenarios. In some embodiments, the control box 115 includes an explosion-proof control box for even greater safety.

[0140] In some embodiments, the control box 115 and the fixing bracket 318 are arranged side by side along the second direction Y and staggered relative to the oil drum support 201 in the second direction Y. The control box 115, the fixing bracket 318, and the oil drum support 201 are arranged on the pallet frame 200, occupying a certain amount of space. If the structure is not compact, the aviation fuel refueling apparatus 10 would be larger, thereby increasing the area occupied by the aviation fuel refueling apparatus 10 and limiting its usability. Therefore, to ensure a smaller and more compact pallet frame 200 and aviation fuel refueling apparatus 10, the control box 115 and the fixing bracket 318 are arranged side by side along the second direction Y.

[0141] In some embodiments, a gap is provided between the control box 115 and the fixed bracket 318. When the oil pump assembly 301 is not assembled in the aviation fuel drum 20, the pump rod 312 is inserted into the storage tube 502 from one end thereof, and the other end of the storage tube 502 extends between the control box 115 and the fixed bracket 318. The storage tube 502 extends from the gap between the control box 115 and the fixed bracket 318, effectively utilizing the gap between the control box 115 and the fixed bracket 318. Its second storage end 504 is positioned toward the front of the vehicle 101. To clean or rinse the plug 505, the transport vehicle 100 can be separated from the pallet frame 200 and the plug 505 removed from the second storage end 504, facilitating operation.

[0142] In some embodiments, the control box 115 includes an operation panel 116, which is located on the side facing away from the oil drum support portion 201 in the second direction Y. The operation panel 116 and the storage bracket 500 are located on the same side of the second direction Y of the pallet frame 200. In some embodiments, the operation panel 116 includes an upper power interface 117 and an oil pump power interface 118, and the upper power interface 117 is pluggable and electrically connected to the power output interface 106. The plug-in electrical connection facilitates disassembly and connection. In some embodiments, the upper power interface 117 includes an explosion-proof plug. In some embodiments, the power output interface 106 includes an explosion-proof socket. By providing an explosion-proof plug and an explosion-proof socket for plug-in connection, safety is enhanced.

[0143] In some embodiments, the upper power connection port 117 is positioned closer to the first side X1 relative to the second side X2. This closer proximity to the power output port 106 reduces the length of the cable connecting the control box 115 to the battery 801. The fuel pump power connection port 118 is positioned closer to the second side X2 relative to the first side X1. This closer proximity to the fuel pump assembly 301 reduces the length of the cable connecting the fuel pump assembly 301 to the inverter 804, making the fuel refueling system 10 more compact.

[0144] In some embodiments, the oil pump assembly 301 includes a power input interface 330 (eg, Figure 3 As shown, the power input interface 330 is pluggably electrically connected to the fuel pump power interface 118. This pluggable electrical connection facilitates removal and connection. In some embodiments, the power input interface 330 includes an explosion-proof plug. In some embodiments, the fuel pump power interface 118 includes an explosion-proof socket. The provision of an explosion-proof plug and socket for pluggable connection enhances safety.

[0145] In some embodiments, the operating panel 116 also includes a wireless remote control switch 119. This wireless remote control switch 119 can be used to emergency-control the oil pump 310. The control box 115 includes a remote indicator light 120 electrically connected to the wireless remote control switch 119. The wireless remote control switch 119 is electrically connected to a battery 801. The battery 801 can power the wireless remote control switch 119. The remote indicator light 120 is located on the top surface of the control box 115. This placement places the remote indicator light 120 in a readily visible location, providing a convenient reminder to personnel.

[0146] In some embodiments, the operating panel 116 further includes a start switch 121 and a power-on indicator light 122. The start switch 121 is positioned closer to the front of the vehicle 101 than the power-on indicator light 122. The start switch 121 and the power-on indicator light 122 are electrically connected to the inverter 804. The start switch 121 is used to control the on / off connection between the inverter 804 and the oil pump assembly 301. The power-on indicator light 122 is used to indicate the operating status of the start switch 121. When the start switch 121 is turned on, the inverter 804 is connected to the oil pump assembly 301, and the power-on indicator light 122 is illuminated to indicate that the start switch 121 is in the on state. When the start switch 121 is turned off, the inverter 804 is disconnected from the oil pump assembly 301, and the power-on indicator light 122 is turned off to indicate that the start switch 121 is in the off state.

[0147] In some embodiments, the control box 115 includes an emergency pump stop function. Before operation, the emergency pump stop function of the control box 115 needs to be tested. The specific steps are: after the upper power interface 117 is connected, the main power switch 107 is turned on, the wireless remote control switch 119 is pressed "ON", and the start switch 121 on the control panel 116 of the control box 115 is pressed (for about 3 seconds or more). The power-on indicator light 122 of the control panel 116 of the control box 115 lights up, and the oil pump power interface 118 is powered normally. Then press the wireless remote control switch 119 "OFF", the power-on indicator light 122 of the control panel 116 of the control box 115 goes out, and the oil pump power interface 118 is powered off, indicating that the emergency pump stop function of the control box 115 is normal. Such testing ensures that the control box 115 can achieve emergency pump stop in an emergency, thereby improving safety.

[0148] Furthermore, in the event of an emergency, the specific emergency response steps include: first, turning off the wireless remote control switch 119 to stop the operation of the fuel pump 310; then, retracting the refueling coil 308 and turning off the fuel pump 310; then, retracting the static conductive wire reel 322; confirming that the support legs 203 of the pallet frame 200 are raised above the minimum safe height specified by the refueling site; then, towing the aviation fuel refueling device 10 away from the danger zone; and finally, turning off the main power switch 107 of the aviation fuel refueling device 10. This configuration improves the safety of both the personnel and the aviation fuel refueling device 10 in the event of an emergency.

[0149] Before towing the entire aviation fueling system 10, ensure that the power-on indicator 122 on the control panel 116 of the control box 115 is off and that the support legs 203 of the pallet frame 200 are raised above the minimum safety height specified by the refueling site. Before separating the transport vehicle 100 from the pallet frame 200, disconnect the electrical connection between the control box 115 and the front end 101 of the transport vehicle 100 and lower the transport vehicle 100 to its lowest position. These precautions ensure the safe use of the aviation fueling system 10.

[0150] In some embodiments, the pallet structure 200 is further provided with a safety sign 207 , which is distributed with the oil drum support portion 201 in the second direction Y. The safety sign 207 is used to indicate safety instructions to comply with safety standards.

[0151] See also Figure 28 As shown, the aviation fuel refueling device 10 also includes an oil pump power supply circuit 800, which is electrically connected to the oil pump assembly 301. In some embodiments, the oil pump power supply circuit 800 includes a rechargeable battery 801, a power conversion circuit 802, and a switch control circuit 803. The battery 801 can provide direct current (DC) power, and the power conversion circuit 802 can convert the DC power output by the battery 801 into alternating current (AC) power to supply power to the oil pump assembly 301. During this process, the on-off connection between the power conversion circuit 802 and the oil pump assembly 301 can be controlled by the switch control circuit 803. It should be noted that supplying power to the oil pump assembly 301 refers to supplying power to the motor 311 in the above embodiment. When the motor 311 is energized, the oil pump 310 can be driven to operate to achieve refueling operations.

[0152] In some embodiments, the power conversion circuit 802 includes an inverter 804, which is electrically connected to the battery 801 and the oil pump assembly 301, respectively. The inverter 804 converts the direct current output of the battery 801 into alternating current and outputs it to power the oil pump assembly 301. The switch control circuit 803 includes a control switch 805, which is electrically connected between the battery 801 and the inverter 804 and is used to control the connection between the inverter 804 and the battery 801. The rechargeable battery 801 of the oil pump power supply circuit 800 provides direct current, and the inverter 804 converts the direct current output of the battery 801 into alternating current and outputs it to power the oil pump assembly 301. The connection between the inverter 804 and the battery 801 is controlled by the control switch 805 of the switch control circuit 803. Such an arrangement can ensure the normal operation of the aviation fuel refueling device 10, and in the event of an emergency, the connection between the inverter 804 and the battery 801 can be promptly shut down by controlling the switch 805.

[0153] In some embodiments, the control switch 805 comprises a mechanical switch. The mechanical switch can be located in the control box 115 for easy operation by personnel. With assistance from personnel, the mechanical switch can be operated to control the connection between the inverter 804 and the battery 801. This method is safe and reliable. The mechanical switch can be the main power switch 107 described in the above embodiment, located on the top surface of the power supply unit 104.

[0154] exist Figure 29 In the illustrated embodiment, the control switch 805 comprises an electromagnetic switch; the switch control circuit 803 further comprises a remote control 806 and a remote control circuit 807 that communicates with the remote control 806. The remote control circuit 807 is electrically connected to the electromagnetic switch and controls the electromagnetic switch on and off according to control commands from the remote control 806. By providing an electromagnetic switch, remote control 806 can be used to remotely control the electromagnetic switch, enabling timely shutdown, thereby enhancing safety. In some embodiments, the electromagnetic switch includes a relay, which has high sensitivity and can be shut off promptly.

[0155] In some embodiments, the remote controller 806 includes a transmitter 808, and the remote control circuit 807 includes a receiver 809 and a controller 810 electrically connected to the receiver 809. The receiver 809 communicates with the transmitter 808, receiving signals from the transmitter 808 and outputting corresponding electrical signals. The controller 810 includes a first control port 8101 electrically connected to the electromagnetic switch. The controller 810 controls the electromagnetic switch on and off via the first control port 8101 based on the electrical signals output by the receiver 809. In some embodiments, the signal received by the receiver 809 from the transmitter 808 may indicate an on or off signal, and the receiver 809 outputs a corresponding electrical signal indicating an on or off state. In this case, the controller 810 controls the electromagnetic switch on or off via the first control port 8101. Compared to a mechanical switch, this method allows remote control of the operating state of the oil pump assembly 301 without the need for operator operation, making it more convenient and labor-saving.

[0156] In some embodiments, the transmitter 808 includes an infrared transmitter, and the receiver 809 includes an infrared receiver. Through communication between the infrared transmitter and the infrared receiver, remote control is possible without geographical or distance restrictions.

[0157] In some embodiments, the remote control circuit 807 further includes a remote control indicator light 120, which is electrically connected to the controller 810. The controller 810 includes a second control port 8102, which is electrically connected to the remote control indicator light 120. The controller 810 controls the remote control indicator light 120 via the second control port 8102 based on the electrical signal output by the receiver 809 to indicate the reception status of the receiver 809. When the receiver 809 receives a signal transmitted by the transmitter 808 and outputs a corresponding electrical signal, the controller 810 can receive the electrical signal. At this time, the controller 810 controls the remote control indicator light 120 to indicate the reception status of the receiver 809. This configuration can conveniently prompt staff members and avoid repeated operations. In this way, the transmission and reception status between the transmitter 808 and the receiver 809 can be observed.

[0158] In some embodiments, the oil pump power supply circuit 800 further includes a start switch 121, which is electrically connected between the inverter 804 and the oil pump assembly 301. The start switch 121 is used to control the on / off state between the inverter 804 and the oil pump assembly 301. In some embodiments, the oil pump power supply circuit 800 further includes a power-on indicator light 122, which is electrically connected between the start switch 121 and the oil pump assembly 301. The power-on indicator light 122 is used to indicate the on / off state of the oil pump assembly 301 and the inverter 804. It should be noted that the battery 801, the inverter 804, the remote control indicator light 120, the start switch 121, and the power-on indicator light 122 included in the oil pump power supply circuit 800 can be the above-mentioned Figures 1 to 26 The battery 801, inverter 804, remote control indicator light 120, start switch 121, and power-on indicator light 122 of the embodiment shown can be specifically referred to the above embodiments and will not be described in detail here.

[0159] See also Figure 30 and Figure 31 The embodiment shown, with Figures 23 to 26 The embodiment shown is similar, with the main difference being that the anti-dump block 900 includes a plurality of arcuate anti-dump plates 903 spaced apart along the edge of the fuel drum support portion 201. Compared to the anti-dump posts 603, the anti-dump plates 903 have a larger surface area. When the aviation fuel drum 20 tips over, they have a greater contact area with the drum 20, thereby providing a better anti-dumping effect. The top area of ​​the arcuate anti-dump plates 903 is larger than the top area of ​​the anti-dump posts 603. During assembly and disassembly of the aviation fuel drum 20, the contact area with the bottom wall of the drum 20 is greater, providing more uniform support. This prevents the drum 20 from tipping over during assembly or disassembly, and, due to its larger size and weight, less likely to damage the bottom of the drum 20.

[0160] exist Figure 30In the embodiment shown, the distance L6 between two adjacent anti-dumping plates 903 ranges from 50 mm to 70 mm. In some embodiments, the distance L6 between two adjacent anti-dumping plates 903 can be 50 mm, 55 mm, 60 mm, 65 mm, or 70 mm, with a preferred value of 60 mm. Figure 31 In the illustrated embodiment, the thickness L7 of the stopper body 901 of the anti-dump plate 903 ranges from 20 mm to 30 mm. In some embodiments, the thickness L7 of the stopper body 901 of the anti-dump plate 903 can be 20 mm, 25 mm, or 30 mm, with a preferred value of 25 mm. In some embodiments, the ratio of the thickness of the stopper body 901 of the anti-dump plate 903 to the thickness of the aviation fuel tank 20 ranges from 15 to 20, with a preferred value of 16.7. In some embodiments, the thickness L8 of the protective layer 902 located on the top wall of the stopper body 901 of the anti-dump plate 903 ranges from 5 mm to 15 mm. In some embodiments, the thickness L8 of the protective layer 902 located on the top wall of the stopper body 901 can be 5 mm, 7 mm, 9 mm, 11 mm, 13 mm, or 15 mm, with a preferred value of 10 mm. In some embodiments, the thickness L9 of the protective layer 902 located on the peripheral wall of the stopper body 901 of the anti-dump plate 903 ranges from 1 mm to 5 mm. The thickness L9 of the protective layer 902 located on the periphery of the block body 901 can be 1 mm, 2 mm, 3 mm, 4 mm, or 5 mm, with a preferred thickness of 3 mm. In some embodiments, a second protective layer chamfer 908 is provided on the top of the protective layer 902. The second protective layer chamfer 908 slopes downward from the outer sidewall of the anti-dump plate 903 toward the inner sidewall. The angle of the second protective layer chamfer 908 relative to the vertical direction is less than 45°. In some embodiments, multiple anti-dump plates 903 are welded to the upper surface of the pallet frame 200.

[0161] See also Figure 32 The embodiment shown, with Figure 30 The embodiment shown is similar, with the primary difference being that the anti-dump block 1000 includes an annular anti-dump ring 1003 that surrounds the fuel drum support (not shown). Compared to the multiple arc-shaped anti-dump plates 903, the anti-dump ring 1003 is easier to assemble. Its larger surface area allows for greater contact with the aviation fuel drum 20 when it tips over, resulting in a better anti-dumping effect and more uniform support, making it less likely to tip over during assembly or disassembly of the aviation fuel drum 20.

[0162] In some embodiments, the anti-dump ring 1003 is welded to the upper surface of the pallet frame 200. In some embodiments, a third protective layer chamfer 1008 is provided on the top of the protective layer. The third protective layer chamfer 1008 is inclined downward from the outer side wall of the anti-dump ring 1003 toward the inner side wall. The angle of the third protective layer chamfer 1008 relative to the vertical direction is less than 45 degrees.

[0163] See also Figure 33 The embodiment shown, with Figures 1 to 5 The embodiment shown is similar, with the main difference being that the oil drum support portion 201 is positioned closer to the first side X1 relative to the second side X2. This arrangement places the center of gravity of the entire aviation fuel refueling device 10 closer to the vehicle front 101, providing better stability during movement.

[0164] The technical solutions disclosed in the various embodiments of this application can complement each other if no conflict occurs.

[0165] The above description is only a preferred embodiment of the present application and is not intended to limit the present application. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present application shall be included in the scope of protection of the present application.

Claims

1. An aviation fuel refueling device, characterized in that: include: Pallet frame for carrying aviation fuel drums; and An oil pumping device is provided on the pallet frame, and includes an oil pump assembly, a filter separator, a flow meter, a hose reel and a refueling gun; Quick-release assembly; the oil pump assembly is detachably assembled to the aviation fuel barrel via the quick-release assembly, the quick-release assembly comprising a fixing seat and a sealing cover detachably assembled to the fixing seat, the fixing seat being an annular structure, the fixing seat being clamped to the oil outlet of the aviation fuel barrel, and the top surface of the fixing seat being higher than the top surface of the oil outlet; The outer peripheral wall of the fixing base is provided with a plurality of flanges, and the plurality of flanges extend obliquely along the circumference of the fixing base; the sealing cover includes a cover body and a plurality of ear buckles, the ear buckles extend downward from the edge of the cover body, and the ends of the ear buckles away from the cover body are bent inward; the flanges are limitedly engaged with the ear buckles; When the oil pump assembly is assembled in the aviation fuel drum, the oil inlet end of the oil pump assembly extends into the aviation fuel drum and contacts the oil in the aviation fuel drum; the oil inlet end of the filter separator is connected to the oil outlet end of the oil pump assembly; the oil inlet end of the flow meter is connected to the oil outlet end of the filter separator; the oil inlet end of the hose reel is connected to the oil outlet end of the flow meter; the oil inlet end of the refueling gun is connected to the oil outlet end of the hose reel; when the oil pump assembly is not assembled in the aviation fuel drum, it is placed on the pallet frame; The oil pump assembly includes an oil pump and a motor drivingly connected to the oil pump; the oil pump includes a pump rod, a support seat, and blades arranged in the pump rod, the blades being arranged at an end of the pump rod away from the motor, the blades being spaced apart from the end of the oil inlet end, and when the oil pump assembly is assembled to the aviation fuel barrel, the pump rod extends into the aviation fuel barrel so that the blades are immersed in the oil in the aviation fuel barrel, the support seat is arranged between the oil inlet end and the oil outlet end of the oil pump, and when the oil pump assembly is assembled to the aviation fuel barrel, the flange and the support seat are limitedly engaged; The tube wall of the pump rod is clamped with the oil outlet of the aviation fuel barrel, and the support seat is in contact with the oil outlet of the aviation fuel barrel.

2. The aviation fuel refueling device according to claim 1, characterized in that: The oil pump and the motor are assembled via a quick-release structure; and / or The oil pump includes an explosion-proof oil pump; and / or The motor comprises an explosion-proof motor.

3. The aviation fuel refueling device according to claim 1, characterized in that: The aviation fuel refueling device further includes a transport vehicle, which includes a vehicle front and a fork extending from the vehicle front to the vehicle rear, and the fork supports the pallet frame.

4. The aviation fuel refueling device according to claim 3, characterized in that: The aviation fuel refueling device includes a power supply device and a control box; The power supply device includes a battery assembled on the vehicle head, the control box is assembled on the tray frame, the control box is pluggably electrically connected to the battery, the control box includes an inverter, the oil pump assembly is pluggably electrically connected to the inverter, the inverter converts the direct current output of the battery into alternating current and outputs it to power the oil pump assembly; and / or The control box includes an explosion-proof control box.

5. The aviation fuel refueling device according to claim 3, characterized in that: The transport truck includes a liftable fork, which includes a raised state and a lowered state; the pallet frame is provided with a plurality of supporting legs, which extend downward from the lower surface of the pallet frame; when the fork is in the raised state, the pallet frame is lifted by the fork, and the plurality of supporting legs are off the ground; when the fork is in the lowered state, the pallet frame is lowered, and the plurality of supporting legs are on the ground.

6. The aviation fuel refueling device according to claim 5, characterized in that: The pallet frame is provided with a retractable first roller, which includes an extended state and a retracted state. When the fork is in the raised state, the first roller is in the retracted state and the first roller is off the ground. When the fork is in the lowered state, the first roller is in the extended state and the first roller is on the ground.

7. The aviation fuel refueling device according to claim 3, characterized in that: The transport vehicle and the pallet frame are separable and assembleable; and / or The aviation fuel refueling device includes a positioning assembly, which includes a positioning pin and a positioning ring corresponding to the position of the positioning pin, wherein the positioning pin is provided on a side of the pallet frame facing the vehicle head and extends in a horizontal direction; the positioning ring is provided on one side of the vehicle head, and the opening of the positioning ring faces the pallet frame; when the pallet frame is assembled on the transport vehicle, the positioning pin is correspondingly inserted into the positioning ring, and when the pallet frame is separated from the transport vehicle, the positioning pin is separated from the positioning ring; and / or The transport vehicle comprises an explosion-proof electric transport vehicle.

8. The aviation fuel refueling device according to claim 1, characterized in that: The pallet frame is provided with a plurality of second rollers and a plurality of brake members corresponding to the positions of the plurality of second rollers. The second rollers are fixed to the bottom of the pallet frame and in contact with the ground. The brake members include a braking position and a non-braking position. When the brake member is in the braking position, the second rollers are braked. When the brake member is in the non-braking position, the second rollers are released from the brake and can move.

9. The aviation fuel refueling device according to claim 1, characterized in that: The pallet frame is provided with a plurality of lifting rings, which extend upward from the upper surface of the pallet frame and are used for assembly with external lifting tooling; and / or The pallet frame comprises stainless steel plates.

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