Fuel oil filling device

Abstract

The application provides a kind of aviation fuel refueling device, including tray frame, storage support and oil pump assembly.Oil drum support part of aviation fuel drum is used to be carried by tray frame.Storage support and oil pump assembly are assembled to tray frame.Storage support includes a plurality of support rods and storage tubes, support rods extend upward from the upper surface of tray frame, and storage tubes are assembled to the upper end of a plurality of support rods relative to the upper surface of tray 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, the pump rod is housed in the storage tube when the oil pump assembly is not assembled to the aviation fuel drum, and the motor is located outside the storage tube. By such arrangement, when the oil pump assembly is not assembled to the aviation fuel drum, the oil pump assembly is assembled to the storage support, the center of gravity of the aviation fuel refueling device is lowered, the stability of transportation is better, and the pump rod of the oil pump assembly is housed in the storage support, the motor of the oil pump assembly is located outside the storage tube, and it is convenient to take.

Description

Technical Field

[0001] This application relates to the field of aviation fuel refueling technology, and in particular to an aviation fuel refueling device. Background Technology

[0002] With the rapid development of my country's economy, the aviation industry has also developed significantly. However, the fuel pump components of existing aviation fuel refueling equipment are not properly stored, making them inconvenient to access and causing inconvenience to staff. Summary of the Invention

[0003] This application provides an aviation fuel refueling device that facilitates the removal of the fuel pump assembly.

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

[0005] Pallet frame, a support structure for carrying aviation fuel drums;

[0006] A storage bracket, assembled onto the tray frame; wherein the storage bracket includes a plurality of support rods and a storage tube, the support rods extending upward from the upper surface of the tray frame, and the storage tube being assembled obliquely to the upper end of the plurality of support rods relative to the upper surface of the tray frame; and

[0007] An oil pump assembly is assembled on the pallet frame; the oil pump assembly is detachably assembled with the aviation fuel tank to extract oil from the aviation fuel tank; wherein the oil pump assembly includes an oil pump and a motor driven by the oil pump, the oil pump includes a pump rod, and when the oil pump assembly is not assembled with the aviation fuel tank, the pump rod is housed in the receiving tube, and the motor is located outside the receiving tube.

[0008] Optionally, the pallet frame extends along a first direction and a second direction, the first direction and the second direction are in the same horizontal plane, the second direction is perpendicular to the first direction, the storage bracket and the oil drum support are distributed along the second direction, and the storage tube is inclined relative to the upper surface of the pallet frame and the second direction.

[0009] Optionally, the pallet frame includes a first side and a second side opposite to each other in the first direction; the receiving tube includes a first receiving end and a second receiving end opposite to each other, wherein the first receiving end and the oil drum support are distributed along the second direction, the first receiving end is closer to the second side relative to the first side, and the second receiving end is closer to the first side relative to the second side; when the oil pump assembly is not assembled to the aviation fuel drum, the pump rod extends from the first receiving end to the second receiving end, and the motor is located outside the first receiving end.

[0010] Optionally, the receiving tube extends obliquely in the direction from the second side to the first side, and in the second direction toward the direction of the oil drum support.

[0011] Optionally, the first storage end is higher than the second storage end.

[0012] Optionally, the aviation fuel refueling device includes a transport vehicle, which includes a cab and forks extending from the cab along the first direction, the cab being located on the first side, and the forks supporting the pallet frame.

[0013] Optionally, the angle of inclination of the storage tube relative to the upper surface of the tray frame is in the range of 5° to 15°.

[0014] Optionally, the tilt angle of the storage tube relative to the second direction is in the range of 65° to 85°.

[0015] Optionally, the plurality of support rods are spaced apart along the first direction and the second direction.

[0016] Optionally, the storage bracket includes a plug, which is detachably assembled to the second storage end to seal the second storage end.

[0017] Optionally, the oil pump includes an oil inlet end located on the pump rod away from the motor. When the oil pump assembly is not assembled into the aviation fuel tank, the oil inlet end is located inside the receiving pipe, closer to the second receiving end relative to the first receiving end, and at a distance from the plug.

[0018] Optionally, the plug is made of Teflon.

[0019] Optionally, the storage bracket includes a ring support member, which is disposed at the first storage end and is at least attached to the inner wall and end face of the first storage end. When the pump rod is housed in the storage tube, the outer wall of the pump rod is in contact with the inner wall of the ring support member, and there is a gap between the outer wall of the pump rod and the inner wall of the storage tube.

[0020] Optionally, the oil pump includes an oil inlet end located away from the motor and an oil outlet end located near the motor on the pump rod; the oil pump assembly also includes a support base located on the pump rod, between the oil inlet end and the oil outlet end, and positioned closer to the oil outlet end than the oil inlet end; when the pump rod is housed in the receiving tube, the bottom of the support base abuts against the top of the annular support member.

[0021] Optionally, the inner diameter of the ring support is in the range of 50mm to 80mm.

[0022] Optionally, the material of the ring support is Teflon.

[0023] Optionally, the cross-section of the ring support is U-shaped and is clamped to the first receiving end.

[0024] Optionally, the oil pump includes an oil inlet end located away from the motor and an oil outlet end located near the motor on the pump rod; the receiving tube includes a limiting protrusion, the limiting protrusion protruding from the inner peripheral wall of the receiving tube, the limiting protrusion being located near the second receiving end relative to the first receiving end; when the pump rod is received in the receiving tube, the limiting protrusion abuts against the pump rod.

[0025] Optionally, the oil pump assembly further includes a motor handle located on one side of the motor.

[0026] Optionally, the oil pump assembly further includes a handheld part disposed on the pump rod and located above the oil outlet end.

[0027] Optionally, the oil pump assembly further includes a dust cover located on one side of the motor.

[0028] When the fuel pump assembly of the aviation fuel refueling device provided in this application embodiment is not assembled on the aviation fuel tank, the fuel pump assembly is assembled on the storage bracket. The center of gravity of the aviation fuel refueling device is lowered, and the stability of transportation is better. In addition, the pump rod of the fuel pump assembly is housed in the storage bracket, and the motor of the fuel pump assembly is located outside the storage tube, which is convenient for handling. Attached Figure Description

[0029] Figure 1 The diagram shown is a structural schematic of an embodiment of the fuel pump assembly of the fuel refueling device of this application assembled in a fuel tank;

[0030] Figure 2 As shown Figure 1 A schematic diagram of the aviation fuel refueling device from another perspective;

[0031] Figure 3 As shown Figure 1 A schematic diagram of the aviation fuel refueling device from another perspective;

[0032] Figure 4 As shown Figure 1 A schematic diagram of the aviation fuel refueling device from another perspective;

[0033] Figure 5 As shown Figure 1 A schematic diagram of the aviation fuel refueling device from another perspective;

[0034] Figure 6The diagram shown is a structural schematic of an embodiment of the aviation fuel refueling device of this application where the fuel pump assembly is not assembled into the aviation fuel tank;

[0035] Figure 7 The diagram shown is a structural schematic of an embodiment of the aviation fuel refueling device of this application, in which the transport vehicle and the pallet frame are separated, and the oil pump assembly is not assembled to the aviation fuel tank;

[0036] Figure 8 The diagram shown is a structural schematic of another embodiment of the tray frame of the aviation fuel refueling device of this application;

[0037] Figure 9 The diagram shown is a cross-sectional schematic of an embodiment of the quick-release assembly of the aviation fuel refueling device of this application assembled in an aviation fuel tank, wherein the fuel pump assembly is not assembled in the aviation fuel tank;

[0038] Figure 10 The diagram shown is a structural schematic of one embodiment of the quick-release assembly of the aviation fuel refueling device of this application;

[0039] Figure 11 As shown Figure 10 A cross-sectional view of the quick-release assembly of the aviation fuel refueling device shown;

[0040] Figure 12 As shown Figure 10 A cross-sectional schematic diagram of the quick-release assembly of the aviation fuel refueling device from one perspective;

[0041] Figure 13 As shown Figure 10 A cross-sectional schematic diagram of the quick-release assembly of the aviation fuel refueling device from another perspective;

[0042] Figure 14 As shown Figure 10 A schematic diagram of the structure of one embodiment of the mounting base of the quick-release assembly of the aviation fuel refueling device shown;

[0043] Figure 15 As shown Figure 14 A front view of the mounting bracket of the quick-release assembly of the aviation fuel refueling device;

[0044] Figure 16 As shown Figure 14 A cross-sectional schematic diagram of the mounting bracket of the quick-release assembly of the aviation fuel refueling device shown;

[0045] Figure 17 As shown Figure 10 A schematic diagram of the sealing cap of the quick-release assembly of the aviation fuel refueling device shown;

[0046] Figure 18 As shown Figure 17A cross-sectional schematic diagram of the sealing cap of the quick-release assembly of the aviation fuel refueling device shown;

[0047] Figure 19 As shown Figure 1 A top view schematic diagram of a portion of the aviation fuel refueling device shown;

[0048] Figure 20 As shown Figure 19 A schematic diagram of a portion of the aviation fuel refueling device from one perspective.

[0049] Figure 21 As shown Figure 19 A schematic diagram of a portion of the aviation fuel refueling device from another perspective;

[0050] Figure 22 As shown Figure 19 The diagram shows the structure of the fuel pump assembly of the aviation fuel refueling device housed in the storage bracket.

[0051] Figure 23 As shown Figure 22 A schematic diagram of the structure of the aviation fuel refueling device's storage bracket A shown;

[0052] Figure 24 As shown Figure 1 A schematic diagram of the anti-tipping stop of the aviation fuel refueling device from one perspective;

[0053] Figure 25 As shown Figure 24 A cross-sectional schematic diagram of the anti-tipping stop of the aviation fuel refueling device shown;

[0054] Figure 26 As shown Figure 1 A schematic diagram of the anti-tipping block of the aviation fuel refueling device from another perspective;

[0055] Figure 27 As shown Figure 26 A cross-sectional schematic diagram of the anti-tipping stop of the aviation fuel refueling device shown;

[0056] Figure 28 As shown Figure 1 The diagram shows the principle block diagram of the fuel pump power supply circuit of the aviation fuel refueling device.

[0057] Figure 29 As shown Figure 28 The schematic diagram of the switch control circuit of the oil pump power supply circuit is shown.

[0058] Figure 30 The diagram shown is a structural schematic of another embodiment of the anti-tipping stop of the aviation fuel refueling device of this application;

[0059] Figure 31 As shown Figure 30 A cross-sectional schematic diagram of another embodiment of the anti-tipping stop of the aviation fuel refueling device shown;

[0060] Figure 32 The diagram shown is a structural schematic of another embodiment of the anti-tipping stop of the aviation fuel refueling device of this application;

[0061] Figure 33 The diagram shown is a structural schematic of another embodiment of the anti-tipping stop of the aviation fuel refueling device of this application. Detailed Implementation

[0062] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numerals in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses consistent with some aspects of this application as detailed in the appended claims.

[0063] The terminology used in this application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. Unless otherwise defined, the technical or scientific terms used in this application should be understood in their ordinary sense by one of ordinary skill in the art to which this application pertains. The words “a” or “one” and similar terms used in this specification and claims do not indicate a limitation of quantity, but rather indicate the presence of at least one. “A plurality” includes two, equivalent to at least two. The words “comprising” or “including” and similar terms mean that the element or object preceding “comprising” or “including” covers the element or object listed following “comprising” or “including” and its equivalents, and does not exclude other elements or objects. The words “connected” or “linked” and similar terms are not limited to physical or mechanical connections and can include electrical connections, whether direct or indirect. The singular forms “a,” “the,” and “the” used in this specification and appended claims are also intended to include the plural forms, unless the context clearly indicates otherwise. It should also be understood that the term “and / or” as used herein refers to and includes any or all possible combinations of one or more associated listed items.

[0064] The aviation fuel refueling device provided in this application includes a pallet frame, a storage bracket, and a fuel pump assembly. The pallet frame serves as a support for aviation fuel drums. The storage bracket is assembled to the pallet frame; the storage bracket includes multiple support rods and a storage tube, the support rods extending upwards from the upper surface of the pallet frame, and the storage tube being assembled obliquely to the upper end of the multiple support rods relative to the upper surface of the pallet frame. The fuel pump assembly is assembled to the pallet frame; the fuel pump assembly is detachably assembled with the aviation fuel drum to extract fuel from the drum; the fuel pump assembly includes a fuel pump and a motor connected to the fuel pump drive, the fuel pump including a pump rod, and when the fuel pump assembly is not assembled to the aviation fuel drum, the pump rod is housed within the storage tube, and the motor is located outside the storage tube. With this configuration, when the fuel pump assembly is not assembled on the fuel tank, it is assembled on the storage bracket. This lowers the center of gravity of the fuel refueling device, improves the stability of transportation, and houses the pump rod of the fuel pump assembly inside the storage bracket, while the motor of the fuel pump assembly is located outside the storage tube for easy access.

[0065] This application provides an aviation fuel refueling device. The aviation fuel refueling device of this application will be described in detail below with reference to the accompanying drawings. Unless otherwise specified, the following embodiments and features can be combined with each other.

[0066] The aviation fuel refueling unit 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, or other geographically harsh environments. The aviation fuel can be aviation gasoline or aviation kerosene, referred to as "aviation fuel".

[0067] Combination Figures 1 to 6 As shown, the aviation fuel refueling device 10 includes a transport vehicle 100, a pallet frame 200, a fuel pump 300, a storage bracket 500, and an anti-tipping block 600.

[0068] Specifically, the pallet truck 100 includes a cab 101 and forks 102. The forks 102 are connected to the cab 101 and extend from the cab 101 to the rear of the truck, supporting the pallet frame 200. The rear of the truck refers to the area opposite the cab 101, extending away from the cab 101. In some embodiments, the cab 101 is also provided with a handle 103 for workers to hold, controlling the direction of movement of the pallet truck 100 for convenient use.

[0069] In some embodiments, the pallet frame 200 includes a drum support 201 for carrying aviation fuel drums 20. The aviation fuel drums 20 can be manually loaded, unloaded, and replaced using an external drum handling vehicle; this method is simple, easy to operate, and economical. A pumping device 300, a storage bracket 500, and an anti-tipping block 600 are mounted on the pallet frame 200, and the upper surface of the pallet frame 200 supports the pumping device 300, the storage bracket 500, and the anti-tipping 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 (e.g., ...). Figure 1 (As shown). In Figure 1 In the embodiment shown, the pallet frame 200 can be a rectangular plate, the first direction X can be the extension direction of the long side of the rectangular plate, and the second direction Y can be the extension direction of the short side of the rectangular plate.

[0070] In some embodiments, the pallet frame 200 includes a first side X1 and a second side X2 opposite to each other in a first direction X. The first side X1 faces the front of the vehicle 101, and the second side X2 is away from the front of the vehicle 101. The fuel tank support 201 is disposed relative to the first side X1 and close to the second side X2. In some embodiments, the forks 102 extend from the front of the vehicle 101 along the first direction X, and the front of the vehicle 101 is located on the first side X1. This arrangement separates the aviation fuel tank 20 placed on the fuel tank support 201 from the front of the vehicle 101 and away from it, increasing safety.

[0071] The aviation fuel refueling device 10 refuels general aviation equipment using gravity refueling. Gravity refueling refers to the method of adding aviation fuel by its own weight, flowing from the fuel tank 20's outlet into the general aviation equipment. Refueling efficiency can be accelerated by using a pumping device 300. In some embodiments, the pumping device 300 includes a pump assembly 301, a filter separator 302, a flow meter 303, a hose reel 304, a refueling nozzle 305, and a sight glass 306. The pump assembly 301 is detachably assembled to the aviation fuel tank 20 and is used to draw fuel from the tank. The inlet end of the filter separator 302 is connected to the outlet end of the pump assembly 301. The inlet end of the flow meter 303 is connected to the outlet end of the filter separator 302. The inlet end of the hose reel 304 is connected to the outlet end of the flow meter 303. The inlet end of the refueling nozzle 305 is connected to the outlet end of the hose reel 304. The inlet of the sight glass 306 is connected to the outlet of the fuel 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 settles to the bottom of the filter separator 302 can be manually drained. The filter separator 302 meets a filtration accuracy of 5μm or complies with the requirements of GB / T 21358-2008 "General Technical Specifications for Jet Fuel Filter Separators". The filter separator 302 must be checked before each use of the fuel pump unit 300 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.

[0072] In some embodiments, the hose reel 304 includes a reel support 307, an oil filling coil 308 disposed on the reel support 307, and a coil handle 309. The oil filling nozzle 305 is connected to the flow meter 303 via the oil filling coil 308. By operating the coil handle 309, the reel support 307 is rotated, causing the oil filling coil 308 to be wound out of the reel support 307 or retracted back to the oil filling coil support 307, thus ensuring a compact structure and reduced footprint for the entire pumping device 300. In some embodiments, the oil filling coil 308 can be manually wound or spring-loaded. In some embodiments, the gravity-fed rated flow rate of the oil filling coil 308 can reach 25 L / min, the diameter of the oil filling coil 308 is 20 mm to 40 mm, preferably 30 mm, and the length of the oil filling coil 308 can reach 15 m. In some embodiments, the sight glass 306 can observe whether the oil (pure or contaminated) in the refueling line has passed through the refueling coil 308 to reach the refueling nozzle 305, so as to ensure that refueling can be carried out smoothly.

[0073] In some embodiments, the coil handle 309 is located on the side of the reel bracket 307 facing away from the fuel drum support 201 in the first direction X. During refueling, the coil handle 309 needs to be operated to reel out the fuel refueling coil 308. The coil handle 309 is positioned on the side of the reel bracket 307 facing the vehicle front 101, and at least partially above the vehicle front 101. This facilitates operation by the operator. 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 operator from easily hitting the top surface of the vehicle front 101, making it easier for them to use. In some embodiments, the fuel nozzle 305 is located on the side of the reel bracket 307 facing away from the coil handle 309 in the first direction X. The fuel nozzle 305 and the coil handle 309 are located on both sides of the reel bracket 307. This effectively utilizes the side space of the reel bracket 307, making the aviation fuel refueling device 10 more compact, and also facilitates operation by the operator.

[0074] exist Figures 1 to 5 In the illustrated embodiment, when the fuel pump assembly 301 is assembled into the aviation fuel tank 20, the inlet end of the fuel pump assembly 301 extends into the aviation fuel tank 20 and comes into contact with the fuel inside. Since aviation gasoline is a low flash point fuel, extending the inlet end of the fuel pump assembly 301 into the aviation fuel tank 20 and ensuring full contact with the fuel prevents the inlet end of the fuel pump assembly 301 from contacting air, thus avoiding sparks and improving safety. Compared to existing technologies using self-priming fuel pumps, this embodiment avoids the formation of vapors due to air pressure, preventing vapor lock and cavitation in the fuel pump assembly 301. Figure 6 In the illustrated embodiment, the fuel pump assembly 301 is placed on the pallet frame 200 when not assembled to the fuel tank 20. When refueling is needed, the fuel pump assembly 301 is assembled to the fuel tank 20; when refueling is not needed, the fuel pump assembly 301 is placed on the pallet frame 200. This allows for convenient refueling of aviation equipment from the fuel tank 20 during operation. The fuel pump assembly can be removed from the fuel tank, allowing for replacement with another fuel tank when the fuel is depleted or nearly depleted. The operation is flexible and convenient. Furthermore, the entire fuel refueling device allows for refueling using fuel tanks, making it suitable for refueling general aviation equipment. The fuel refueling device can be relatively miniaturized and adapted to harsh geographical environments, such as refueling general aviation equipment in disaster relief situations.

[0075] Furthermore, when refueling is not required, placing the fuel pump assembly 301 on the pallet frame 200 enhances safety during transportation. Because the fuel pump assembly 301 has a certain weight and volume, if it is assembled into the aviation fuel tank 20 and cannot be disassembled, it adds weight to the top of the tank 20, raising its center of gravity and making it prone to tipping over during transport, potentially posing a safety hazard. Moreover, prolonged insertion of the fuel pump assembly 301 into the aviation fuel tank 20 can also affect the quality of the fuel within.

[0076] Combination Figure 22 and Figure 23 In the illustrated embodiment, the oil pump assembly 301 includes an oil pump 310 and a motor 311 driven by the oil pump 310. The motor 311 provides power to the oil pump 310 to drive its operation. The oil pump 310 includes a pump rod 312, blades 313 disposed within the pump rod 312, a support 314, and an inlet end 315 located on the pump rod 312 away from the oil pump 310 and an outlet end 316 located near the oil pump 310. The blades 313 are located at the end of the pump rod 312 away from the motor 311 and are closer to the inlet end 315 relative to the outlet end 316. The support 314 is located between the inlet end 315 and the outlet end 316 of the oil pump 310 and is positioned closer to the outlet end 316 relative to the inlet end 315. When the fuel pump assembly 301 is assembled into the aviation fuel tank 20, the pump rod 312 is inserted into the aviation fuel tank 20, the inlet end 315 is inserted into the aviation fuel tank 20, the vane 313 is immersed in the fuel in the aviation fuel tank 20, and the outlet end 316 is exposed outside the aviation fuel tank 20 and connected to external pipelines. Since aviation gasoline is a low flash point fuel, ensuring full contact between the vane 313 and the fuel in the aviation fuel tank 20 prevents the inlet end 315 of the fuel pump 310 from contacting air, thus avoiding sparks and improving safety. Furthermore, during this fuel extraction process, the pipe wall of the pump rod 312 engages with the outlet of the aviation fuel tank 20, and the support base 314 abuts against the outlet of the aviation fuel tank 20, ensuring that it does not easily detach during extraction and providing better stability.

[0077] In some embodiments, the oil pump 310 can be a vane-type pump that does not require priming and can run dry for up to 30 minutes without being damaged by dry running. The oil pump 310 and motor 311 are infinitely variable in speed, allowing for adjustable flow rates to meet different filling requirements. The maximum flow rate can reach 50L, and operators can flexibly configure the pump according to actual needs. Furthermore, the motor 311 is equipped with an overheat protection device to prevent burnout due to overload.

[0078] In some embodiments, the aviation fuel refueling device 10 further includes a flame arrestor vent valve 317, which is assembled at the air inlet of the aviation fuel tank 20. The aviation fuel tank 20 can be connected to the outside through the flame arrestor vent valve 317, ensuring pressure equalization within the aviation fuel tank 20. Furthermore, the flame arrestor vent valve 317 prevents external open flames from entering the aviation fuel tank 20, providing a high safety factor. In some embodiments, the aviation fuel refueling device also includes a pressure monitoring component (not shown), which can monitor system pressure in real time to ensure safe use and maintenance.

[0079] In some embodiments, the oil pump 310 and the motor 311 are assembled via a quick-release structure. This quick-release assembly offers advantages such as a compact structure, convenient installation without the need for auxiliary tools, and ease of disassembly and cleaning for convenient maintenance. In some embodiments, the oil pump 310 includes an explosion-proof oil pump with a power consumption of up to 880W. In some embodiments, the motor 311 includes an explosion-proof motor. The use of explosion-proof oil pumps and motors prevents explosions and ensures high safety. In some embodiments, the overall weight of the oil pump 310 and motor 311 ranges from 4kg to 8kg. Compared to existing oil pump assemblies 301, this is lighter and easier to carry and maintain. In some embodiments, the oil pump assembly 301 can be of model HD-E2-V+SS304-1000HP or a German FLUX drum pump.

[0080] In some embodiments, the pallet truck 100 includes an electric pallet truck. In some embodiments, the pallet truck 100 includes an explosion-proof electric pallet truck. This explosion-proof electric pallet truck has electronic steering and an explosion-proof rating of IIB T4 Gb. Since the pallet truck 100 transports aviation gasoline, a low flash point fuel, higher safety requirements are imposed, thus the use of this explosion-proof electric pallet truck provides enhanced safety. In some embodiments, the heavy-duty dimensions of the pallet truck 100 are 2300mm*1000mm*2100mm, and the unloaded dimensions are 2300mm*1000mm*1200mm. In some embodiments, the maximum permissible gross weight of the pallet truck 100 can reach 1.5t, indicating a large load capacity. The maximum speed of the pallet truck 100 can reach 4km / h.

[0081] In some embodiments, the transport vehicle 100 includes a power supply unit 104 and a cable management box 105. The power supply unit 104 includes a battery 801 (e.g., ...). Figure 28The vehicle 100 includes a power output cable (not shown) and a power output interface 106. A battery 801 is located at the front of the vehicle 101, and the power output cable connects the battery 801 and the power output interface 106. A cable management box 105 is located at the front of the vehicle 101 and is used to store the power output cable. The power output interface 106 is located on one side of the cable management box 105. By using the cable management box 105 to store the power output cable, the space occupied by the power output cable is reduced, making the layout of the front of the vehicle 101 more compact and aesthetically pleasing. Furthermore, connecting to external interfaces via the power output interface increases safety. It should be noted that the power output cable is not shown in the attached drawing because it is located inside the cable management box 105.

[0082] In some embodiments, the battery 801 may 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, with a charging time of 4-6 hours and a maximum load capacity of 1.5t. The minimum ground clearance of the battery 801 is 20mm-40mm, with a preferred value of 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 85AH of the battery 801 can support the transport vehicle 100 to move approximately 12km, or support the refueling operation of the superstructure for approximately 2 hours. In some other embodiments, the battery capacity of 210AH of the battery 801 can support the transport vehicle 100 to move approximately 25km, or support the refueling operation of the superstructure for approximately 6 hours.

[0083] exist Figure 2 In the illustrated embodiment, the power supply unit 104 includes a main power switch 107 and a power indicator light 108. Both are located on the top surface of the vehicle front 101 and are electrically connected to the battery 801. The main power switch 107 controls the on / off state of the battery 801, providing power protection for operational safety in emergencies. The power indicator light 108 indicates the operating status of the main power switch 107; for example, the indicator light 108 illuminates when the main power switch 107 is on and remains off when the main power switch 107 is off. Furthermore, the placement of the main power switch 107 and the power indicator light 108 on the top surface of the vehicle front 101 facilitates operation by personnel.

[0084] In some embodiments, the cable storage box 105 is located on the front side of the tractor unit 101 facing away from the forks 102. Since the side of the tractor unit 101 facing the forks 102 has a relatively small space where the oil pump 300 is placed on the pallet frame 200, the space is limited. Conversely, the front side of the tractor unit 101 facing away from the forks 102 faces the handlebars 103, providing more space. Placing the cable storage box 105 on this side effectively utilizes space, making the overall layout of the transport vehicle 100 more compact. In some embodiments, the cable storage box 105 includes a first storage box side 109 extending in the fork extension direction and a second storage box side 110 opposite to the first storage box side 109. A power output interface 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 interface 106 on the first storage box side 109 facilitates connection to an external power cord.

[0085] In some embodiments, the transport vehicle 100 further includes a driving warning light 111 and a charging interface 112, which are electrically connected to the battery 801. The driving warning light 111 is located on one side of the front of the vehicle 101, specifically, it is located on the side 110 of the second storage box. The driving warning light 111 is used to alert surroundings to avoid the vehicle while it is in motion. Since the power output cable of the battery 801 is stored in the cable storage box 105, placing the driving warning light 111 on the side 110 of the second storage box facilitates connection to the power output cable. Furthermore, the power output interface 106 and the driving warning light 111 are symmetrically arranged on the side 109 of the first storage box and the side 110 of the second storage box, reducing the amount of power output cable wiring and effectively utilizing the side of the cable storage box 105, making the transport vehicle 100 compact and aesthetically pleasing. The charging interface 112 is located on one side of the front of the vehicle 101 and on one side of the power supply unit 104, facilitating connection to an external power cord. In some embodiments, the charging interface 112 includes an explosion-proof socket. The explosion-proof socket offers good explosion-proof performance and high safety.

[0086] In some embodiments, the transport vehicle 100 is equipped with front wheels 113 and multiple rear wheels 114. The front wheels 113 extend downward from the lower surface of the front end 101, and the multiple rear wheels 114 extend downward from the lower surface of the forks 102, located in the area of ​​the forks 102 away from the front end 101. In this embodiment, the length of the aviation fuel tank 20 in the vertical direction is between 850mm and 900mm, with a preferred value of 890mm. The weight when fully filled with fuel can reach 150kg to 200kg, with a preferred value of 170kg. The weight when empty can reach 15kg to 20kg, with a preferred value of 19kg. According to the above data, the aviation fuel tank 20 is relatively heavy whether it is full of fuel or empty. By placing the multiple rear wheels 114 in the area of ​​the forks 102 away from the front end 101, most of the weight of the aviation fuel tank 20 can be supported, making the transportation of the aviation fuel refueling device 10 more stable.

[0087] 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 for assembly with external lifting fixtures. In this embodiment, the pallet frame 200 is rectangular, and four lifting rings 202 are provided, located at the four corners of the pallet frame 200. For example, in cases requiring refueling at a certain height or in special practical scenarios, external lifting fixtures can be connected to multiple lifting rings 202 to ensure normal refueling and expand the application scenarios. In some embodiments, the pallet frame 200 includes a stainless steel plate. Stainless steel plates are highly corrosion-resistant, conductive, explosion-proof, and highly safe. Furthermore, stainless steel plates have high hardness and are sturdy and robust.

[0088] exist Figure 3 and Figure 7 In the illustrated embodiment, the transport vehicle 100 and the pallet frame 200 are detachably assembled. In some embodiments, the transport vehicle 100 includes liftable forks 102, the forks 102 being in an upward position (e.g., Figure 3 (as shown) and the depressed state (as shown) Figure 7(As shown). In some embodiments, the pallet frame 200 is provided with a plurality of support legs 203, which extend downward from the lower surface of the pallet frame 200. When the forks 102 are in the raised state, the pallet frame 200 is lifted by the forks, and the plurality of support legs 203 are off the ground. At this time, the transport vehicle 100 can move the pallet frame 200, the oil pump device 300 and the aviation fuel tank 20 located on the pallet frame 200. When it moves to the designated location, the forks 102 switch from the raised state to the lowered state. When the forks 102 are in the lowered state, the pallet frame 200 descends, and the plurality of support legs 203 land on the ground. At this time, the plurality of support legs 203 play a supporting and fixing role, so that the transport vehicle 100, the pallet frame 200 and the oil pump device 300 located on the pallet frame 200 are fixed and do not move, thus ensuring that they are not easily moved during the refueling process and ensuring safety. In this embodiment, four support legs 203 are provided at the four corners of the pallet frame 200.

[0089] In some embodiments, the aviation fuel refueling device 10 includes a positioning component 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 located on the side of the pallet frame 200 facing the front of the vehicle 101 and extends horizontally; the positioning ring 702 is located on the side of the front of the vehicle 101, and the opening of the positioning ring 702 faces the pallet frame 200. Figures 1 to 5 In the embodiment shown, when the pallet frame 200 is assembled onto the transport vehicle 100, the positioning pin 701 is inserted into the positioning ring 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. By setting the positioning pin 701 and the positioning ring 702, the transport vehicle 100 and the pallet frame 200 can be quickly assembled and positioned. In some other embodiments, the positioning component 700 may also be a magnetic component, which is not limited in this application.

[0090] 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. Since the fuel tank 20 and the pumping device 300 are relatively heavy, placing the first roller 204 in the middle region of the pallet frame 200 allows it to support the weight of the fuel tank 20 and the pumping device 300, thus ensuring that the center of gravity of the entire fuel refueling device 10 is located in the middle region of the pallet frame 200, thereby making it more stable during movement.

[0091] In some embodiments, the first roller 204 includes an extended state and a retracted state, wherein the forks 102 are in an raised state (e.g., Figure 3When the forks 102 are in the depressed state, the first roller 204 is in the retracted state and off the ground (as shown in the diagram). When the forks 102 are in the depressed state, the first roller 204 is in the extended state and on the ground (not shown in the diagram). The pallet frame 200, by setting the retractable first roller 204, can be moved by external towing tools, thus allowing for flexible movement when the pallet trolley 100 is not set up, expanding the application scenarios.

[0092] exist Figure 8 In the illustrated embodiment, the pallet frame 200 is provided with a plurality of second rollers 205 and a plurality of brakes 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 brakes 206 include a brake position 2061 and a non-brake position 2062. When the brakes 206 are in the brake position 2061, the second rollers 205 are braked; when the brakes 206 are in the non-brake position 2062, the second rollers 205 are released from braking and can move. By providing the second rollers 205 and the corresponding brakes 206, the pallet frame 200 can be switched to the non-brake position 2062 using the brakes 206 when movement is needed, allowing the pallet frame 200 to move using the second rollers 205. When movement is not needed, the brakes 206 are switched to the brake position 2061 for braking, fixing the pallet frame 200, and then oil is added using the oil pump 300. It can be towed using external towing tools, thus allowing for flexible movement even without a transport vehicle 100, expanding its application scenarios.

[0093] In some embodiments, a plurality of rollers 205 and a plurality of brakes 206 extend downward from the lower surface of the pallet frame 200 and are distributed at the four corners of the pallet frame 200. Since the pallet frame 200 carries the aviation fuel tank 20 and the fuel pumping device 300, and its weight is relatively large, distributing the plurality of rollers 205 and the plurality of brakes 206 at the four corners of the pallet frame 200 serves two purposes: firstly, it facilitates the operation of the brakes 206 by the operator; secondly, it improves the stability of the entire aviation fuel refueling device when it is moved.

[0094] It should be noted that the switching of brake component 206 from non-brake position 2062 to brake position 2061 can be operated by personnel or controlled by other automatic components, and is not limited in this application.

[0095] exist Figures 1 to 5In the illustrated embodiment, the flow meter 303, hose reel 304, and refueling nozzle 305 are all distributed along the first direction X with the fuel tank support 201. The refueling nozzle 305 is positioned close to the fuel tank support 201 relative to the flow meter 303 and hose reel 304. The filter separator 302 is distributed side-by-side with the refueling nozzle 305 along the second direction Y. In actual use, the aviation fuel refueling device 10 is positioned close to one side of the refueling port of the general aviation equipment, and its aviation fuel tank 20 is also close to one side of the general aviation equipment. The flow meter 303 and the fuel tank support 201 are located on the same side of the first direction X, making it convenient for staff to observe the specific refueling flow rate. The hose reel 304 and the refueling nozzle 305 are located on the same side of the first direction X, making it convenient for staff to refuel the general aviation equipment. Furthermore, the required refueling coil 308 is relatively short, and winding or retracting the refueling coil 308 is simpler and more convenient.

[0096] In some embodiments, the aviation fuel refueling device 10 further includes a fixed bracket 318, which protrudes from the upper surface of the tray frame 200 and has a certain height. The fixed bracket 318 is used to fix the flow meter 303, the hose reel 304, and the refueling nozzle 305, wherein the hose reel 304 and the refueling nozzle 305 are located at the top of the fixed bracket 318. Because the aviation fuel refueling device 10 requires manual operation during refueling, placing the hose reel 304 and the refueling nozzle 305 at the top of the fixed bracket 318, so that the flow meter 303, hose reel 304, and refueling nozzle 305 have a certain height, effectively utilizes the upper space of the fixed bracket 318, and makes it more convenient and labor-saving for the operator to operate. The flow meter 303 is located on the side of the fixed bracket 318 facing away from the filter separator 302. This makes the display surface of the flow meter 303 face the operator, making it convenient for the operator to observe the flow rate of the refueling. The above height is based on the upper surface of the pallet frame 200. It can be set according to the height of the staff or the height of their hands. It is not limited in this application.

[0097] In some embodiments, the fixed bracket 318 and the fuel tank support 201 are distributed along the first direction X, and are arranged side by side with the filter separator 302 along the second direction Y. In this embodiment, the maximum diameter of the aviation fuel tank 20 is between 550mm and 600mm, with a preferred value of 580mm. The aviation fuel tank 20 occupies most of the space in the second direction Y of the pallet frame 200, while the fixed bracket 318, as well as the flow meter 303, hose reel 304, and refueling nozzle 305 located on the fixed bracket 318, also occupy a certain amount of space. If the structural layout is not compact, the aviation fuel refueling device 10 will be large in size, resulting in a large area occupied by the aviation fuel refueling device 10 and limiting its use. Therefore, in order to ensure that the pallet frame 200 and the aviation fuel refueling device 10 are smaller and more compact, the fixed bracket 318 and the fuel tank support 201 are distributed along the first direction X, and the fixed bracket 318 and the filter separator 302 are arranged side by side along the second direction Y.

[0098] In some embodiments, the bottom of the fixed bracket 318 has a receiving space 319, and the aviation fuel refueling device 10 includes a plurality of storage boxes 320 disposed within the receiving space 319. The receiving space 319 effectively utilizes the lower space of the fixed bracket 318. Furthermore, the multiple storage boxes 320 disposed within the receiving space 319 effectively store various small, handheld maintenance tools, thus enriching the storage functionality of the aviation fuel refueling device 10.

[0099] In some embodiments, the fixed bracket 318 is provided with a refueling gun limiting groove 321 (e.g. Figure 1 As shown, the fuel nozzle limiting groove 321 is located on the side of the fixed bracket 318 facing away from the filter separator 302, and the oil outlet end of the fuel nozzle 305 is engaged in the fuel nozzle limiting groove 321. The oil outlet end of the fuel nozzle 305 is the fuel inlet of the fuel nozzle 305. Engaging the fuel inlet of the fuel nozzle 305 in the fuel nozzle limiting groove 321 serves two purposes: firstly, it facilitates fixing the fuel nozzle 305 to the fixed bracket 318 for easy handling by personnel; secondly, it prevents the fuel inlet of the fuel nozzle 305 from being exposed to the outside and avoiding contamination of the fuel inlet of the fuel nozzle 305 by the external environment.

[0100] exist Figure 1 and Figure 4In the illustrated embodiment, the aviation fuel refueling device 10 also includes a static-dissipating wire reel 322, mounted on a fixed bracket 318. During refueling, the aviation fuel refueling device 10 removes the static-dissipating wire reel 322 from the fixed bracket 318. The static-dissipating wire reel 322 contains a static-dissipating wire used to quickly release static electricity from the aviation fuel refueling device. During the refueling operation, the static-dissipating wire must be reliably grounded. A static-dissipating device is provided on the working surface side of the general aviation equipment. In some embodiments, the static-dissipating wire reel 322 is located on one side of the hose reel 304 in the first direction X. This effectively utilizes the upper space of the fixed bracket 318 and facilitates access for personnel.

[0101] In some embodiments, the oil pumping device 300 further includes a connecting pipe 323 connected to the sight glass 306. The inlet end of the connecting pipe 323 is connected to the outlet end 316 of the oil pump assembly 301. The connecting pipe 323 includes a first outlet end 3231 and a second outlet end 3232. The inlet end of the sight glass 306 is connected to the first outlet end 3231, and the inlet end of the filter separator 302 is connected to the second outlet end 3232. Since the oil pump assembly 301 is detachably assembled to the aviation fuel tank 20, and the pipeline connecting it to the outlet end 316 of the oil pump 310 is detachably assembled, by providing the connecting pipe 323, at least the connecting pipe 323 connecting the oil pump 310 to the sight glass 306 and the filter separator 302 can be kept intact, only the pipeline connecting the connecting pipe 323 to the outlet end 316 of the oil pump 310 needs to be disconnected. This reduces assembly time and improves assembly efficiency.

[0102] In some embodiments, a gap exists between the fixed bracket 318 and the oil drum support 201, and the sight glass 306 and the connecting pipe 323 are disposed within this gap. This effectively utilizes the space between the fixed bracket 318 and the oil drum support 201. The sight glass 306 and the connecting pipe 323 are arranged side-by-side in the second direction Y and are located on one side of the oil drum support 201. The filter separator 302 and the connecting pipe 323 are also arranged side-by-side in the second direction Y. This results in shorter pipelines connecting the connecting pipe 323 to the sight glass 306, the oil pump 310, and the filter separator 302, leading to a more compact pipeline layout. Consequently, the aviation fuel refueling device 10 has a compact layout, smaller size, smaller footprint, and is applicable to a wider range of scenarios.

[0103] In some embodiments, the aviation fuel refueling device 10 includes a fixing rod 324 disposed on one side of the fuel tank support 201. The fixing rod 324 protrudes from the upper surface of the tray 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.

[0104] 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 also higher than the height of the sight glass 306 and the height of the fuel tank 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 sight glass 306, and the fuel tank 20. This ensures that the oil in the connecting pipe 323 is oil pumped from the fuel tank 20 by the oil pump 310, and can flow smoothly into the sight glass 306 for easy observation, rather than being oil stored in the pipeline connected to the oil outlet 316 of the oil pump 310. This ensures the normal operation of the oil pumping device 300.

[0105] In some embodiments, the first oil outlet 3231 is at a higher height than the second oil outlet 3232. Since the oil entering from the inlet of the connecting pipe 323 first enters the sight glass 306 through the first oil outlet 3231, it is only when oil is observed in the sight glass 306 that it indicates that the pipeline connected to the oil pump 310 can be normally transported. This arrangement facilitates observation and ensures the normal operation of the oil pumping device 300.

[0106] In some embodiments, the aviation fuel refueling device 10 further includes a fire extinguisher 325, assembled on the pallet frame 200, which enhances safety. In some embodiments, the fire extinguisher 325 and the fuel drum support 201 are arranged side by side along the second direction Y and located on one side of the storage bracket 500. This effectively utilizes the space of the pallet frame 200, making the components on the pallet frame 200 compact and thus reducing the size of the pallet frame 200. Furthermore, there is a distance 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 easy for workers to reach without effort.

[0107] 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 facilitates the operator's handling of the motor 311, and the location of the handle 326 on one side of the motor 311 is more ergonomic and easier for operators to use. In some embodiments, the oil pump assembly 301 also includes a handheld part 327, which is located on the pump rod 312 and above the oil outlet 316. When it is necessary to disassemble the oil pump assembly 301 from the oil outlet of the aviation fuel tank 20, the handheld part 327 facilitates disassembly. In some embodiments, the oil pump assembly 301 also includes a dust cover (not shown), located on one side of the motor 311. When the pump rod 312 is stored in the receiving tube 502, the motor 311 is located outside the receiving tube 502. In this case, the dust cover can be used to cover the motor 311, preventing it from being affected by the external environment.

[0108] In some embodiments, the fuel refueling device 10 includes a quick-release assembly 400. The fuel pump assembly 301 is detachably assembled to the fuel tank 20 via the quick-release assembly 400. Figures 1 to 5 , Figures 9 to 18 As shown, the quick-release assembly 400 includes a mounting base 401 and a sealing cap 402 detachably assembled to the mounting base 401. The mounting base 401 has a ring-shaped structure and is held in place by the fuel outlet of the fuel tank 20, with the top surface of the mounting base 401 higher than the top surface of the fuel outlet. To ensure that when the fuel pump assembly 301 is assembled to the fuel tank 20, the pump rod 312 is inserted from the mounting base 401, connected to the mounting base 401, and extends into the fuel tank 20, with the bottom of the support base 314 abutting against the top of the mounting base 401; when the fuel pump assembly 301 is not assembled to the fuel tank 20, the sealing cap 402 is assembled to the top of the mounting base 401, sealing the fuel outlet of the fuel tank 20 (e.g., ...). Figure 9 (As shown). By setting a fixing base 401 and a sealing cover 402 for the quick-release assembly 400, the fixing base 401 can quickly assemble the oil pump 310 to the oil outlet of the aviation fuel tank 20. When the oil pump 310 is not assembled to the aviation fuel tank 20, the sealing cover 402 can quickly seal the oil outlet of the aviation fuel tank 20. This quick-release structure is simple and easy to assemble. When used with the oil pump 310 and the aviation fuel tank 20, it can be easily disassembled and assembled, improving assembly efficiency.

[0109] In some embodiments, the fixing base 401 includes a first fixing part 403 and a second fixing part 404 connected to the first fixing part 403, the second fixing part 404 extending downward along the bottom of the first fixing part 403. The first fixing part 403 includes a vertically penetrating first channel 405, and the second fixing part 404 includes a vertically penetrating second channel 406, the second channel 406 communicating with the first channel 405 and forming a downward step 407 with the first channel 405. In some embodiments, a groove 408 is provided between the first fixing part 403 and the second fixing part 404, wherein the inner wall of the first channel 405 extends inward and forms the step 407 with the groove 408. The groove 408 is recessed inward from the inner peripheral wall of the fixing base 401 and communicates with the first channel 405 and the second channel 406. When the mounting base 401 is assembled onto the fuel tank 20, the fuel outlet of the fuel tank 20 is engaged within the second channel 406, and the edge of the fuel outlet of the fuel tank 20 is matched with the groove 408 for limiting, while the top of the fuel outlet of the fuel tank 20 abuts against the step 407. This assembly method is simple, and the mounting base 401 is not easily detached from the fuel outlet of the fuel tank 20. When the fuel pump assembly 301 is assembled onto the fuel tank 20, the pump rod 312 is engaged within 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 part 403 and the second fixing part 404 are integrally formed, resulting in a simple structure.

[0110] In some embodiments, the groove 408 has a first chamfer 409 on the side of the first channel 405 near the second channel 406. The first chamfer 409 is inclined from top to bottom in the direction from the outer side wall of the fixing seat 401 toward the inner side wall. The first chamfer 409 serves a guiding function, which facilitates the fixing seat 401 being fitted onto the oil outlet of the aviation fuel tank 20, and makes it less likely for the fixing seat 401 to detach from the groove 408 when it is fitted onto the oil outlet of the aviation fuel tank 20.

[0111] In some embodiments, the maximum diameter of the second channel 406 is greater than the maximum diameter of the first channel 405. Since the outlet of the fuel tank 20 is engaged within the second channel 406, and the outlet itself has a thickness, making the maximum diameter of the second channel 406 greater than the maximum diameter of the first channel 405 ensures that the inner wall of the outlet is flush with the inner wall of the first channel 405, ensuring that the pump rod 312 does not get stuck when passing through the first channel 405 and the second channel 406, and can be smoothly inserted into the fuel tank 20.

[0112] 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 part 403, and the lower edge of the flange 410 is located at the second fixing part 404. The sealing cover 402 includes a cover body 411 and a plurality of ear loops 412. The ear loops 412 extend downward from the edge of the cover body 411, and the end of the ear loop 412 away from the cover body 411 is bent inward. When the oil pump assembly 301 is not assembled to the aviation fuel tank 20, the sealing cover 402 is closed to the fixing base 401 by the limiting cooperation of the plurality of flanges 410 and the plurality of ear loops 412. In this embodiment, there are two flanges 410, and the two flanges 410 have the same oblique direction. When the sealing cap 402 is fitted onto the fixing base 401, the latches 412 of the sealing cap 402 close the gap between two adjacent flanges 410 and rotate along the extending direction of the flanges 410 from the high end to the low end (the high and low ends can be referenced to the plane containing the radial direction of the fixing base 401) to engage with the flanges 410 until the bottom end face of the flanges 410 abuts against the end face of the latches 412 opposite to the flanges 410, indicating that the sealing cap 402 is engaged with the fixing base 401. When it is necessary to remove the sealing cap 402, it can be removed from the fixing 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 dimension of the latches 412 in the horizontal direction. This arrangement facilitates easier closing of the latches 412 into the gap between two adjacent flanges 410, improving assembly efficiency.

[0113] The mounting base 401 is provided with multiple flanges 410, which serve two purposes: firstly, to limit the engagement with the ear loops 412 of the sealing cover 402, and secondly, to limit the engagement with the support base 314 provided on the pump rod 312, facilitating the assembly of the pump rod 312 and ensuring its secure fixation. In some embodiments, the edge of the support base 314 is provided with locking elements 329 (e.g., locking members 329). Figure 2 As shown), the locking member 329 can move along the axial direction of the support base 314. When the support base 314 is assembled onto the fixed base 401, the locking member 329 is operated from bottom to top along the axial direction of the support base 314, and the support base 314 is locked to the flange 410 (as shown). Figure 3 (As shown). When disassembling the oil pump assembly 301, the locking member 329 is operated from top to bottom along the axial direction of the support 314, and the support 314 is unlocked from the flange 410. This arrangement ensures that the oil pump 310 can be stably assembled at the oil outlet of the aviation fuel tank 20.

[0114] exist Figure 15 In the illustrated embodiment, the radial tilt angle of the flange 410 relative to the fixed base 401 is... The range is 2° to 6°. In some embodiments, the radial tilt angle of the flange 410 relative to the fixing base 401 is... The angle can be 2°, 3°, 4°, 5°, or 6°, with 4° being the preferred value. Setting a suitable tilt angle for the flange 410 ensures better contact between the ear clip 412 and the flange 410, resulting in better sealing of the assembly.

[0115] exist Figures 13 to 15 In the illustrated embodiment, the outer peripheral wall of the fixing base 401 is further provided with a plurality of limiting ribs 413, which extend axially along the fixing base 401 and are located above the flange 410. Figure 18 In the illustrated embodiment, the inner wall of the cover 411 is provided with a receiving groove 414. When the sealing cover 402 is assembled onto the fixing base 401, the limiting rib 413 engages with the receiving groove 414 for limiting engagement. The fixing base 401 is provided with multiple limiting ribs 413, which serve two purposes: firstly, to engage with the inner wall of the sealing cover 402 for limiting engagement, and secondly, 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 spaced apart along the circumference of the fixing base 401. In this embodiment, four limiting ribs 413 are provided and symmetrically arranged around the first fixing part 403.

[0116] exist Figure 18In the illustrated embodiment, a buffer groove 415 is provided inside the cover 411. The buffer groove 415 is located at the top of the cover 411 and communicates with the receiving groove 414. Since the flange 410 is inclined along the circumference of the fixing base 401, when the sealing cover 402 is closed on the fixing base 401, the sealing cover 402 has a certain vertical movement distance. 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 part 403 from touching the top wall of the cover 411. When the sealing cover 402 is assembled on the fixing base 401, the top of the fixing base 401 is located inside the buffer groove 415. A limiting block 416 protrudes from the inner wall of the cover 411 and is located between the buffer groove 415 and the receiving groove 414. The limiting block 416 is used to separate the buffer groove 415 and 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 side wall to the outer side wall 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 limiting block 416. The fixing base 401 is provided with a second chamfer 417 to avoid collision with the limiting block 416.

[0117] 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 tank 20 placed on the fuel tank support 201 occupies a large space, and the storage bracket 500 has 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 fuel tank support 201 are distributed along the second direction Y, so that the storage bracket 500 is located on one side of the aviation fuel tank 20. This effectively utilizes the space of the pallet frame 200 in the first direction X.

[0118] If the fuel pump assembly 301 is assembled onto the fuel tank 20 without being disassembled when refueling is not required, the height of the entire fuel refueling device 10 increases, raising its center of gravity and making it less safe to move. Furthermore, the motor 311 has a certain size and weight, and its load-bearing capacity and volume are relatively large for the entire fuel pump assembly 301, making it less safe to move and prone to misalignment with the fuel outlet of the fuel tank 20, resulting in poor fixation. In this application, however, when the fuel pump assembly 301 is not assembled onto the fuel tank 20, it is assembled onto the storage bracket 500, lowering the center of gravity of the fuel refueling device 10 and improving its stability during transport.

[0119] exist Figures 19 to 23In the illustrated embodiment, the storage bracket 500 includes a plurality of support rods 501 and a storage tube 502, with the support rods 501 extending upward from the upper surface of the pallet frame 200. The support rods 501 are spaced relative to the upper surface of the pallet frame 200. In some embodiments, the storage tube 502 is obliquely assembled to the upper end of the plurality of support rods 501 relative to the upper surface of the pallet frame 200 and extends from a second side X2 to a first side X1. The storage tube 502, extending from the second side X2 to the first side X1, effectively utilizes 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 tank 20, the pump rod 312 is housed within the storage tube 502, and the motor 311 is located outside the storage tube 502. In this configuration, the receiving tube 502 is inclined relative to the upper surface of the tray frame 200 and is at a distance from the upper surface of the tray frame 200. When the oil pump assembly 301 is assembled on the receiving bracket 500, the oil pump assembly 301 is at a certain distance from the upper surface of the tray frame 200, making it convenient for workers to handle. The pump rod 312 is housed in the receiving tube 502. Due to the accumulation of impurities over a long period of time, some of the oil in the pump rod 312 is collected in the receiving tube 502. The receiving tube 502 is inclined relative to the upper surface of the tray frame 200, which facilitates cleaning or removing the oil from the receiving tube 502. In some embodiments, multiple support rods 501 are spaced apart along the first direction X and the second direction Y, and the multiple support rods 501 are spaced apart from the second side X2 to the first side X1. In this application, there are two support rods 501, located in the middle region of the receiving tube 502. This configuration makes the force on the receiving tube 502 more balanced, resulting in better stability.

[0120] In some embodiments, the storage bracket 500 and the fuel tank support 201 are distributed along the second direction Y, and the storage tube 502 is inclined 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 to the fuel tank 20, the motor 311 and the fuel tank 20 placed on the fuel tank support 201 are distributed along the second direction Y and located on one side of the fuel tank 20, making it more convenient to retrieve the fuel pump assembly 301. Since the motor 311 has a certain size and weight, its location on the same side as the fuel tank 20 reduces the distance to retrieve it, making it more labor-saving.

[0121] In some embodiments, the receiving tube 502 includes a first receiving end 503 and a second receiving end 504 opposite to each other, wherein the first receiving end 503 and the fuel tank support 201 are distributed along a second direction Y, the first receiving end 503 is closer to the second side X2 relative to the first side X1, and the second receiving end 504 is closer to the first side X1 relative to the second side X2. When the fuel pump assembly 301 is not assembled to the fuel tank 20, the pump rod 312 extends from the first receiving end 503 to the second receiving end 504, and the motor 311 is located outside the first receiving end 503. This arrangement places the motor 311 on the same side of the fuel tank 20 placed on the fuel tank support 201, facilitating retrieval.

[0122] exist Figure 19 In the illustrated embodiment, the receiving tube 502 extends obliquely towards the fuel tank support 201 in the direction from the second side X2 to the first side X1 and in the second direction Y. Since the pump rod 312 is inserted into the aviation fuel tank 20, and the inlet end 315 of the pump rod 312 is in contact with the fuel in the aviation fuel tank 20, it indicates that the pump rod 312 has a certain length. When it is not needed to be assembled into the aviation fuel tank 20, it is housed in the receiving tube 502, giving the receiving tube 502 a certain length. The receiving tube 502 extends obliquely towards the fuel tank support 201 in the direction from the second side X2 to the first side X1 and in the second direction Y, effectively utilizing the diagonally opposite space of the pallet frame 200, making the pallet frame 200 smaller in volume, and thus making the aviation fuel refueling device 10 shorter. This allows the center of gravity of the aviation fuel refueling device 10 to be closer to the front of the vehicle 101 during transportation. In some embodiments, the receiving tube 502 is obliquely arranged relative to the vertical direction and the first direction X.

[0123] If the storage tube 502 is not tilted, the pallet frame 200 will be longer, resulting in a longer distance from the front 101 of the transport vehicle 100 to the forks 102, thus increasing the overall length and volume of the aviation fuel refueling device 10. Furthermore, the aviation fuel tank 20 has considerable weight and is located away from the front 101. With the longer pallet frame 200, the rear of the transport vehicle 100 will have a greater weight, shifting the center of gravity of the entire aviation fuel refueling device 10 further back, making it unstable during transport. Therefore, the tilted design of the storage tube 502 effectively utilizes the diagonal space of the pallet frame 200, reducing its volume and thus 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 transport.

[0124] 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 within the receiving tube 502. Due to the accumulation of impurities over a long period, some of the oil inside the pump rod 312 is collected within the receiving tube 502. The receiving tube 502 is inclined relative to the upper surface of the tray frame 200, with its first receiving end 503 higher than the second receiving end 504, which facilitates cleaning or removing the oil from the receiving tube 502.

[0125] exist Figure 21 In the embodiment shown, the angle of inclination of the storage tube 502 relative to the upper surface of the tray frame 200 is... The range is 5° to 15°. In some embodiments, the angle of inclination of the receiving tube 502 relative to the upper surface of the tray frame 200 is 5°, 7°, 9°, 10°, 13°, or 15°. Setting the inclination angle of the receiving tube 502 relative to the upper surface of the tray frame 200 appropriately makes it easier to insert the pump rod 312 into the receiving tube 502, making it more convenient for operators.

[0126] exist Figure 19 In the embodiment shown, the tilt angle of the receiving tube 502 relative to the second direction Y The range is 65° to 85°. In some embodiments, the tilt angle of the receiving tube 502 relative to the second direction Y is... The angle can be 65°, 70°, 75°, 80°, or 85°, with 77° being the preferred value. By setting an appropriate tilt angle of the receiving tube 502 relative to the second direction Y, the tray frame 200 is made smaller while still being able to accommodate the pump rod 312, thereby reducing the overall volume and footprint of the aviation fuel refueling device 10.

[0127] 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 groove structure, allowing the transport vehicle 100 and pallet frame 200 to separate when it is necessary to clean the oil in the storage tube 502, thus facilitating operator operation. In some embodiments, when the oil pump assembly 301 is not assembled to the aviation fuel tank 20, the oil inlet end 315 of the oil pump 310 is located inside the storage tube 502, close to the second storage end 504 relative to the first storage end 503, and at a distance from the plug 505. A suitable distance is set between the oil inlet end 315 of the oil pump 310 and the plug 505 to allow space for storing a certain amount of oil. This ensures that the oil collected at the second receiving end 504 does not come into contact with the oil inlet end 315 of the oil pump 310, thus reducing the amount of oil drawn from the receiving pipe 502 when the oil pump 310 is used again, preventing waste. In some embodiments, the plug 505 is made of Teflon, which is antistatic, safer, and more corrosion-resistant.

[0128] exist Figure 21 and Figure 22 In the illustrated embodiment, the storage bracket 500 includes a ring support 506, which is disposed at the first storage end 503. The ring support 506 serves a supporting function, which means that the inner sidewall of the ring support 506 supports the outer sidewall of the pump rod 312, and the end face of the ring support 506 supports the support base 314.

[0129] In some embodiments, the annular support 506 is at least attached to the inner wall and end face of the first receiving end 503. When the pump rod 312 is received in the receiving tube 502, the outer wall of the pump rod 312 is in contact with the inner wall of the annular support 506. This arrangement creates a gap 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, preventing contact friction between the outer wall of the pump rod 312 and the inner wall of the receiving tube 502 when the pump rod 312 is inserted into or withdrawn from the receiving tube 502, thus avoiding static electricity or sparks and improving safety. In some embodiments, the annular support 506 has a U-shaped cross-section and is clamped in the first receiving end 503 (e.g., Figure 23(As shown). This arrangement prevents the annular support 506 from easily detaching from the first receiving end 503 when the pump rod 312 is pulled out of the receiving tube 502. In some embodiments, when the pump rod 312 is housed in the receiving tube 502, the bottom of the support base 314 abuts against the top of the annular support 506. The bottom end face of the support base 314 fits against the top end face of the annular support 506 and engages with the inner sidewall of the annular support 506, thus improving the fixation effect of the pump rod 312 housed in the receiving tube 502.

[0130] In some embodiments, the inner diameter of the ring support 506 ranges from 50mm to 80mm. In some embodiments, the inner diameter of the ring support 506 can be 50mm, 55mm, 60mm, 65mm, 70mm, 75mm, or 80mm, with 65mm being the preferred value. Setting the inner diameter of the ring support 506 appropriately prevents static electricity or sparks from being generated due to contact friction when the pump rod 312 is inserted into or withdrawn from the receiving tube 502, thus improving safety. In some embodiments, the ring support 506 is made of Teflon. Teflon is antistatic, provides better safety, and has strong corrosion resistance.

[0131] In some embodiments, the receiving tube 502 includes a limiting protrusion 507 (such as...). Figure 22 As shown, a limiting protrusion 507 protrudes from the inner peripheral wall of the receiving tube 502. The limiting protrusion 507 is positioned closer to the second receiving end 504 than the first receiving end 503. When the pump rod 312 is housed within the receiving tube 502, the limiting protrusion 507 abuts against the pump rod 312. When the aviation fuel refueling device 10 moves, the pump rod 312 located within the receiving tube 502 is prone to contact and friction with the receiving tube 502. Therefore, this application provides a limiting protrusion 507 on the inner wall of the receiving tube 502 to prevent the pump rod 312 located within the receiving tube 502 from shaking and to avoid contact and friction with the inner wall of the receiving tube 502, which could generate static electricity or sparks.

[0132] Combination Figures 1 to 6 , Figures 24 to 27In the illustrated embodiment, the anti-tipping block 600 includes a block body 601 and a protective layer 602 covering the surface of the block body 601. The anti-tipping block 600 protrudes upwards from the upper surface of the pallet frame 200 and is located at the edge of the fuel tank support 201. The fuel tank support 201 supports the aviation fuel tank 20. Due to the large volume and weight of the aviation fuel tank 20, it may tip over during the movement of the aviation fuel refueling device 10 due to instability. Therefore, the anti-tipping block 600 with a block body 601 is provided at the edge of the fuel tank support 201 to prevent the aviation fuel tank 20 located on the fuel tank support 201 from tipping over. The protective layer 602 on the surface of the block body 601 protects the block body 601 and prevents friction between the aviation fuel tank 20 and the block body 601. Furthermore, when loading and unloading aviation fuel drum 20, the anti-tipping block 600 can play a role in positioning, fixing and buffering protection.

[0133] exist Figures 24 to 27 In the illustrated embodiment, the anti-tipping block 600 includes a plurality of columnar anti-tipping posts 603, which are spaced apart on the edge of the fuel tank support 201. In this embodiment, four anti-tipping posts 603 are provided, spaced apart on the edge of the fuel tank support 201, to prevent the aviation fuel tank 20 from tipping over in any direction. The anti-tipping block 600, with its columnar anti-tipping posts 603, has a simple structure and is easy to assemble.

[0134] In some embodiments, when the aviation fuel tank 20 is placed on the tank support 201, the maximum horizontal distance between the anti-tipping block 600 and the outer wall of the aviation fuel tank 20 ranges from 10mm to 20mm, with a preferred value of 15mm. Setting a suitable horizontal distance between the anti-tipping block 600 and the aviation fuel tank 20 ensures that the aviation fuel tank 20 is not easily in contact with or rubbed against the anti-tipping block 600 when placed on the tank support 201, thus ensuring safety.

[0135] In some embodiments, the height L1 of the stop body 601 ranges from 150mm to 200mm (e.g., Figure 25(As shown). In some embodiments, the height L1 of the stop body 601 can be 150mm, 160mm, 170mm, 180mm, 190mm, or 200mm, with a preferred value of 180mm. Since the fuel tank 20 has a large volume and weight, the height of the stop body 601 should not be too high or too low. If the height of the stop body 601 is too high, lifting the fuel tank 20 to the fuel tank support 201 will be too difficult; if the height of the stop body 601 is too low, it will not prevent the fuel tank 20 from tipping over. Therefore, setting the height of the stop body 601 appropriately can both prevent tipping and ensure that lifting the fuel tank 20 is at a moderate height and requires little effort. In some embodiments, the ratio of the height of the stop body 601 to the height of the fuel tank 20 is between 1 / 5 and 1 / 4.5, with a preferred value of 1 / 4.8. This setting, which appropriately balances the height of the block body 601 with the height of the aviation fuel tank 20, serves two purposes: preventing tipping and ensuring that the aviation fuel tank 20 is lifted to a suitable height without requiring much effort.

[0136] In some embodiments, the stop body 601 is made of stainless steel, and the pallet frame 200 includes a stainless steel plate, with the stop body 601 and the stainless steel plate connected. Stainless steel is highly corrosion-resistant, conductive, explosion-proof, and highly safe. In some embodiments, the protective layer 602 is made of Teflon. Teflon prevents mechanical friction between the aviation fuel tank 20 and the stop body 601 from easily causing sparks, thus improving safety. Teflon is also antistatic and highly corrosion-resistant.

[0137] exist Figures 24 to 27In the illustrated embodiment, the anti-tipping post 603 includes a first end 604 and a second end 605. The second end 605 includes a bottom surface and is located near the pallet frame 200, extending downwards from the upper surface of the pallet frame 200 to the bottom surface. The second end 605 has a circumferential thread 606, and the pallet frame 200 has a threaded hole (not shown) corresponding to the thread 606 and extending vertically through it. The anti-tipping post 603 is fixed to the pallet frame 200 through the engagement of the thread 606 and the threaded hole. Due to the large volume and weight of the aviation fuel tank 20, a high level of fixation is required for the anti-tipping block 600. The anti-tipping post 603 is fixed to the pallet frame 200 through the engagement of the thread 606 and the threaded hole. This fixation method is simple, and the anti-tipping post 603 is not easily loosened during the movement of the aviation fuel refueling device 10, resulting in a good fixation effect. 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. Setting the length of the second end 605 appropriately ensures that it can pass through the upper surface of the pallet frame 200 and onto the lower surface of the pallet frame 200, providing sufficient fixing length for a more secure fixation and reducing the likelihood of loosening. In some embodiments, the length L2 of the second end 605 ranges from 25mm to 35mm. In some embodiments, the length L2 of the second end 605 can be 25mm, 27mm, 29mm, 31mm, 33mm, or 35mm, with a preferred value of 30mm.

[0138] In some embodiments, the protective layer 602 has a clearance through hole 607 on its sidewall. The clearance through hole 607 is located closer to the second end 605 than the first end 604, and the block body 601 located in the clearance through hole 607 is exposed thereout. The purpose of providing the clearance through hole 607 in the protective layer 602, with the block body 601 located in the clearance through hole 607 exposed thereoutout, is to facilitate workers to use external fixing tools to fix the anti-tipping column 603 to the pallet frame 200, using the clearance through hole 607 as a fixing support surface.

[0139] In some embodiments, the vertical distance between the upper and lower edges of the clearance through-hole 607 is greater than or equal to 1 / 9 of the length of the anti-tipping post 603. Setting the vertical distance between the upper and lower edges of the clearance through-hole 607 appropriately provides a sufficient fixing support surface for full contact with external fixing tools, ensuring that the fixing tools do not easily slip off the anti-tipping post 603 when fixing it. In some embodiments, the vertical distance L3 between the upper and lower edges of the clearance through-hole 607 ranges from 15mm to 25mm (e.g., ...). Figure 25 or Figure 26 As shown), its preferred value is 20mm.

[0140] In some embodiments, the maximum diameter of the anti-tipping post 603 ranges from 28mm to 36mm. In some embodiments, the maximum diameter of the anti-tipping post 603 can be 28mm, 30mm, 32mm, 34mm, or 36mm, with 32mm being the preferred value. Setting the maximum diameter of the anti-tipping post 603 appropriately ensures that the fuel tank 20 has sufficient rigidity to prevent tipping. In some embodiments, the ratio of the maximum diameter of the anti-tipping post 603 to the maximum outer diameter of the fuel tank 20 ranges from 1 / 20 to 1 / 15, with 1 / 18 being the preferred value. Setting the ratio of the maximum diameter of the anti-tipping post 603 to the maximum outer diameter of the fuel tank 20 appropriately ensures that the anti-tipping post 603 will not damage the fuel tank 20 when it is tipped over.

[0141] In some embodiments, the thickness L4 of the protective layer 602 located on the periphery of the stop body 601 in the anti-tipping post 603 ranges from 3mm to 7mm (e.g., Figure 25 (As shown). In some embodiments, the thickness L4 of the protective layer 602 located on the peripheral wall of the stop body 601 can be 3mm, 4mm, 5mm, 6mm, or 7mm, with a preferred value of 5mm. Properly setting the thickness of the protective layer 602 on the peripheral wall of the stop body 601 can prevent the cylinder wall of the aviation fuel tank 20 from contacting and rubbing against the protective layer 602 on the peripheral wall of the stop body 601. In some embodiments, the thickness L5 of the protective layer 602 located on the top wall of the stop body 601 in the anti-tipping column 603 ranges from 5mm to 15mm (e.g., ...). Figure 25 (As shown). In some embodiments, the thickness L5 of the protective layer 602 located on the top wall of the stop body 601 can be 5mm, 7mm, 9mm, 11mm, 13mm, or 15mm, with a preferred value of 10mm. Since the fuel tank 20 is large in volume and weight, when it needs to be placed on or removed from the fuel tank support 201, the bottom of the fuel tank 20 is likely to come into contact with the top of the anti-tipping post 603 more frequently. Therefore, compared to the protective layer 602 located on the periphery of the stop body 601, the protective layer 602 located on the top wall of the stop body 601 is thicker. Setting the thickness of the protective layer 602 on the top wall of the stop body 601 appropriately ensures that it is not easily damaged, preventing the bottom wall of the fuel tank 20 from contacting the top of the stop body 601 and protecting the fuel tank 20.

[0142] 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 from top to bottom in a direction away from the central axis of the anti-tipping post 603, and 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°. Since the aviation fuel tank 20 has a large volume and weight, when it is necessary to place the aviation fuel tank 20 on the tank support 201, the first protective layer chamfer 608 on the top of the protective layer 602 serves a guiding function, facilitating the rapid placement of the aviation fuel tank 20 on the tank support 201. Furthermore, the fact that 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° provides a better guiding effect, allowing the aviation fuel tank 20 to be placed on the tank support 201 more quickly.

[0143] exist Figures 1 to 6 In the illustrated embodiment, the aviation fuel refueling device 10 includes a control box 115, which is assembled on the pallet frame 200. The control box 115 is positioned relative to the second side X2 and closer to the first side X1, and is electrically connected to the battery 801. This arrangement separates the control box 115 from the aviation fuel tank 20 placed on the tank support 201, resulting in a high safety factor. Furthermore, the control box 115 is close to the front of the vehicle 101 and near the battery 801 inside the front of the vehicle 101, facilitating connection to the battery 801, reducing the length of the power cable to the battery 801, and making the entire aviation fuel refueling device 10 more compact. Figure 28 As shown, the control box 115 is detachably connected to the battery 801. The control box 115 includes an inverter 804, and the fuel pump assembly 301 is detachably 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. With this configuration, the aviation fuel refueling device 10 does not require an external power source, making it more mobile and applicable to more scenarios. In some embodiments, the control box 115 includes an explosion-proof control box for enhanced safety.

[0144] In some embodiments, the control box 115 and the fixed bracket 318 are arranged side by side along the second direction Y, and are offset from the fuel tank support 201 in the second direction Y. The control box 115, fixed bracket 318, and fuel tank support 201 are located on the pallet frame 200, occupying a certain amount of space. If the structure is not compact, the fuel refueling device 10 will be large, resulting in a large footprint and limited usability. Therefore, to ensure a smaller size and more compact layout for the pallet frame 200 and the fuel refueling device 10, the control box 115 and the fixed bracket 318 are arranged side by side along the second direction Y.

[0145] In some embodiments, there is a gap between the control box 115 and the fixed bracket 318. When the oil pump assembly 301 is not assembled to the aviation fuel tank 20, the pump rod 312 is inserted into the receiving tube 502 from one end, and the other end of the receiving tube 502 extends between the control box 115 and the fixed bracket 318. The receiving tube 502 extends from the gap between the control box 115 and the fixed bracket 318, thus effectively utilizing the gap between the control box 115 and the fixed bracket 318. Its second receiving end 504 is positioned facing the front of the vehicle 101. When it is necessary to clean or wash the plug 505, the transport vehicle 100 can be separated from the pallet frame 200, and the plug 505 can be removed from the second receiving end 504 for easy operation by staff.

[0146] 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 201 in the second direction Y. The operation panel 116 and the storage bracket 500 are located on the same side of the tray frame 200 in the second direction Y. In some embodiments, the operation panel 116 includes an upper-mount power supply interface 117 and an oil pump power supply interface 118, and the upper-mount power supply interface 117 is pluggably electrically connected to the power output interface 106. The pluggable electrical connection facilitates disassembly and connection. In some embodiments, the upper-mount power supply interface 117 includes an explosion-proof plug. In some embodiments, the power output interface 106 includes an explosion-proof socket. By providing a pluggable connection between the explosion-proof plug and the explosion-proof socket, safety is enhanced.

[0147] In some embodiments, the power input interface 117 is positioned closer to the first side X1 than the second side X2. This closer proximity to the power output interface 106 reduces the length of the connection cable between the control box 115 and the battery 801. The fuel pump power input interface 118 is positioned closer to the second side X2 than the first side X1. This closer proximity to the fuel pump assembly 301 reduces the length of the connection cable between the fuel pump assembly 301 and the inverter 804, resulting in a more compact fuel refueling device 10.

[0148] In some embodiments, the oil pump assembly 301 includes a power input interface 330 (e.g., ...). Figure 3 As shown, the power input interface 330 and the oil pump power input interface 118 are detachably connected. This detachable connection facilitates disassembly and connection. In some embodiments, the power input interface 330 includes an explosion-proof plug. In some embodiments, the oil pump power input interface 118 includes an explosion-proof socket. The detachable connection of the explosion-proof plug and socket enhances safety.

[0149] In some embodiments, the operation panel 116 further includes a wireless remote control switch 119. The wireless remote control switch 119 can be used to stop the oil pump 310 in an emergency. The control box 115 includes a remote control indicator light 120 electrically connected to the wireless remote control switch 119, which is also electrically connected to a battery 801. The battery 801 can power the wireless remote control switch 119. The remote control indicator light 120 is located on the top surface of the control box 115. This arrangement places the remote control indicator light 120 in an easily visible position, providing convenient notification to personnel.

[0150] In some embodiments, the operation panel 116 further includes a start switch 121 and a power-on indicator light 122. The start switch 121 is positioned near the front of the vehicle 101 relative to the power-on indicator light 122, and the start switch 121 and power-on indicator light 122 are electrically connected to the inverter 804. The start switch 121 controls the connection between the inverter 804 and the oil pump assembly 301. The power-on indicator light 122 indicates the operating status of the start switch 121. When the start switch 121 is open, the inverter 804 is connected to the oil pump assembly 301, and the power-on indicator light 122 illuminates to indicate that the start switch 121 is in the open state. When the start switch 121 is closed, the inverter 804 is disconnected from the oil pump assembly 301, and the power-on indicator light 122 turns off to indicate that the start switch 121 is in the closed state.

[0151] 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. Specifically, after connecting the power input interface 117, turn on the main power switch 107, press the wireless remote control switch 119 "ON", and press the start switch 121 on the operation panel 116 of the control box 115 (for approximately 3 seconds or more). The power indicator light 122 on the operation panel 116 of the control box 115 will illuminate, indicating that the oil pump power input interface 118 is receiving power normally. Then, press the wireless remote control switch 119 "OFF". The power indicator light 122 on the operation panel 116 of the control box 115 will turn off, indicating that the oil pump power input interface 118 is de-energized, demonstrating that the emergency pump stop function of the control box 115 is normal. This test ensures that the control box 115 can achieve emergency pump stop in case of an emergency, improving safety.

[0152] Furthermore, in case of an emergency, the specific emergency procedures 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; next, retracting the anti-static cable reel 322; confirming that the support legs 203 of the pallet frame 200 are raised above the minimum safe height specified for 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 setup improves the safety of personnel and the aviation fuel refueling device 10 in case of an emergency.

[0153] Before towing the entire aviation fuel refueling unit 10, ensure that the power indicator light 122 on the control panel 116 of the control box 115 is off; raise the support legs 203 of the pallet frame 200 to above the minimum safe height specified for 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 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 fuel refueling unit 10.

[0154] In some embodiments, the pallet frame 200 is further provided with a safety signboard 207, which is distributed along with the drum support 201 in the second direction Y. The safety signboard 207 is used to indicate safety instructions to comply with safety standards.

[0155] See Figure 28 As shown, the aviation fuel refueling device 10 also includes a fuel pump power supply circuit 800, which is electrically connected to the fuel pump assembly 301. In some embodiments, the fuel 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), and the power conversion circuit 802 can convert the DC output from the battery 801 into alternating current (AC) to power the fuel pump assembly 301. During this process, the switching control circuit 803 can control the connection and disconnection between the power conversion circuit 802 and the fuel pump assembly 301. It should be noted that powering the fuel pump assembly 301 refers to powering the motor 311 in the above embodiment. When the motor 311 is energized, it can drive the fuel pump 310 to operate, thereby realizing the refueling operation.

[0156] 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. The inverter 804 converts the DC power output from the battery 801 into AC power 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. The control switch 805 is used to control the on / off connection between the inverter 804 and the battery 801. The oil pump power supply circuit 800 provides DC power through the rechargeable battery 801, and the inverter 804 converts the DC power output from the battery 801 into AC power and outputs it to power the oil pump assembly 301. The control switch 805 of the switch control circuit 803 controls the on / off connection between the inverter 804 and the battery 801. This configuration ensures the normal operation of the aviation fuel refueling device 10, and in case of an emergency, the connection between the inverter 804 and the battery 801 can be promptly cut off by the control switch 805.

[0157] In some embodiments, the control switch 805 includes a mechanical switch. The mechanical switch can be located in the control box 115 for easy operation by staff. When staff are assisting with the operation, the connection between the inverter 804 and the battery 801 can be controlled by operating the mechanical switch; this method is safe and reliable. The mechanical switch can be the main power switch 107 in the above embodiments, located on the top surface of the power supply unit 104.

[0158] exist Figure 29 In the illustrated embodiment, the control switch 805 includes an electromagnetic switch; the switch control circuit 803 further includes a remote controller 806 and a remote control circuit 807 communicating with the remote controller 806. The remote control circuit 807 is electrically connected to the electromagnetic switch and controls the on / off state of the electromagnetic switch according to the control commands from the remote controller 806. By setting an electromagnetic switch, it can be remotely controlled by the remote controller 806, and the electromagnetic switch can be turned off in a timely manner, thus enhancing safety. In some embodiments, the electromagnetic switch includes a relay, which has high sensitivity and can be turned off in a timely manner.

[0159] 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 an electromagnetic switch. The controller 810 controls the on / off state of the electromagnetic switch through the first control port 8101 based on the electrical signals output by the receiver 809. In some embodiments, the receiver 809 receives signals from the transmitter 808 that indicate an open or closed state and outputs corresponding electrical signals indicating an open or closed state. In this case, the controller 810 controls the electromagnetic switch to open or close through the first control port 8101. Compared to mechanical switches, this method allows for remote control of the oil pump assembly 301's operating state without the need for operator intervention, making it more convenient and saving manpower.

[0160] In some embodiments, transmitter 808 includes an infrared transmitter, and receiver 809 includes an infrared receiver. Communication between the infrared transmitter and receiver enables remote control, unrestricted by location or distance.

[0161] 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 through the second control port 8102 based on the electrical signal output by the receiver 809, to indicate the receiving status of the receiver 809. When the receiver 809 receives the signal transmitted by the transmitter 808 and outputs a corresponding electrical signal, the controller 810 can receive this electrical signal. At this time, the controller 810 will control the remote control indicator light 120 to indicate the receiving status of the receiver 809. This configuration facilitates prompting to personnel, avoids repeated operations, and allows observation of the transmission and reception status between the transmitter 808 and the receiver 809.

[0162] In some embodiments, the oil pump power supply circuit 800 further includes a start switch 121 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 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 between the oil pump assembly 301 and the inverter 804. It should be noted that the battery 801, inverter 804, remote control indicator light 120, start switch 121, and power-on indicator light 122 included in the oil pump power supply circuit 800 can be the aforementioned components. Figures 1 to 26 The battery 801, inverter 804, remote control indicator 120, start switch 121, and power-on indicator 122 shown in the embodiment can be referred to the above embodiment for details, and will not be repeated here.

[0163] See Figure 30 and Figure 31 The illustrated embodiment, and Figures 23 to 26 The embodiments shown are similar, with the main difference being that the anti-tipping block 900 includes multiple arc-shaped anti-tipping plates 903, which are spaced apart along the edge of the fuel tank support 201. Compared to the anti-tipping post 603, the anti-tipping plate 903 has a larger surface area, resulting in a larger contact area with the fuel tank 20 when it tipes over, thus providing a better anti-tipping effect. The top area of ​​the arc-shaped anti-tipping plate 903 is larger than that of the top of the anti-tipping post 603, providing a larger contact area with the bottom wall of the fuel tank 20 during assembly and disassembly, offering more uniform support, making it less prone to tipping over during assembly or disassembly, and, due to the larger volume and weight of the fuel tank 20, less damage to its bottom is possible.

[0164] exist Figure 30In the illustrated embodiment, the distance L6 between two adjacent anti-tipping plates 903 ranges from 50mm to 70mm. In some embodiments, the distance L6 between two adjacent anti-tipping plates 903 can be 50mm, 55mm, 60mm, 65mm, or 70mm, with 60mm being the preferred value. Figure 31 In the illustrated embodiment, the thickness L7 of the stop body 901 of the anti-tipping plate 903 ranges from 20mm to 30mm. In some embodiments, the thickness L7 of the stop body 901 of the anti-tipping plate 903 can be 20mm, 25mm, or 30mm, with a preferred value of 25mm. In some embodiments, the ratio of the thickness of the stop body 901 of the anti-tipping 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 stop body 901 in the anti-tipping plate 903 ranges from 5mm to 15mm. In some embodiments, the thickness L8 of the protective layer 902 located on the top wall of the stop body 901 can be 5mm, 7mm, 9mm, 11mm, 13mm, or 15mm, with a preferred value of 10mm. In some embodiments, the thickness L9 of the protective layer 902 located on the peripheral wall of the stop body 901 in the anti-tipping plate 903 ranges from 1mm to 5mm. The thickness L9 of the protective layer 902 located on the periphery of the stop body 901 can be 1mm, 2mm, 3mm, 4mm, or 5mm, with a preferred value of 3mm. In some embodiments, the top of the protective layer 902 is provided with a second protective layer chamfer 908, which is inclined from top to bottom from the outer sidewall of the anti-tipping plate 903 towards the inner sidewall, and the angle of inclination of the second protective layer chamfer 908 relative to the vertical direction is less than 45°. In some embodiments, a plurality of anti-tipping plates 903 are welded to the upper surface of the pallet frame 200.

[0165] See Figure 32 The illustrated embodiment, and Figure 30 The illustrated embodiment is similar, with the main difference being that the anti-tipping block 1000 includes an annular anti-tipping ring 1003 surrounding the fuel tank support (not shown). Compared to multiple arc-shaped anti-tipping plates 903, the anti-tipping ring 1003 is easier to assemble. It has a larger surface area, resulting in a larger contact area with the fuel tank 20 when it tipes over, thus providing a better anti-tipping effect, more uniform support, and making it less prone to tipping over during assembly or disassembly of the fuel tank 20.

[0166] In some embodiments, the anti-tipping ring 1003 is welded to the upper surface of the pallet frame 200. In some embodiments, the top of the protective layer is provided with a third protective layer chamfer 1008, which is inclined from top to bottom from the outer sidewall of the anti-tipping ring 1003 toward the inner sidewall, and the angle of inclination of the third protective layer chamfer 1008 relative to the vertical direction is less than 45°.

[0167] See Figure 33 The illustrated embodiment, and Figures 1 to 5 The embodiments shown are similar, with the main difference being that the fuel tank support 201 is positioned closer to the first side X1 than the second side X2. This arrangement brings the center of gravity of the entire aviation fuel refueling device 10 closer to the front of the vehicle 101, resulting in better stability during movement.

[0168] The technical solutions disclosed in the various embodiments of this application can complement each other without causing conflict.

[0169] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of protection of this application.

Claims

1. An aviation fuel refueling device, characterized in that, include: Pallet frame, a support structure for carrying aviation fuel drums; Storage bracket, assembled onto the tray frame; The storage bracket includes multiple support rods and a storage tube. The support rods extend upward from the upper surface of the tray frame, and the storage tube is assembled at an angle to the upper end of the multiple support rods relative to the upper surface of the tray frame. and An oil pump assembly is assembled on the pallet frame; the oil pump assembly is detachably assembled with the aviation fuel tank to extract oil from the aviation fuel tank; wherein the oil pump assembly includes an oil pump and a motor driven by the oil pump, the oil pump includes a pump rod, and when the oil pump assembly is not assembled with the aviation fuel tank, the pump rod is housed in the receiving tube, and the motor is located outside the receiving tube; The storage bracket includes a ring-shaped support member; the oil pump assembly also includes a support base, which is disposed on the pump rod, and when the pump rod is housed in the storage tube, the bottom of the support base abuts against the top of the ring-shaped support member; The aviation fuel refueling device includes a quick-release assembly; the fuel pump assembly is detachably assembled to the aviation fuel tank via the quick-release assembly; the quick-release assembly includes a mounting base and a sealing cap detachably assembled to the mounting base; The fixing seat has a ring structure and is held in place at the oil outlet of the aviation fuel tank. The top surface of the fixing seat is higher than the top surface of the oil outlet. When the fuel pump assembly is assembled into the fuel tank, the pump rod is inserted into the mounting base, connected to the mounting base, and extends into the fuel tank, with the bottom of the support base abutting against the top of the mounting base; when the fuel pump assembly is not assembled into the fuel tank, the sealing cap is assembled into the top of the mounting base to seal the fuel tank outlet. The fixing base includes a first fixing part and a second fixing part connected to the first fixing part, the second fixing part extending downward along the bottom of the first fixing part; wherein, the first fixing part includes a first channel that runs vertically through the base, the second fixing part includes a second channel that runs vertically through the base, the second channel communicates with the first channel and forms a downward step with the first channel; A groove is provided between the first fixing part and the second fixing part, wherein the inner wall of the first channel extends inward and forms the step with the groove; the groove is recessed inward from the inner peripheral wall of the fixing seat and communicates with the first channel and the second channel; When the mounting base is assembled onto the aviation fuel tank, the fuel outlet of the aviation fuel tank is engaged within the second channel, and the edge of the fuel outlet of the aviation fuel tank is matched with the groove for limiting, and the top of the fuel outlet of the aviation fuel tank abuts against the step.

2. The aviation fuel refueling device according to claim 1, characterized in that, The pallet frame extends along a first direction and a second direction, the first direction and the second direction are in the same horizontal plane, the second direction is perpendicular to the first direction, the storage bracket and the oil drum support are distributed along the second direction, and the storage tube is inclined relative to the upper surface of the pallet frame and the second direction.

3. The aviation fuel refueling device according to claim 2, characterized in that, The pallet frame includes a first side and a second side opposite to each other in the first direction; the storage tube includes a first storage end and a second storage end opposite to each other, wherein the first storage end and the oil drum support are distributed along the second direction, the first storage end is closer to the second side relative to the first side, and the second end is closer to the first side relative to the second side. When the oil pump assembly is not assembled into the aviation fuel tank, the pump rod extends from the first receiving end to the second receiving end, and the motor is located outside the first receiving end; the first receiving end is higher than the second receiving end.

4. The aviation fuel refueling device according to claim 3, characterized in that, The receiving tube extends obliquely in the direction from the second side to the first side, and in the second direction toward the direction of the oil drum support.

5. The aviation fuel refueling device according to claim 4, characterized in that, The aviation fuel refueling device includes a transport vehicle, which includes a cab and forks extending from the cab along a first direction. The cab is located on the first side, and the forks support the pallet frame.

6. The aviation fuel refueling device according to claim 2, characterized in that, The angle of inclination of the storage tube relative to the upper surface of the tray frame is in the range of 5° to 15°; and / or The tilt angle of the storage tube relative to the second direction is in the range of 65°~85°; and / or The plurality of support rods are spaced apart along the first direction and the second direction.

7. The aviation fuel refueling device according to claim 3, characterized in that, The storage bracket includes a plug, which is detachably assembled to the second storage end to seal the second storage end.

8. The aviation fuel refueling device according to claim 7, characterized in that, The oil pump includes an oil inlet end located on the pump rod away from the motor. When the oil pump assembly is not assembled into the aviation fuel tank, the oil inlet end is located inside the receiving pipe, closer to the second receiving end relative to the first receiving end, and at a distance from the plug; and / or The plug is made of Teflon.

9. The aviation fuel refueling device according to claim 3, characterized in that, The ring support is disposed at the first receiving end and is at least attached to the inner wall and end face of the first receiving end. When the pump rod is received in the receiving tube, the outer wall of the pump rod is attached to the inner wall of the ring support, and there is a gap between the outer wall of the pump rod and the inner wall of the receiving tube.

10. The aviation fuel refueling device according to claim 9, characterized in that, The oil pump includes an oil inlet end located away from the motor and an oil outlet end located near the motor; the support base is located between the oil inlet end and the oil outlet end, and is located closer to the oil outlet end than the oil inlet end; when the pump rod is housed in the receiving tube, the bottom of the support base abuts against the top of the annular support member.

11. The aviation fuel refueling device according to claim 10, characterized in that, The inner diameter of the ring support is in the range of 50mm to 80mm; and / or The material of the annular support is Teflon; and / or The ring support has a U-shaped cross-section and is clamped at the first receiving end.

12. The aviation fuel refueling device according to claim 3, characterized in that, The oil pump includes an oil inlet end located away from the motor and an oil outlet end located near the motor on the pump rod; The receiving tube includes a limiting protrusion that protrudes from the inner peripheral wall of the receiving tube and is positioned closer to the second receiving end relative to the first receiving end; when the pump rod is received within the receiving tube, the limiting protrusion abuts against the pump rod; and / or The oil pump assembly also includes a motor handle located on one side of the motor; and / or The oil pump assembly further includes a handle, which is disposed on the pump rod and located above the oil outlet end; and / or The oil pump assembly also includes a dust cover, which is located on one side of the motor.

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