阅读说明：本技术 航油加油装置 (Aviation fuel filling device ) 是由 张序洋 陈培 王雷 李雪枫 于 2021-07-30 设计创作，主要内容包括：本申请提供一种航油加油装置,包括托盘构架、泵油装置和防倾倒挡块。托盘构架包括用于承载航油油桶的油桶支撑部。泵油装置组装于托盘构架,泵油装置包括油泵组件,油泵组件用于与航油油桶可拆卸地组装,抽取航油油桶中的油品。防倾倒挡块包括挡块主体和覆盖于挡块主体表面的防护层；其中防倾倒挡块向上凸设于托盘构架的上表面,且位于油桶支撑部的边缘。如此设置,在油桶支撑部的边缘设置防倾倒挡块,在航油加油装置运输过程中,防倾倒挡块可防止设于油桶支撑部的航油油桶倾倒,防倾倒挡块的挡块主体用以防止设于油桶支撑部的航油油桶倾倒,其设于挡块主体的表面的防护层用以保护挡块主体,避免航油油桶与挡块主体发生摩擦。(The application provides a fuel filling device by plane, including tray framework, oil pumping device and anti-overturning dog. The tray framework is including being used for bearing the oil drum supporting part of boat oil drum. The oil pumping device is assembled on the tray framework and comprises an oil pump assembly, and the oil pump assembly is used for being detachably assembled with the aviation oil barrel and pumping oil in the aviation oil barrel. The anti-toppling check block comprises a check block main body and a protective layer covering the surface of the check block main body; wherein prevent empting the dog and upwards protruding the upper surface of locating the tray framework, and be located the edge of oil drum supporting part. According to the arrangement, the anti-dumping check block is arranged at the edge of the oil drum supporting part, the anti-dumping check block can prevent the aviation oil drum arranged on the oil drum supporting part from dumping in the transportation process of the aviation oil refueling device, the check block main body of the anti-dumping check block is used for preventing the aviation oil drum arranged on the oil drum supporting part from dumping, the protective layer arranged on the surface of the check block main body is used for protecting the check block main body, and the aviation oil drum is prevented from rubbing with the check block main body.)

1. A aviation fuel filling device, comprising:

the tray framework comprises an oil drum supporting part for bearing an oil drum of the aviation oil;

an oil pumping device assembled to the tray frame; and

the anti-toppling check block comprises a check block main body and a protective layer covering the surface of the check block main body; wherein the anti-toppling stop block is upwards convexly arranged on the upper surface of the tray framework and is positioned at the edge of the oil drum supporting part.

2. The marine oil refueling device as recited in claim 1, wherein the anti-toppling stopper comprises a plurality of cylindrical anti-toppling pillars spaced apart from the edge of the oil drum supporting portion.

3. The marine oil refueling unit of claim 2 wherein the anti-tipping column includes opposing first and second ends, the second end including a bottom end surface, the second end being one end proximate the tray frame, and the second end extending downwardly from the upper surface of the tray frame to the bottom end surface;

the periphery of the second end is provided with threads, the tray framework is provided with threaded holes which correspond to the threads and are vertically communicated, and the anti-toppling column is fixed on the tray framework through the matching of the threads and the threaded holes; and/or

1/6 where the length of the second end is greater than or equal to the length of the anti-tipping post; and/or

The length of the second end ranges from 25mm to 35 mm.

4. The marine oil refueling unit of claim 2 wherein the anti-tipping column includes opposing first and second ends, the second end including a bottom end surface, the second end being one end proximate the tray frame, and the second end extending downwardly from the upper surface of the tray frame to the bottom end surface; the side wall of the protective layer is provided with a abdicating through hole, the abdicating through hole is arranged closer to the second end relative to the first end, and the check block body positioned in the abdicating through hole is exposed out of the abdicating through hole;

the vertical distance between the upper edge and the lower edge of the abdicating through hole is greater than or equal to 1/9 of the length of the anti-toppling column; and/or

The vertical distance range between the upper edge and the lower edge of the abdicating through hole is 15 mm-25 mm.

5. The marine oil refueling unit as recited in claim 2 wherein the maximum diameter of the anti-toppling post ranges from 28mm to 36 mm; and/or

The ratio range of the maximum diameter of the anti-toppling column to the maximum outer diameter of the aviation oil drum is 1/20-1/15; and/or

The thickness range of the protective layer positioned on the peripheral wall of the stop block main body is 3-7 mm; and/or

The thickness range of the protective layer positioned on the top wall of the block main body is 5-15 mm; and/or

The top of inoxidizing coating is equipped with first chamfer, first chamfer from the top down to keeping away from the direction slope of preventing the center pin of toppling over the post, first chamfer for prevent the angle of toppling over the center pin slope of post is less than 45.

6. The marine oil refueling device as recited in claim 1, wherein the anti-tipping stop comprises a plurality of arc-shaped anti-tipping plates spaced apart from the edge of the oil drum supporting portion.

7. The marine oil refueling device as recited in claim 6, wherein the distance between two adjacent anti-tipping plates is in a range of 50mm to 70 mm; and/or

The thickness range of the stop block main body of the anti-toppling plate is 20-30 mm; and/or

The proportion range of the thickness of the stop block main body of the anti-toppling plate to the thickness of the aviation oil drum is 15-20; and/or

The thickness range of the protective layer positioned on the top wall of the block main body is 5-15 mm; and/or

The thickness range of the protective layer positioned on the peripheral wall of the stop block main body is 1 mm-5 mm; and/or

The top of the protective layer is provided with a second chamfer, the second chamfer inclines from the outer side wall of the anti-toppling plate to the inner side wall from top to bottom, and the inclination angle of the second chamfer relative to the vertical direction is less than 45 degrees; and/or

A plurality of the anti-toppling panels are welded to an upper surface of the tray frame.

8. The marine oil refueling unit as recited in claim 1 wherein the anti-tip stop comprises an annular anti-tip ring surrounding the oil drum support portion.

9. The marine oil refueling unit as recited in claim 8 wherein the anti-tip over ring is welded to an upper surface of the tray frame; and/or

The top of inoxidizing coating is equipped with the third chamfer, the third chamfer is followed from top to bottom the lateral wall that prevents empting the ring inclines to the inboard wall direction, the angle that the third chamfer inclines for vertical direction is less than 45.

10. The marine oil refueling device as recited in claim 1 wherein a maximum horizontal distance between the anti-tip stop and an outer side wall of the marine oil drum is in a range of 10mm to 20mm when the marine oil drum is placed on the drum support portion; and/or

The height range of the stop block main body is 150 mm-200 mm; and/or

The proportion range of the height of the block main body to the height of the aviation oil barrel is 1/5-1/4.5; and/or

The tray frame comprises a tray frame and a stop block main body, wherein the stop block main body is made of stainless steel, the tray frame comprises a stainless steel plate, and the stop block main body is connected with the stainless steel plate; and/or

The protective layer is made of Teflon.

Technical Field

The application relates to the technical field of aviation fuel filling, in particular to an aviation fuel filling device.

Background

With the rapid development of economy in China, the aviation industry is also greatly developed. In recent years, as countries gradually start to release low-altitude areas and encourage the development of general aviation in policy, it is urgent to enhance fueling services for general aviation equipment.

Disclosure of Invention

The application provides a prevent aviation fuel filling device that aviation fuel oil barrel emptys.

The embodiment of the application provides a fuel filling device by plane, includes:

the tray framework comprises an oil drum supporting part for bearing an oil drum of the aviation oil;

an oil pumping device assembled to the tray frame; and

the anti-toppling check block comprises a check block main body and a protective layer covering the surface of the check block main body; wherein the anti-toppling stop block is upwards convexly arranged on the upper surface of the tray framework and is positioned at the edge of the oil drum supporting part.

Optionally, the anti-toppling stopper includes a plurality of column anti-toppling posts, and a plurality of the anti-toppling posts are distributed at intervals on the edge of the oil drum supporting portion.

Optionally, the anti-toppling column comprises first and second opposite ends, the second end comprising a bottom end face, the second end being the end adjacent to the tray frame, and the second end extending downwardly from the upper surface of the tray frame to the bottom end face;

optionally, the second end is circumferentially provided with threads, the tray frame is provided with threaded holes corresponding to the threads and penetrating up and down, and the anti-toppling column is fixed to the tray frame through the matching of the threads and the threaded holes.

Optionally, the length of the second end is greater than or equal to 1/6 of the length of the anti-tipping post.

Optionally, the length of the second end ranges from 25mm to 35 mm.

Optionally, the anti-toppling column comprises first and second opposite ends, the second end comprising a bottom end face, the second end being the end adjacent to the tray frame, and the second end extending downwardly from the upper surface of the tray frame to the bottom end face; the lateral wall of inoxidizing coating is equipped with the through-hole of stepping down, the through-hole of stepping down for first end is closer to the second end sets up, is located the through-hole of stepping down the dog main part expose in the through-hole of stepping down.

Optionally, the vertical distance between the upper and lower edges of the abdicating through-hole is greater than or equal to 1/9 of the length of the anti-tipping post.

Optionally, the vertical distance between the upper edge and the lower edge of the abdicating through hole ranges from 15mm to 25 mm.

Optionally, the maximum diameter of the anti-toppling column ranges from 28mm to 36 mm.

Optionally, the ratio range of the maximum diameter of the anti-tipping column to the maximum outer diameter of the aviation oil drum is 1/20-1/15.

Optionally, the thickness of the protective layer on the circumferential wall of the block main body ranges from 3mm to 7 mm.

Optionally, the thickness of the protective layer on the top wall of the block main body ranges from 5mm to 15 mm.

Optionally, a first chamfer is arranged at the top of the protective layer, the first chamfer is inclined from top to bottom in a direction away from the central axis of the anti-toppling column, and the inclination angle of the first chamfer relative to the central axis of the anti-toppling column is less than 45 °.

Optionally, the anti-toppling stopper includes a plurality of arc-shaped anti-toppling plates, and a plurality of anti-toppling plates are distributed at intervals on the edge of the oil drum supporting portion.

Optionally, the distance between two adjacent anti-toppling plates is in a range of 50mm to 70 mm.

Optionally, the thickness of the stopper body of the anti-toppling plate ranges from 20mm to 30 mm.

Optionally, the proportion range of the thickness of the stop block main body of the anti-toppling plate to the thickness of the aviation oil drum is 15-20.

Optionally, the thickness of the protective layer on the top wall of the block main body ranges from 5mm to 15 mm.

Optionally, the thickness of the protective layer on the circumferential wall of the block main body ranges from 1mm to 5 mm.

Optionally, the top of inoxidizing coating is equipped with the second chamfer, the second chamfer from top to bottom the lateral wall that prevents the board that topples to the inside lateral wall direction slope, the angle that the second chamfer inclines for vertical direction is less than 45.

Optionally, a plurality of the anti-toppling panels are welded to the upper surface of the tray frame.

Optionally, the anti-toppling stopper includes an annular anti-toppling ring that surrounds the oil drum supporting portion.

Optionally, the anti-tipping ring is welded to the upper surface of the tray frame.

Optionally, a third chamfer is arranged at the top of the protective layer, the third chamfer inclines from top to bottom from the outer side wall of the anti-toppling ring to the inner side wall, and the inclination angle of the third chamfer relative to the vertical direction is less than 45 °.

Optionally, when the aviation oil drum is arranged in the oil drum supporting part, the maximum horizontal distance range between the anti-toppling stop block and the outer side wall of the aviation oil drum is 10 mm-20 mm.

Optionally, the height of the stopper body ranges from 150mm to 200 mm.

Optionally, the ratio range of the height of the block main body to the height of the aviation oil barrel is 1/5-1/4.5.

Optionally, the stopper main body is made of stainless steel, the tray frame includes a stainless steel plate, and the stopper main body is connected to the stainless steel plate.

Optionally, the protective layer is made of teflon.

The utility model provides a boat oil filling device sets up at the edge of oil drum supporting part and prevents empting the dog, and in the boat oil filling device transportation, prevent empting the dog and can prevent to locate the boat oil drum of oil drum supporting part and empty, prevent empting the dog main part of dog and be used for preventing to locate the boat oil drum of oil drum supporting part and empty, its inoxidizing coating of locating the surface of dog main part is used for protecting the dog main part, avoids boat oil drum and dog main part to take place the friction.

Drawings

Fig. 1 is a schematic structural diagram illustrating an embodiment of an oil pump assembly of the aviation fuel filling apparatus of the present application assembled in an aviation fuel tank;

FIG. 2 is a schematic view of another perspective of the marine fuel loading unit of FIG. 1;

FIG. 3 is a schematic view of the marine fuel loading unit of FIG. 1 from a further perspective;

FIG. 4 is a schematic illustration of a further perspective view of the marine fuel loading unit of FIG. 1;

FIG. 5 is a schematic view of the marine fuel loading unit of FIG. 1 from another perspective;

FIG. 6 is a schematic structural diagram illustrating an embodiment of the aviation fuel filling apparatus of the present application in which the fuel pump assembly is not mounted on the aviation fuel tank;

FIG. 7 is a schematic structural view of one embodiment of the present disclosure with a cart separated from a tray frame, wherein the oil pump assembly is not assembled to a aviation oil drum;

FIG. 8 is a schematic structural view of another embodiment of a tray frame of the marine fuel loading system of the present application;

FIG. 9 is a schematic cross-sectional view of an embodiment of a quick release assembly of the present disclosure assembled to a aviation fuel drum, wherein the fuel pump assembly is not assembled to the aviation fuel drum;

FIG. 10 is a schematic illustration of a quick release assembly of an embodiment of the subject disclosure;

FIG. 11 is a cross-sectional view of a quick release assembly of the marine fuel loading system of FIG. 10;

FIG. 12 is a cross-sectional view of one perspective of a quick release assembly of the marine fuel loading system of FIG. 10;

FIG. 13 is a schematic cross-sectional view of another perspective of a quick release assembly of the marine fuel loading system of FIG. 10;

FIG. 14 is a schematic structural view of an embodiment of a quick release assembly mounting base of the marine oil refueling apparatus shown in FIG. 10;

FIG. 15 is a front view of the quick release assembly fastening base of the marine oil refueling apparatus shown in FIG. 14;

FIG. 16 is a cross-sectional view of a quick release assembly mounting base of the marine fuel loading apparatus shown in FIG. 14;

FIG. 17 is a schematic view of a seal cover of the quick release assembly of the marine fuel loading system of FIG. 10;

FIG. 18 is a schematic cross-sectional view of a seal cap of the quick release assembly of the marine fuel filling apparatus shown in FIG. 17;

FIG. 19 is a schematic top view of a portion of the structure of the marine fuel loading unit of FIG. 1;

FIG. 20 is a schematic structural view showing a perspective view of a portion of the structure of the marine fuel loading unit shown in FIG. 19;

FIG. 21 is a schematic structural view showing another perspective of a portion of the structure of the marine fuel loading unit shown in FIG. 19;

FIG. 22 is a schematic view of the oil pump assembly of the marine oil refueling unit shown in FIG. 19 being received in the receiving bracket;

FIG. 23 is a schematic view of the structure of the storage bracket A of the marine oil refueling device shown in FIG. 22;

FIG. 24 is a schematic view of a perspective view of an anti-tip-over stop for the marine fuel loading unit of FIG. 1;

FIG. 25 is a schematic cross-sectional view of the anti-tip over stop of the marine fuel loading unit of FIG. 24;

FIG. 26 is a schematic view of another perspective of the anti-tip over stop of the marine fuel loading unit of FIG. 1;

FIG. 27 is a schematic cross-sectional view of the anti-tip over stop of the marine fuel filling apparatus of FIG. 26;

FIG. 28 is a schematic block diagram of an oil pump power supply circuit of the marine oil refueling unit shown in FIG. 1;

FIG. 29 is a schematic block diagram of a switching control circuit of the oil pump power supply circuit shown in FIG. 28;

FIG. 30 is a schematic structural view of another embodiment of an anti-tip-off stop for a marine fuel filling apparatus according to the present application;

FIG. 31 is a schematic cross-sectional view of another embodiment of an anti-tip back stop for the marine fuel filling apparatus shown in FIG. 30;

FIG. 32 is a schematic structural view of yet another embodiment of an anti-tip-off stop for a marine fuel filling apparatus according to the present application;

fig. 33 is a schematic structural view showing a further embodiment of an anti-toppling stopper of the aviation fuel filling apparatus of the present application.

Detailed Description

Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present application. Rather, they are merely examples of apparatus consistent with certain aspects of the present application, as detailed in the appended claims.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. Unless otherwise defined, technical or scientific terms used herein shall have the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The use of the terms "a" or "an" and the like in the description and in the claims of this application do not denote a limitation of quantity, but rather denote the presence of at least one. "plurality" includes two, and is equivalent to at least two. The word "comprising" or "comprises", and the like, means that the element or item listed as preceding "comprising" or "includes" covers the element or item listed as following "comprising" or "includes" and its equivalents, and does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, but may include electrical connections, whether direct or indirect. As used in this specification and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

The application embodiment provides a fuel filling device that sails by plane, including tray framework, oil pumping device and anti-overturning dog. The tray framework is including being used for bearing the oil drum supporting part of boat oil drum. The oil pumping device is assembled on the tray framework. The anti-toppling check block comprises a check block main body and a protective layer covering the surface of the check block main body; wherein prevent empting the dog and upwards protruding the upper surface of locating the tray framework, and be located the edge of oil drum supporting part.

According to the arrangement, the anti-dumping check block is arranged at the edge of the oil drum supporting part, the anti-dumping check block can prevent the aviation oil drum arranged on the oil drum supporting part from dumping in the transportation process of the aviation oil refueling device, the check block main body of the anti-dumping check block is used for preventing the aviation oil drum arranged on the oil drum supporting part from dumping, the protective layer arranged on the surface of the check block main body is used for protecting the check block main body, and the aviation oil drum is prevented from rubbing with the check block main body.

The application provides a fuel filling device sails. The aviation fuel filling device of the present application will be described in detail below with reference to the accompanying drawings. The features of the following examples and embodiments may be combined with each other without conflict.

The aviation fuel filling device 10 can provide aviation fuel filling service for general aviation equipment parked on an airplane runway and/or an airplane apron, and can also provide aviation fuel filling service for general aviation equipment parked in earthquake regions, mountain areas and other severe geographic environments. The aviation fuel can be aviation gasoline or aviation kerosene, which is called aviation fuel for short.

As shown in fig. 1 to 6, the marine oil refueling apparatus 10 includes a truck 100, a tray frame 200, an oil pumping device 300, a storage bracket 500, and an anti-toppling stopper 600.

Specifically, the truck 100 includes a head 101 and a fork 102, the fork 102 is connected to the head 101 and extends along the head 101 toward the tail, and the fork 102 is configured to support the pallet frame 200. Wherein the vehicle rear is referred to as being opposite the vehicle front 101 and extending from the vehicle front 101 in a direction away from the vehicle front 101. In some embodiments, the head 101 is further provided with a handle 103 for a worker to hold, and the handle 103 controls the moving direction of the transportation vehicle 100 for the worker to use.

In some embodiments, the tray frame 200 includes an oil drum support 201 for carrying the aviation oil drum 20. Aviation oil drum 20 accessible outside oil drum carrier carries out manual loading and unloading and changes, and this mode is simple easily to be operated, and economy is suitable for. The oil pumping device 300, the storage bracket 500, and the anti-toppling stopper 600 are provided on (assembled to) the tray frame 200, and the oil pumping device 300, the storage bracket 500, and the anti-toppling stopper 600 are carried on the upper surface of the tray frame 200. In some embodiments, the tray 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 (as shown in fig. 1). In the embodiment shown in fig. 1, the tray frame 200 may be a rectangular plate, and the first direction X may be an extending direction of a long side of the rectangular plate, and the second direction Y may be an extending direction of a short side of the rectangular plate.

In some embodiments, the pallet frame 200 includes a first side X1 and a second side X2 opposite in the first direction X, the first side X1 facing the vehicle head 101, the second side X2 being away from the vehicle head 101, the oil drum support 201 being disposed proximate to the second side X2 relative to the first side X1. In some embodiments, the forks 102 extend in a first direction X from the head 101, the head 101 being located on a first side X1. So set up, make and place in the aviation oil drum 20 and the locomotive 101 of oil drum supporting part 201 and separate, and keep away from locomotive 101, increase the security.

The aviation fuel filling device 10 is used for filling general aviation equipment by a gravity fuel filling mode. The gravity refueling refers to a mode of filling the aviation oil from the oil outlet of the aviation oil drum 20 into the general aviation equipment by means of the weight of the aviation oil. The refueling efficiency can be accelerated by means of the oil pumping device 300. In some embodiments, oil pumping device 300 includes an oil pump assembly 301, a filter separator 302, a flow meter 303, a hose reel 304, an oil gun 305, and an oil viewer 306. Wherein, oil pump assembly 301 detachably is assembled in aviation oil drum 20 for the oil in the pumping aviation oil drum 20. The oil inlet end of the filter separator 302 is communicated with the oil outlet end of the oil pump assembly 301. The oil inlet end of the flow meter 303 is communicated with the oil outlet end of the filtering separator 302. The oil inlet end of the rubber hose reel 304 is communicated with the oil outlet end of the flowmeter 303. The oil inlet end of the oil gun 305 communicates with the oil outlet end of the hose reel 304. The oil inlet end of the oil viewer 306 is communicated with the oil outlet end of the oil pump assembly 301. When the aviation oil flows through the filtering separator 302, solid particles and impurities in the aviation oil are filtered by the filter element, moisture in the aviation oil is separated, and the moisture which is sunk to the bottom of the filtering separator 302 can be manually discharged. The filter separator 302 meets the requirements of 5 μm of filter precision or GB/T21358-. And the filtering separator 302 must be checked before each use of the oil pumping device 300 to ensure safety. The flowmeter 303 is used for recording and displaying the flow of the added aviation oil, wherein the metering precision of the flowmeter 303 is +/-0.2%, and the metering is accurate.

In some embodiments, the hose reel 304 includes a reel bracket 307, a refueling coil 308 disposed on the reel bracket 307, and a coil turner 309. Wherein the fuel gun 305 communicates with the flow meter 303 through the fuel fill coil 308. Through operating the coil pipe turning hand 309, the reel bracket 307 is rotated to drive the oiling coil pipe 308 to be rolled out from the reel bracket 307 or the oiling coil pipe 308 is retracted to the oiling coil pipe bracket 307, so that the structure of the whole oil pumping device 300 is ensured to be compact, and the occupied area is reduced. In some embodiments, the refueling coil 308 may be hand-wound or spring-wound. In some embodiments, the gravity fueling rated flow of the fueling coil 308 may be up to 25L/min, the fueling coil 308 may be 20mm to 40mm, with a preferred value of 30mm, and the length of the fueling coil 308 may be up to 15 m. In some embodiments, the oil viewer 306 may observe whether oil (clean or contaminated) in the filler line passes through the filler coil 308 to the gun 305 to ensure that the oil is successfully dispensed.

In some embodiments, the coil pipe turning hand 309 is disposed on a side of the coil pipe bracket 307 facing away from the oil drum supporting portion 201 in the first direction X. When refueling, the refueling coil 308 needs to be rolled out by operating the coil turning hand 309, and the coil turning hand 309 is arranged on one side of the reel bracket 307 facing the vehicle head 101 and at least partially positioned right above the vehicle head 101. The operation of staff is convenient. And the lowest point of rotation of the coil turner 309 is above the top surface of the locomotive 101. So that the top surface of the vehicle head 101 is not easy to touch when the worker operates, and the use of the worker is facilitated. In some embodiments, the grease gun 305 is disposed on the side of the spool bracket 307 facing away from the coil turner 309 in the first direction X. The oil gun 305 and the coil pipe turning hand 309 are arranged on two sides of the coil pipe bracket 307, so that the side space of the coil pipe bracket 307 is effectively utilized, the structure of the aviation oil refueling device 10 is compact, and the operation of workers is convenient.

In the embodiment shown in fig. 1 to 5, when the oil pump assembly 301 is assembled in the aviation oil drum 20, the oil inlet end of the oil pump assembly 301 extends into the aviation oil drum 20 and contacts with the oil in the aviation oil drum 20. Because the aviation gasoline is low flash point fuel, the oil inlet end of the oil pump assembly 301 extends into the aviation gasoline barrel 20 and is fully contacted with the aviation gasoline, the mode can avoid the contact of the oil inlet end of the oil pump assembly 301 with air, avoid the generation of sparks and has higher safety. Compared with the related technology of using the oil pump with the self-suction function, the embodiment of the application can avoid the phenomena of air resistance and cavitation erosion of the oil pump assembly 301 caused by oil gas generated by air pressure. In the embodiment shown in fig. 6, the oil pump assembly 301 is placed on the tray frame 200 when it is not assembled to the aviation oil drum 20. When needing to refuel, assemble oil pump assembly 301 in aviation oil drum 20, when not needing to refuel, place oil pump assembly 301 on tray framework 200. So at the operation in-process, can conveniently give aviation equipment with the oil filling in the aviation oil drum 20, oil pump assembly can take off from the aviation oil drum, can change another bucket of oil when oil in the aviation oil drum runs out or basically used up, the operation mode is nimble, high durability and convenient use, and whole aviation oil filling device makes and to utilize the aviation oil drum to refuel, so can be applicable to the refueling of general aviation equipment, aviation oil filling device can be more miniaturized, can adapt to some harsher geographical environment, for example, can be used for the refueling of general aviation equipment under the rescue environment.

In addition, when oil filling is not needed, the oil pump assembly 301 is placed on the tray framework 200, so that the transportation process is safer, and the safety is improved. Because oil pump assembly 301 has certain weight and volume, if oil pump assembly 301 assembles in aviation oil drum 20 and can not dismantle, increase certain weight to the top of aviation oil drum 20, make the focus of aviation oil drum 20 shift up to empty easily at the in-process of transportation, the potential safety hazard appears easily. Moreover, the long-time insertion of the oil pump assembly 301 into the aviation oil barrel 20 also affects the oil in the aviation oil barrel 20.

In the embodiment shown in fig. 22 and 23, the oil pump assembly 301 includes an oil pump 310 and a motor 311 drivingly connected to the oil pump 310. The motor 311 may provide power for the oil pump 310 to drive the oil pump 310 to work. The oil pump 310 includes a pump rod 312, a vane 313 disposed in the pump rod 312, a support seat 314, an oil inlet 315 disposed at the pump rod 312 and far away from the oil pump 310, and an oil outlet 316 disposed at the pump rod 312 and near the oil pump 310. The vane 313 is disposed at an end of the pump rod 312 away from the motor 311 and is close to the oil inlet 315 relative to the oil outlet 316. The support seat 314 is disposed between the oil inlet end 315 and the oil outlet end 316 of the oil pump 310, and is disposed closer to the oil outlet end 316 than the oil inlet end 315. When the oil pump assembly 301 is assembled in the aviation oil drum 20, the pump rod 312 is inserted into the aviation oil drum 20, the oil inlet 315 is inserted into the aviation oil drum 20, the vane 313 is immersed in the oil in the aviation oil drum 20, and the oil outlet 316 is exposed out of the aviation oil drum 20 and connected to an external pipeline. Because the aviation gasoline is low-flash-point fuel, the blade 313 is in full contact with oil in the aviation gasoline barrel 20, the mode can avoid the contact of the oil inlet 315 of the oil pump 310 with air, avoid spark generation and achieve higher safety. In addition, in the oil pumping process, the pipe wall of the pump rod 312 is clamped with the oil outlet of the aviation oil drum 20, and the supporting seat 314 is abutted against the oil outlet of the aviation oil drum 20, so that the separation is not easy to occur in the oil pumping process, and the stability is better.

In some embodiments, the oil pump 310 may be a vane-type liquid pump, and the oil pump 310 may operate without a pump priming and may run dry for up to 30 minutes, without being damaged by an empty oil pump. The oil pump 310 and the motor 311 can be steplessly adjusted in speed, flow adjustment is achieved, filling requirements of different flows are met, the maximum flow can reach 50L, and workers can flexibly configure the oil pump according to actual requirements. The motor 311 is also provided with an overheat protection device to prevent the motor 311 from being burnt out by overload.

In some embodiments, the aviation fuel filling apparatus 10 further includes a fire-retardant vent valve 317, the fire-retardant vent valve 317 is assembled at an air inlet of the aviation fuel drum 20, and the aviation fuel drum 20 can communicate with the outside through the fire-retardant vent valve 317. The air pressure in the aviation oil drum 20 is balanced. And back-fire relief breather valve 317 can prevent outside naked light to get into in the aviation fuel oil barrel 20, and factor of safety is high. In some embodiments, the aviation fuel filling device further comprises a pressure monitoring component (not shown), which can monitor the system pressure in real time to ensure the safety of use and maintenance.

In some embodiments, the oil pump 310 and the motor 311 are assembled through a quick release structure. The quick-release structure is adopted for assembly, so that the structure is compact, the butt joint and the installation are convenient, and no auxiliary tool is needed; on the other hand, the device is easy to disassemble and wash and convenient to maintain. In some embodiments, the oil pump 310 comprises an explosion-proof oil pump, which may consume up to 880W. In some embodiments, motor 311 comprises an explosion-proof motor. Through setting up explosion-proof oil pump and explosion-proof machine, prevent the explosion, the security is high. In some embodiments, the overall weight of the oil pump 310 and the motor 311 ranges from 4kg to 8 kg. Compared with the related oil pump assembly 301, the oil pump assembly is light in weight and easy to carry and maintain. In some embodiments, the oil pump assembly 301 may be a model HD-E2-V + SS304-1000HP or Germany FLUX sump pump.

In some embodiments, the cart 100 comprises an electric cart. In some embodiments, cart 100 comprises an explosion-proof electric cart. The explosion-proof electric truck has electronic steering and an explosion-proof grade of II B T4 Gb. Since the carrier 100 transports aviation gasoline, which is low flash point fuel, and has higher requirements for safety, the safety of the explosion-proof electric carrier is higher. In some embodiments, the truck 100 has a heavy load dimension of 2300mm 1000mm 2100mm and an empty load dimension of 2300mm 1000mm 1200 mm. In some embodiments, the maximum allowable total mass of the truck 100 may be up to 1.5t, which may be relatively heavy. The maximum speed of the truck 100 can reach 4 km/h.

In some embodiments, the cart 100 includes a power device 104 and a cable storage box 105. The power supply device 104 includes a storage battery 801 (as shown in fig. 28), a power supply output line (not shown), and a power supply output interface 106, wherein the storage battery 801 is disposed on the vehicle head 101, and the power supply output line is connected to the storage battery 801 and the power supply output interface 106. Cable storage box 105 is provided in head 101, cable storage box 105 is used to store power output lines, and power output interface 106 is provided on one side of cable storage box 105. Accomodate power output line through setting up cable receiver 105, reduce power output line's occupation space, make the locomotive 101 overall arrangement of carrier 100 compacter, the outward appearance is more beautiful. And the power output interface is connected with an external interface, so that the safety factor is higher. Note that, since the power output line is located in the cable storage box 105, it is not shown in the drawing.

In some embodiments, battery 801 may be an explosion-proof battery, not supporting pull-down charging. In some embodiments, battery 801 is a rechargeable battery. In some embodiments, the battery 801 can output 24VDC, the charging time is 4-6 hours, and the maximum load capacity is 1.5 t. The minimum ground clearance of the battery 801 is 20mm to 40mm, and a preferable value is 30 mm. In some embodiments, the battery capacity of battery 801 includes 85AH (amp hour) or 210AH (amp hour). In this embodiment, the battery capacity 85AH of the battery 801 supports the transportation vehicle 100 to move about 12km or supports the top-loading refueling operation for about 2 hours. In other embodiments, the battery capacity 210AH of the battery 801 may support the truck 100 to move about 25km or about 6 hours for refueling.

In the embodiment shown in fig. 2, the power supply device 104 includes a main power switch 107 and a switch indicator 108, and the main power switch 107 and the switch indicator 108 are disposed on the top surface of the vehicle head 101 and electrically connected to the storage battery 801. The power main switch 107 is used for controlling the on-off of the storage battery 801, and the power-off protection operation is safe in emergency. The switch indicator 108 is used to indicate the working status of the main power switch 107, for example, when the main power switch 107 is turned on, the switch indicator 108 is turned on, and when the main power switch 107 is turned off, the switch indicator 108 is not turned on. In addition, the power main switch 107 and the switch indicator lamp 108 are arranged on the top surface of the vehicle head 101, so that the operation of workers is facilitated.

In some embodiments, the cable storage box 105 is provided on a front side of the head 101 facing away from the forks 102. Because locomotive 101 is towards one side of fork 102, has placed oil pumping device 300 on the tray framework 200, and oil pumping device 300 is nearer with locomotive 101's distance, and the space is limited, and the front side that locomotive 101 dorsad fork 102 is towards handlebar 103, and the space is bigger, locates this side with cable receiver 105, effectively utilizes the space, makes the overall arrangement of whole carrier 100 compacter. In some embodiments, cable organizer 105 includes a first organizer side 109 extending in a direction of extension of forks 102 and a second organizer side 110 opposite first organizer side 109. Wherein, the power output interface 106 is arranged on the first storage box side 109. First receiver side 109 is located the different sides respectively with oil drum supporting part 201, locates this first receiver side 109 with power output interface 106, conveniently connects the external power cord.

In some embodiments, the transportation vehicle 100 further includes a driving warning light 111 and a charging interface 112 electrically connected to the battery 801. The driving warning light 111 is located on one side of the vehicle head 101, and specifically, the driving warning light 111 is disposed on the second storage box side 110. The driving warning light 111 is used to remind the driver of avoiding the surrounding area when the truck 100 is in the driving process. Because the power output line of battery 801 is accomodate in cable receiver 105, locate driving warning light 111 in second receiver side 110, conveniently with power output line connection. The power output interface 106 and the traffic light 111 are symmetrically provided on the first storage box side 109 and the second storage box side 110, so that the power output line wiring is reduced, and the side of the cable storage box 105 is effectively utilized, thereby making the carrier 100 compact in structure and beautiful in appearance. The charging interface 112 is disposed on one side of the vehicle head 101 and is located on one side of the power supply device 104. The external power line is conveniently connected. In some embodiments, charging interface 112 includes an explosion-proof socket. The explosion-proof socket has good explosion-proof performance and high safety.

In some embodiments, the truck 100 is provided with a front wheel 113 and a plurality of rear wheels 114, the front wheel 113 extending downwardly from a lower surface of the head 101, and the plurality of rear wheels 114 extending downwardly from a lower surface of the forks 102 and located in an area of the forks 102 away from the head 101. In this embodiment, the length of the aviation oil barrel 20 in the vertical direction is 850mm to 900mm, and the preferred value is 890 mm. The weight of the oil product when the oil product is filled can reach 150 kg-200 kg, and the optimal value is 170 kg. The weight of the oil product can reach 15 kg-20 kg without oil product, and the optimal value is 19 kg. According to the data, the weight of the aviation oil barrel 20 is larger no matter the aviation oil barrel is full of oil or empty. A plurality of rear wheels 114 are provided on the area of the fork 102 remote from the head 101 to bear a substantial portion of the weight of the aviation fuel drum 20, making the aviation fuel filling apparatus 10 more stable in transportation.

In some embodiments, the tray frame 200 is provided with a plurality of lifting rings 202, the lifting rings 202 extending upwardly from the upper surface of the tray frame 200 for assembly with an external lifting tool. In this embodiment, the tray frame 200 is rectangular, and four hanging rings 202 are provided, which are respectively located at four corners of the tray frame 200. For example, in the case that a certain height or a practical scene is required to be specified, an external dispatching tool can be connected with the plurality of hanging rings 202 to ensure normal refueling, so that the application scene can be enlarged. In some embodiments, the tray frame 200 comprises a stainless steel plate. The corrosion resistance of the stainless steel plate is strong, static electricity is conducted, explosion is prevented, and the safety is high. And the stainless steel plate has higher hardness and is firm.

In the embodiment shown in fig. 3 and 7, the truck 100 is detachably assembled with the tray frame 200. In some embodiments, the cart 100 includes a liftable fork 102, the fork 102 including a raised state (shown in fig. 3) and a depressed state (shown in fig. 7). In some embodiments, the tray frame 200 is provided with a plurality of support feet 203, the plurality of support feet 203 extending downwardly from the lower surface of the tray frame 200; when the fork 102 is in the raised state, the pallet frame 200 is raised by the fork, and the plurality of support legs 203 are lifted off. At this time, the carrier 100 can drive the tray frame 200, the oil pumping device 300 arranged on the tray frame 200 and the aviation oil drum 20 to move, when the carrier moves to a designated place, the fork 102 is switched from the uplifted state to the pressed state, when the fork 102 is in the pressed state, the tray frame 200 descends, and the supporting legs 203 fall to the ground. At this time, the supporting legs 203 play a role in supporting and fixing, so that the carrier 100, the tray frame 200 and the oil pumping device 300 arranged on the tray frame 200 are fixed and do not move, and thus the oil pumping device is not easy to move in the oil filling process, and the safety is ensured. In the present embodiment, four support legs 203 are provided at four corners of the tray frame 200, respectively.

In some embodiments, the aviation fuel filling apparatus 10 includes a positioning assembly 700, the positioning assembly 700 includes a positioning pin 701 and a positioning ring 702 corresponding to the position of the positioning pin 701, the positioning pin 701 is disposed on a side of the tray frame 200 facing the locomotive 101 and extends in a horizontal direction; the positioning ring 702 is disposed on one side of the head 101, and the positioning ring 702 opens toward the tray frame 200. In the embodiment shown in fig. 1 to 5, the positioning pin 701 is inserted into the positioning ring 702 when the pallet frame 200 is assembled to the truck 100. In the embodiment shown in fig. 6, the locating pin 701 is disengaged from the locating ring 702 when the pallet frame 200 is disengaged from the cart 100. By providing the positioning pin 701 and the positioning ring 702, the truck 100 and the pallet frame 200 can be quickly assembled and positioned. In other embodiments, the positioning component 700 may also be a magnetic component, which is not limited in this application.

In some embodiments, the tray frame 200 is provided with a retractable first roller 204, the first roller 204 extending downward from the lower surface of the tray frame 200 and being located in the middle region of the tray frame 200. Because the weight of the aviation oil drum 20 and the oil pumping device 300 is large, the first roller 204 is arranged in the middle area of the tray frame 200, so that the weight of the aviation oil drum 20 and the oil pumping device 300 can be borne, the center of gravity of the whole aviation oil filling device 10 is located in the middle area of the tray frame 200, and the movement is more stable.

In some embodiments, the first roller 204 includes an extended state and a retracted state, wherein when the fork 102 is in the raised state (as shown in fig. 3), the first roller 204 is in the retracted state, the first roller 204 is off-ground, and when the fork 102 is in the depressed state, the first roller 204 is in the extended state, and the first roller is on the ground (not shown). The tray frame 200 can be drawn and moved by an external drawing tool by providing the first roller 204 which is retractable, so that the tray frame can be flexibly moved to increase application scenes when the carrier 100 is not provided.

In the embodiment shown in fig. 8, the tray frame 200 is provided with a plurality of second rollers 205 and a plurality of braking members 206 corresponding to the positions of the plurality of second rollers 205, the second rollers 205 are fixed at the bottom of the tray frame 200 and contact with the ground, the braking members 206 include a braking position 2061 and a non-braking position 2062, wherein when the braking member 206 is in the braking position 2061, the second rollers 205 are braked, and when the braking member 206 is in the non-braking position 2062, the second rollers 205 are released from braking and can move. The pallet frame 200 can be switched to the non-braking position 2062 by the brake member 206 when the pallet frame 200 needs to be moved by arranging the second roller 205 and the corresponding brake member 206, and the pallet frame 200 can be moved by the second roller 205. When the movement is not required, the brake 206 is switched to the brake position 2061 to brake, the tray frame 200 is fixed, and then the oil is supplied by the oil pump 300. The external traction tool can be used for traction, so that the trolley 100 can be flexibly moved when not provided, and application scenes are enlarged.

In some embodiments, the rollers 205 and the brakes 206 extend downward from the lower surface of the tray frame 200 and are distributed at four corners of the tray frame 200. Because the tray frame 200 bears the aviation oil drum 20 and the oil pumping device 300, the weight of the tray frame is large, and the plurality of rollers 205 and the plurality of braking pieces 206 are distributed at four corners of the tray frame 200, on one hand, the operation of the braking pieces 206 by workers is facilitated; on the other hand, the whole aviation fuel filling device is stable and better when moving.

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

In the embodiment shown in fig. 1 to 5, the flow meter 303, the hose reel 304, and the fuel gun 305 are all distributed with the canister support portion 201 along the first direction X, the fuel gun 305 is disposed close to the canister support portion 201 relative to the flow meter 303 and the hose reel 304, and the filter separator 302 and the fuel gun 305 are distributed side by side along the second direction Y. In actual use, the aviation fuel filling device 10 is stopped close to one side of a fuel filling port of general aviation equipment, the aviation fuel drum 20 is also close to one side of the general aviation equipment, and the flow meter 303 and the fuel drum supporting part 201 are positioned on the same side of the first direction X, so that a worker can conveniently observe the flow of specific filling; the hose reel 304 and the fuel gun 305 are located on the same side in the first direction X, so that workers can conveniently fuel general aviation equipment, the required fuel filling coil pipe 308 is short, and the fuel filling coil pipe 308 can be rolled out or retracted more simply and conveniently.

In some embodiments, the fueling apparatus 10 further includes a fixing bracket 318 protruding from the upper surface of the tray frame 200 and having a certain height. The fixing bracket 318 is used for fixing the flowmeter 303, the hose reel 304 and the fuel nozzle 305, wherein the hose reel 304 and the fuel nozzle 305 are arranged on the top of the fixing bracket 318. Because when the aviation fuel filling device 10 is used for filling fuel, a worker is required to operate, the rubber hose reel 304 and the fuel filling gun 305 are arranged at the top of the fixed support 318, so that the flow meter 303, the rubber hose reel 304 and the fuel filling gun 305 have certain heights, the upper space of the fixed support 318 is effectively utilized, and the worker can operate more conveniently and more labor-saving. The flow meter 303 is disposed on a side of the mounting bracket 318 facing away from the filter separator 302. The display surface of the flowmeter 303 faces the staff, so that the staff can conveniently observe the flow of the oil product. The height is set by the upper surface of the tray frame 200 as a reference surface according to the height of the worker or the hand-held height, and is not limited in the present application.

In some embodiments, the fixing brackets 318 are distributed with the oil drum supporting portion 201 along the first direction X and are arranged side by side with the filtering separator 302 along the second direction Y. In this embodiment, the maximum diameter of the aviation oil drum 20 is 550 mm-600 mm, and the preferred value is 580 mm. The aviation oil drum 20 occupies most of the space of the tray frame 200 in the second direction Y, and the fixing bracket 318, the flow meter 303, the hose reel 304 and the oil gun 305 disposed on the fixing bracket 318 also occupy a certain space, which may cause the aviation oil filling device 10 to have a larger volume if the structural layout is not compact, so that the aviation oil filling device 10 may have a larger occupied area and may be limited in use. Therefore, to ensure that the tray frame 200 and the aviation fuel filling apparatus 10 are smaller and more compact, the fixing bracket 318 and the oil drum supporting portion 201 are distributed along the first direction X, and the fixing bracket 318 and the filtering separator 302 are arranged side by side along the second direction Y.

In some embodiments, the bottom of the fixing bracket 318 has a receiving space 319, and the refueling device 10 includes a plurality of receiving boxes 320 disposed in the receiving space 319. The lower space of the fixing bracket 318 is effectively used by providing the accommodation space 319. In addition, a plurality of storage cases 320 are provided in the storage space 319, so that various small handheld maintenance tools and the like can be stored in the storage cases 320, thereby making it possible to enrich the storage function of the fuel filling apparatus 10.

In some embodiments, the fixing bracket 318 has a fuel nozzle limiting groove 321 (shown in fig. 1), the fuel nozzle limiting groove 321 is disposed on a side of the fixing bracket 318 facing away from the filtering separator 302, and the fuel outlet end of the fuel nozzle 305 is engaged in the fuel nozzle limiting groove 321. The oil outlet end of the oil gun 305 is the oil filler of the oil gun 305, and the oil filler of the oil gun 305 is clamped in the oil gun limiting groove 321, so that the oil gun 305 is conveniently fixed on the fixing bracket 318, a worker can conveniently take the oil gun, and the oil filler of the oil gun 305 is prevented from being exposed outside and being polluted by the external environment.

In the embodiment shown in fig. 1 and 4, the marine oil refueling unit 10 further includes a static conductive cord reel 322 disposed on the fixed bracket 318. When the aviation oil refueling device 10 refuels, the static conductive wire reel 322 is taken down from the fixing support 318, a static conductive wire is arranged in the static conductive wire reel 322, the static conductive wire is used for rapidly releasing static on the aviation oil refueling device, and the static conductive wire must be reliably grounded in the refueling operation process. The working surface side of the general aviation equipment is provided with an electrostatic conducting device. In some embodiments, the static conductive wire reel 322 is located on one side of the hose reel 304 in the first direction X. Therefore, the upper space of the fixing bracket 318 can be effectively utilized, and the fixing bracket is convenient for workers to take.

In some embodiments, the oil pumping device 300 further comprises a communication pipe 323 connected to the oil observer 306, an oil inlet end of the communication pipe 323 is communicated with the oil outlet end 316 of the oil pump assembly 301, the communication pipe 323 comprises a first oil outlet end 3231 and a second oil outlet end 3232, the oil inlet end of the oil observer 306 is communicated with the first oil outlet end 3231, and the oil inlet end of the filtering separator 302 is communicated with the second oil outlet end 3232. Because the oil pump assembly 301 is detachably assembled in the aviation oil drum 20, the pipeline connected with the oil outlet end 316 of the oil pump 310 is detachably assembled, and the communicating pipe 323 at least connecting the oil pump 310 with the oil viewer 306 and the filtering separator 302 can be detached without detaching the communicating pipe 323, and only the pipeline connecting the communicating pipe 323 with the oil outlet end 316 of the oil pump 310 is detached, so that the assembling time can be reduced, and the assembling efficiency can be improved.

In some embodiments, a gap is formed between the fixing bracket 318 and the oil drum supporting portion 201, and the oil viewer 306 and the communication pipe 323 are disposed in the gap between the fixing bracket 318 and the oil drum supporting portion 201. So effectively utilize the space between fixed bolster 318 and oil drum supporting part 201. The oil viewer 306 and the communicating pipe 323 are distributed in parallel in the second direction Y and are disposed on one side of the oil drum supporting portion 201, and the filtering separator 302 and the communicating pipe 323 are distributed in parallel in the second direction Y. The pipeline connecting the communicating pipe 323 with the oil viewer 306, the oil pump 310 and the filtering separator 302 is shorter, the pipeline layout is more compact, and the aviation oil refueling device 10 is compact in layout, smaller in size, smaller in occupied area and more applicable in scenes.

In some embodiments, the aviation fuel filling apparatus 10 includes a fixing rod 324 disposed at one side of the fuel tank supporting portion 201, the fixing rod 324 is protruded from the upper surface of the tray frame 200, and the communicating pipe 323 is fixed to the fixing rod 324. Fixing rod 324 is used to fix communication pipe 323 to ensure that communication pipe 323 has a certain height.

In some embodiments, the oil inlet end of the communication pipe 323 is higher than the first oil outlet end 3231 of the communication pipe 323, and is higher than the level of the oil viewer 306 and the level of the aviation oil drum 20. Therefore, the oil inlet end of the communication pipe 323, the first oil outlet end 3231 of the communication pipe 323, the oil viewer 306 and the aviation oil barrel 20 have height difference, so that the oil product in the communication pipe 323 is the oil product pumped out from the aviation oil barrel 20 through the oil pump 310 and can smoothly flow into the oil viewer 306 for observation, instead of the oil product stored in a pipeline connected with the oil outlet end 316 of the oil pump 310, and the normal operation of the oil pumping device 300 is ensured.

In some embodiments, the first drain end 3231 is at a higher elevation than the second drain end 3232. Because the oil entering from the oil inlet end of the communicating pipe 323 firstly enters the oil viewer 306 through the first oil outlet end 3231, when the oil is observed in the oil viewer 306, the normal conveying of the oil in the pipeline connected with the oil pump 310 is indicated, so the arrangement is convenient for observation, and the normal operation of the oil pumping device 300 is ensured.

In some embodiments, the aviation fuel filling apparatus 10 further comprises a fire extinguisher 325 assembled to the tray frame 200, and safety is improved by providing the fire extinguisher 325. In some embodiments, the fire extinguisher 325 and the oil drum support 201 are distributed side by side along the second direction Y and are located at one side of the storage bracket 500. The space of the tray frame 200 is effectively used, the components provided on the tray frame 200 are made compact, and the volume of the tray frame 200 is made small. And the lowest point of the fire extinguisher 325 is spaced from the upper surface of the tray frame 200. The height of the fire extinguisher 325 is convenient for the staff to take, and is easy to use.

In some embodiments, the oil pump assembly 301 further comprises a motor handle 326, the motor handle 326 being disposed on one side of the motor 311. The motor 311 can be taken by the worker, and the motor handle 326 is arranged on one side of the motor 311, so that the motor is more ergonomic and is easy for the worker to use. In some embodiments, the oil pump assembly 301 further includes a hand-held portion 327, and the hand-held portion 327 is disposed on the pump rod 312 and above the oil outlet end 316. When the oil pump assembly 301 needs to be detached from the oil outlet of the aviation oil drum 20, the handle portion 327 can be arranged to facilitate detachment for workers. In some embodiments, the oil pump assembly 301 further includes a dust cover (not shown) disposed on one side of the motor 311. When the pump rod 312 is accommodated in the accommodating tube 502, the motor 311 is located outside the accommodating tube 502, and the motor 311 is shielded by the dust cover, thereby preventing the motor 311 from being affected by the external environment.

In some embodiments, the aviation fuel filling apparatus 10 includes a quick release assembly 400. Oil pump assembly 301 is detachably assembled to aviation oil drum 20 through quick detach assembly 400. As shown in fig. 1 to 5 and 9 to 18, the quick release assembly 400 includes a fixing base 401 and a sealing cover 402 detachably assembled to the fixing base 401. Wherein fixing base 401 is ring structure, and fixing base 401 blocks in the oil-out of aviation oil drum 20, and the top surface of fixing base 401 is higher than the top surface of oil-out. In order to ensure that the oil pump assembly 301 is assembled in the aviation oil drum 20, the pump rod 312 is inserted from the fixing seat 401, connected with the fixing seat 401, and extends into the aviation oil drum 20, and the bottom of the supporting seat 314 abuts against the top of the fixing seat 401; when the oil pump assembly 301 is not assembled to the aviation oil drum 20, the sealing cover 402 is assembled to the top of the fixing seat 401 to seal the oil outlet of the aviation oil drum 20 (as shown in fig. 9). Through fixing base 401 and the sealed lid 402 that sets up quick detach subassembly 400, wherein fixing base 401 can assemble oil pump 310 in the oil-out of boat oil drum 20 fast, when oil pump 310 is not assembled in boat oil drum 20, sealed lid 402 can be fast sealed with the oil-out of boat oil drum 20, this quick detach simple structure, and the packaging hardware is simple, uses with oil pump 310, the cooperation of boat oil drum 20, can conveniently dismantle and assemble, improves the packaging efficiency.

In some embodiments, the fixing base 401 includes a first fixing portion 403 and a second fixing portion 404 connected to the first fixing portion 403, and the second fixing portion 404 extends downward along a bottom of the first fixing portion 403. The first fixing portion 403 includes a first channel 405 penetrating up and down, the second fixing portion 404 includes a second channel 406 penetrating up and down, and the second channel 406 is communicated with the first channel 405 and forms a downward step 407 with the first channel 405. In some embodiments, a recess 408 is disposed between the first fixing portion 403 and the second fixing portion 404, wherein an inner wall of the first channel 405 extends inward and forms a step 407 with the recess 408. The groove 408 is recessed inward from the inner peripheral wall of the holder 401 and communicates with the first passage 405 and the second passage 406. When fixing base 401 assembles in aviation oil drum 20, the oil-out joint of aviation oil drum 20 is in second channel 406, and the edge of the oil-out of aviation oil drum 20 and recess 408 spacing cooperation, and the top of the oil-out of aviation oil drum 20 supports with step 407 and leans on. This kind of assembled mode is simple, and fixing base 401 is difficult for breaking away from the oil-out of aviation oil drum 20. When oil pump assembly 301 assembles in aviation oil drum 20, pump rod 312 joint is in first passageway 405, and the outer wall of its pump rod 312 and the inner wall laminating of first passageway 405. In some embodiments, the first fixing portion 403 and the second fixing portion 404 are integrally formed, and the structure is simple.

In some embodiments, the groove 408 is provided with a first chamfer 409 at a side of the first channel 405 close to the second channel 406, and the first chamfer 409 is inclined from top to bottom in a direction from the outer side wall towards the inner side wall of the fixing seat 401. Play the guide effect through setting up first chamfer 409, be favorable to fixing base 401 cover to locate the oil-out of navigating oil drum 20, and when fixing base 401 cover was located the oil-out of navigating oil drum 20, be difficult for breaking away from in the recess 408.

In some embodiments, the maximum aperture of the second channel 406 is greater than the maximum aperture of the first channel 405. Because the oil-out joint of boat oil drum 20 is in second passageway 406, the oil-out itself has thickness, is greater than the maximum aperture of first passageway 405 with the maximum aperture of second passageway 406, guarantees that the inner wall of oil-out flushes with the inner wall of first passageway 405 mutually, guarantees that pump rod 312 does not block the shell through first passageway 405 and second passageway 406, can insert boat oil drum 20 smoothly.

In some embodiments, the outer circumferential wall of the holder 401 is provided with a plurality of flanges 410, and the plurality of flanges 410 extend obliquely along the circumferential direction of the holder 401. Wherein the upper edge of the flange 410 is located at the first fixing portion 403 and the lower edge of the flange 410 is located at the second fixing portion 404. The sealing cover 402 comprises a cover 411 and a plurality of ear buckles 412, wherein the ear buckles 412 extend from the top to the bottom from the edge of the cover 411, and one end of the ear buckles 412 far away from the cover 411 is bent inwards; when the oil pump assembly 301 is not assembled in the aviation oil drum 20, the sealing cover 402 covers the fixing seat 401 through the limit fit of the plurality of flanges 410 and the plurality of ear fasteners 412. In the present embodiment, the flanges 410 are provided in two, and the inclination directions of the two flanges 410 coincide. When the sealing cover 402 is covered on the fixing seat 401, the ear clip 412 of the sealing cover 402 covers the gap between two adjacent flanges 410, and rotates from the high end to the low end of the flange 410 (where the high end and the low end can be in contact with the plane of the radial direction of the fixing seat 401 as the reference plane) along the extending direction of the flange 410 to be clamped with the flange 410 until the bottom end surface of the flange 410 is in contact with the end surface of the ear clip 412 opposite to the flange 410, which indicates that the sealing cover 402 is clamped with the fixing seat 401. When the sealing cover 402 needs to be detached, the sealing cover 402 can be detached from the fixing seat 401 by rotating in the opposite direction. In some embodiments, the horizontal separation distance between adjacent flanges 410 is at least greater than the maximum dimension of the ear clip 412 in the horizontal direction. The arrangement is convenient for the ear clip 412 to cover the gap between two adjacent flanges 410 more easily, and the assembly efficiency is improved.

The fixing seat 401 is provided with a plurality of flanges 410, on one hand, the flanges are in limit fit with the ear buckles 412 of the sealing cover 402, on the other hand, the flanges are in limit fit with the supporting seat 314 arranged on the pump rod 312, the pump rod 312 is convenient to assemble, and the fixing effect of the pump rod 312 is ensured. In some embodiments, the edge of the supporting seat 314 is provided with a locking member 329 (as shown in fig. 2), the locking member 329 is movable along the axial direction of the supporting seat 314, and when the supporting seat 314 is assembled to the fixing seat 401, the locking member 329 is operated along the axial direction of the supporting seat 314 from the bottom to the top, and the supporting seat 314 is locked to the flange 410 (as shown in fig. 3). When the oil pump assembly 301 is disassembled, the lock member 329 is operated in the upward and downward direction in the axial direction of the support seat 314, and the support seat 314 is unlocked from the flange 410. So set up, can guarantee that oil pump 310 can assemble stably in the oil-out of aviation oil drum 20.

In the embodiment shown in fig. 15, the flange 410 is inclined at an angle α 1 in the range of 2 ° to 6 ° with respect to the radial direction of the holder 401. In some embodiments, the angle α 1 at which the flange 410 is inclined with respect to the radial direction of the fixing base 401 may be 2 ° or 3 ° or 4 ° or 5 ° or 6 °, with a preferred value of 4 °. The flange 410 is provided with a proper inclination angle, so that the abutting effect of the ear clip 412 and the flange 410 is better, and the assembly tightness is better.

In the embodiment shown in fig. 13 to 15, the outer peripheral wall of the fixing seat 401 is further provided with a plurality of limiting ribs 413, and the plurality of limiting ribs 413 extend along the axial direction of the fixing seat 401 and are located above the flange 410. In the embodiment shown in fig. 18, the inner wall of the cover 411 is provided with a receiving groove 414, and when the sealing cover 402 is assembled to the fixing base 401, the limiting rib 413 is in limiting fit with the receiving groove 414. Fixing base 401 sets up a plurality of spacing muscle 413, is on the one hand for the spacing cooperation of the inner wall with sealed lid 402, and on the other hand is for with storage tank 414 butt, conveniently assembles sealed lid 402, guarantees the fixed effect of sealed lid 402. In some embodiments, a plurality of limiting ribs 413 are arranged at intervals along the circumference of the fixing seat 401. In this embodiment, the limiting ribs 413 are four and symmetrically disposed on the circumferential direction of the first fixing portion 403.

In the embodiment shown in fig. 18, a buffer slot 415 is disposed in the cover 411, and the buffer slot 415 is disposed at the top of the cover 411 and is communicated with the accommodating slot 414. Because flange 410 sets up along the circumference slope of fixing base 401, when sealed lid 402 lid fits fixing base 401, sealed lid 402 has certain displacement distance in vertical direction, through set up buffer slot 415 at the top of sealed lid 402, buffer slot 415 is provided with the buffer space, avoids the top of first fixed part 403 touching the roof of lid 411. When the sealing cover 402 is assembled to the fixing base 401, the top of the fixing base 401 is located in the buffer slot 415. The inner wall of the cover 411 is protruded with a stopper 416 disposed between the buffer slot 415 and the receiving slot 414. The stopper 416 is used to separate the buffer groove 415 and the accommodating groove 414. The peripheral wall of fixing base 401 is equipped with second chamfer 417, and second chamfer 417 from the top down, is at the ascending slope of the direction of following the inside wall to the lateral wall of fixing base 401, and when sealed lid 402 was assembled in fixing base 401, second chamfer 417 leaned against with the inner wall of stopper 416. The fixing seat 401 is provided with a second chamfer 417 to avoid collision with the limiting block 416.

In some embodiments, when the oil pump assembly 301 is not assembled to the aviation oil drum 20, the oil pump assembly 301 is assembled to the receiving bracket 500. As shown in fig. 19 to 23, the aviation fuel tank 20 disposed on the tank support portion 201 occupies a large space, and the storage bracket 500 has a certain length, so that the whole aviation fuel filling apparatus 10 has a compact structure and a small volume. Will accomodate support 500 and oil drum supporting part 201 and distribute along second direction Y, make and accomodate support 500 and be located one side of boat oil drum 20. This makes it possible to effectively use the space of the tray frame 200 in the first direction X.

If the oil pump assembly 301 is assembled on the aviation fuel oil drum 20 and is not detached when fuel is not needed, the height of the whole aviation fuel oil filling device 10 is increased, so that the gravity center of the whole aviation fuel oil filling device 10 is raised, and the device is not safe enough in the moving process. And because motor 311 has certain volume and weight, and to whole oil pump assembly 301, it is great to bear weight and volume, safe inadequately in the removal process, and easy and the oil-out of boat oil drum 20 emergence dislocation, fixed effect is not good. In this application, when oil pump assembly 301 is not assembled in aviation oil drum 20, oil pump assembly 301 is assembled in accomodating support 500, and aviation oil filling device 10's focus reduces, and the stability of transportation is better.

In the embodiment shown in fig. 19 to 23, the receiving bracket 500 includes a plurality of support rods 501 and receiving tubes 502, the support rods 501 extending upward from the upper surface of the tray frame 200. The support bar 501 has a distance with respect to the upper surface of the tray frame 200. In some embodiments, the receiving pipe 502 is assembled to the upper end of the plurality of support rods 501 obliquely with respect to the upper surface of the tray frame 200 and extends from the second side X2 to the first side X1. The storage tubes 502 extend from the second side X2 to the first side X1, effectively utilizing the space of the tray frame 200 in the first direction X. When the oil pump assembly 301 is not assembled in the aviation oil drum 20, the pump rod 312 is accommodated in the accommodating pipe 502, and the motor 311 is located outside the accommodating pipe 502. So set up, accomodate pipe 502 and set up for the upper surface slope of tray framework 200, and have the distance with the upper surface of tray framework 200, oil pump assembly 301 assembles when accomodating support 500, and oil pump assembly 301 has certain distance for the upper surface of tray framework 200, makes things convenient for the staff to take. The pump rod 312 is accommodated in the accommodating pipe 502, and due to the generation of impurities caused by long-term accumulation, part of the oil in the pump rod 312 is collected in the accommodating pipe 502, and the accommodating pipe 502 is inclined relative to the upper surface of the tray frame 200, so that the oil in the accommodating pipe 502 can be conveniently cleaned or cleaned. In some embodiments, the plurality of support bars 501 are spaced along the first direction X and the second direction Y, and the plurality of support bars 501 are spaced from the second side X2 to the first side X1. In this application, the bracing piece 501 is set to two, and with the middle region of accomodating the pipe 502, so set up, the messenger bears the power equilibrium of accomodating the pipe 502, and stability is better.

In some embodiments, the receiving brackets 500 and the oil drum supporting parts 201 are distributed along the second direction Y, and the receiving pipes 502 are disposed obliquely with respect to the upper surface of the tray frame 200 and the second direction Y. So set up, when oil pump assembly 301 is not assembled in aviation oil drum 20, motor 311 distributes at second direction Y with aviation oil drum 20 of placing in oil drum supporting part 201, and is located aviation oil drum 20's one side, and is more convenient when oil pump assembly 301 takes. Because the motor 311 has certain volume and weight, the motor 311 is located same side with the aviation oil drum 20, reduces the distance of taking, and is more laborsaving.

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 oil drum supporting portion 201 are distributed along the second direction Y, the first receiving end 503 is close to the second side X2 relative to the first side X1, and the second receiving end 504 is close to the first side X1 relative to the second side X2. When the oil pump assembly 301 is not assembled in the aviation oil drum 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. So set up, make motor 311 lie in and place in same one side of the aviation oil drum 20 of oil drum supporting part 201, conveniently take.

In the embodiment shown in fig. 19, the storage tube 502 extends obliquely in the second direction Y toward the oil drum supporting portion 201 in the direction from the second side X2 to the first side X1. Because the pump rod 312 is inserted into the aviation oil drum 20, and the oil inlet 315 of the pump rod 312 contacts with the oil in the aviation oil drum 20, it indicates that the pump rod 312 has a certain length, and when the pump rod is not required to be assembled into the aviation oil drum 20, the pump rod is accommodated in the accommodating tube 502, so that the accommodating tube 502 has a certain length, and the accommodating tube 502 extends obliquely from the second side X2 to the first side X1 and in the second direction Y to the direction close to the oil drum supporting portion 201, so that the space of the oblique diagonal of the tray frame 200 is effectively utilized, the volume of the tray frame 200 is smaller, and the length of the aviation oil filling device 10 is shorter, so that the center of gravity of the aviation oil filling device 10 is closer to the vehicle head 101 during transportation. In some embodiments, the receiving tube 502 is disposed obliquely with respect to the vertical direction and the first direction X.

If the receiving tube 502 is not inclined, the length of the tray frame 200 is long, and thus the distance from the head 101 of the truck 100 to the fork 102 is long, resulting in a long length and a large volume of the whole aviation fuel filling apparatus 10. The aviation fuel oil barrel 20 has a certain weight and is located at one side far away from the vehicle head 101, and under the condition that the length of the tray frame 200 is long, the weight of the tail of the carrier 100 is large, so that the center of gravity of the whole aviation fuel oil filling device 10 is backward and unstable in the transportation process. Therefore, the inclined arrangement of the accommodating tube 502 of the present application can effectively utilize the space of the inclined diagonal of the tray frame 200, so that the volume of the tray frame 200 is smaller, and the length of the aviation fuel filling device 10 is shorter, so that the center of gravity of the aviation fuel filling device 10 is closer to the vehicle head 101 during transportation.

In the embodiment shown in fig. 20, the first receiving end 503 is higher than the second receiving end 504. The pump rod 312 is accommodated in the accommodating pipe 502, and due to the generation of impurities caused by long-term accumulation, part of the oil in the pump rod 312 is collected in the accommodating pipe 502, the accommodating pipe 502 is obliquely arranged relative to the upper surface of the tray frame 200, and the first accommodating end 503 is higher than the second accommodating end 504, so that the oil in the accommodating pipe 502 can be conveniently cleaned or cleared.

In the embodiment shown in fig. 21, the angle α 2 of inclination of the storage tubes 502 with respect to the upper surface of the tray frame 200 is in the range of 5 ° to 15 °. In some embodiments, the angle at which the receiving tubes 502 are inclined with respect to the upper surface of the tray frame 200 is 5 ° or 7 ° or 9 ° or 10 ° or 13 ° or 15 °. The inclination angle of the storage pipe 502 with respect to the upper surface of the tray frame 200 is set to be appropriate, so that the pump rod 312 can be more easily inserted into the storage pipe 502, and the operation by the worker is more convenient.

In the embodiment shown in fig. 19, the inclination angle α 3 of the storage tube 502 with respect to the second direction Y is in the range of 65 ° to 85 °. In some embodiments, the inclination angle α 3 of the receiving tube 502 with respect to the second direction Y may be 65 ° or 70 ° or 75 ° or 80 ° or 85 °, which is preferably 77 °. The inclination angle of the storage pipe 502 with respect to the second direction Y is set to be appropriate, and the tray frame 200 is made smaller in the case where the pump rod 312 can be stored, so that the volume and the occupied area of the entire aviation fuel filling apparatus 10 are made smaller.

In the embodiment shown in fig. 22, the receiving bracket 500 includes a plug member 505, and the plug member 505 is detachably assembled to the second receiving end 504 to close the second receiving end 504. In some embodiments, the plug member 505 may be a groove structure, and when oil inside the receiving pipe 502 needs to be cleaned, the truck 100 is separated from the tray frame 200, so that the plug member 505 is detached from the second receiving end 504, thereby facilitating the operation of workers. In some embodiments, when the oil pump assembly 301 is not assembled to the aviation oil drum 20, the oil inlet 315 of the oil pump 310 is located inside the receiving tube 502, close to the second receiving end 504 relative to the first receiving end 503, and spaced apart from the plug 505. An appropriate distance is arranged between the oil inlet end 315 of the oil pump 310 and the plug member 505, so that a space is reserved between the oil inlet end 315 of the oil pump 310 and the plug member 505, a certain oil product can be stored, and the oil product collected to the second accommodating end 504 is ensured not to contact with the oil inlet end 315 of the oil pump 310, so that when the oil pump 310 is reused, less oil product of the oil inlet end 315 of the oil pump 310 is extracted from the accommodating pipe 502, and waste is avoided. In some embodiments, the material of the plug 505 is teflon, which is antistatic, safer, and resistant to corrosion.

In the embodiment shown in fig. 21 and 22, the receiving bracket 500 includes a loop support 506, and the loop support 506 is disposed at the first receiving end 503. The ring support 506 functions as a support, in which on one hand, the inner sidewall of the ring support 506 functions as an outer sidewall of the pump rod 312, and on the other hand, the end surface of the ring support 506 functions as a support seat 314.

In some embodiments, the ring support 506 is attached to at least the inner wall and the end surface of the first receiving end 503, and when the pump rod 312 is received in the receiving tube 502, the outer sidewall of the pump rod 312 is attached to the inner sidewall of the ring support 506. So configured, there is a gap between the outer sidewall of the pump rod 312 and the inner sidewall of the receiving tube 502. By providing the ring support 506, the inner sidewall of the ring support can support the pump rod 312, so as to prevent the pump rod 312 from contacting and rubbing with the inner sidewall of the storage tube 502 when being inserted into or withdrawn from the storage tube 502, thereby generating static electricity or sparks, thereby improving safety. In some embodiments, the ring support 506 has a U-shaped cross-section and is clamped to the first receiving end 503 (as shown in fig. 23). With this arrangement, when the pump rod 312 is drawn out from the storage tube 502, the ring support 506 is not easily detached from the first storage end 503. In some embodiments, the bottom of the support seat 314 abuts the top of the ring support 506 when the pump rod 312 is received within the receiving tube 502. The bottom end surface of the support seat 314 is attached to the top end surface of the ring support 506, and is combined with the inner side wall of the ring support 506, so that the pump rod 312 is better fixed in the storage tube 502.

In some embodiments, the inner diameter of the ring support 506 ranges from 50mm to 80 mm. In some embodiments, the inner diameter of the ring support 506 may be 50mm or 55mm or 60mm or 65mm or 70mm or 75mm or 80mm, with a preferred value of 65 mm. The inner diameter of the ring support 506 is set to be appropriate so that when the pump rod 312 is inserted into the receiving tube 502 or withdrawn from the receiving tube 502, generation of static electricity or generation of sparks due to contact friction is avoided, and safety is improved. In some embodiments, the material of the ring support 506 is teflon. The Teflon is antistatic, better in safety and strong in corrosion resistance.

In some embodiments, the receiving tube 502 includes a limiting protrusion 507 (as shown in fig. 22), the limiting protrusion 507 is protruded on the inner peripheral wall of the receiving tube 502, and the limiting protrusion 507 is disposed close to the second receiving end 504 relative to the first receiving end 503; when the pump rod 312 is accommodated in the accommodating tube 502, the limit protrusion 507 abuts against the pump rod 312. When the aviation fuel filling device 10 moves, the pump rod 312 in the storage pipe 502 is easy to contact and rub with the storage pipe 502, therefore, the application sets the limiting protrusion 507 on the inner side wall of the storage pipe 502, can limit the pump rod 312 in the storage pipe 502 to be not easy to shake, avoids contacting and rubbing with the inner side wall of the storage pipe 502, and generates static electricity or sparks.

In the embodiment shown in fig. 1 to 6 and 24 to 27, the anti-toppling stopper 600 includes a stopper body 601 and a protective layer 602 covering a surface of the stopper body 601. Wherein the anti-toppling stopper 600 is upwardly protruded on the upper surface of the tray frame 200 and is located at the edge of the oil drum supporting portion 201. The oil drum supporting portion 201 is used to support the aviation oil drum 20, and the aviation oil drum 20 may topple due to unstable gravity center during the movement of the aviation oil refueling device 10 due to the large volume and weight of the aviation oil drum 20. Therefore, the edge of the oil drum supporting portion 201 is provided with the stop body 601 of the anti-toppling stop 600, so as to prevent the aviation oil drum 20 arranged on the oil drum supporting portion 201 from toppling over, and the protective layer 602 arranged on the surface of the stop body 601 is used for protecting the stop body 601, thereby avoiding the aviation oil drum 20 from rubbing against the stop body 601. Moreover, when the aviation oil drum 20 is loaded and unloaded, the anti-toppling stop block 600 can play a role in positioning, fixing and buffering protection.

In the embodiment shown in fig. 24 to 27, the anti-toppling stopper 600 includes a plurality of anti-toppling pillars 603 in a column shape, and the anti-toppling pillars 603 are spaced apart from the edge of the oil drum supporting portion 201. In this embodiment, the anti-toppling columns 603 are set to four, and the interval is set at the edge of the oil drum supporting portion 201, so that the oil drum 20 can be prevented from toppling in all directions. The anti-toppling stopper 600 is a columnar anti-toppling column 603, and has simple structure and convenient assembly.

In some embodiments, the maximum horizontal distance between the anti-toppling block 600 and the outer sidewall of the aviation oil drum 20 when the aviation oil drum 20 is disposed on the drum support portion 201 is in the range of 10mm to 20mm, and a preferred value thereof is 15 mm. Prevent empting and set up suitable horizontal distance between dog 600 and the oil drum 20 of navigating, when guaranteeing that oil drum 20 places in oil drum supporting part 201, be difficult for with prevent empting dog 600 contact friction, guarantee the security.

In some embodiments, the height L1 of the stop body 601 ranges from 150mm to 200mm (as shown in FIG. 25). In some embodiments, the height L1 of the stopper body 601 may be 150mm or 160mm or 170mm or 180mm or 190mm or 200mm, with a preferred value of 180 mm. Because the volume and the weight of the aviation oil barrel 20 are large, the height of the block main body 601 is not too high or too low, and when the height of the block main body 601 is too high and the aviation oil barrel 20 needs to be placed on the oil barrel supporting part 201, the height for lifting the aviation oil barrel 20 is too high, which is very laborious; when the height of dog main part 601 is crossed lowly, place in the time of the aviation oil drum 20 of oil drum supporting part 201 emptys, play the effect of preventing empting. Consequently, set up the height of dog main part 601 suitable, can reach the effect of preventing empting on the one hand, on the other hand can guarantee to lift the height of aviation oil drum 20 moderate, and is not hard. In some embodiments, the ratio of the height of the stop body 601 to the height of the jet fuel tank 20 is in the range of 1/5-1/4.5, with a preferred value of 1/4.8. So set up, set up the proportion of the height of dog main part 601 and the height of boat oil drum 20 suitable, can reach the effect of preventing empting on the one hand, on the other hand can guarantee to lift up the height moderate of boat oil drum 20, and is not hard.

In some embodiments, the material of the stop body 601 is stainless steel, the tray frame 200 comprises a stainless steel plate, and the stop body 601 is attached to the stainless steel plate. The stainless steel has strong corrosion resistance, static electricity conduction, explosion resistance and high safety. In some embodiments, the material of the protective layer 602 is teflon, and the teflon can prevent the aviation oil drum 20 and the stopper body 601 from mechanical friction, so that sparks are easily caused, and the safety is better. The Teflon is antistatic and has strong corrosion resistance.

In the embodiment shown in fig. 24-27, the anti-tipping post 603 comprises opposing first and second ends 604, 605, the second end 605 comprising a bottom end surface, the second end 605 being the end proximate the tray frame 200, and the second end 605 extending downwardly from the upper surface to the bottom end surface of the tray frame 200; the second end 605 has a screw 606 in the circumferential direction, the tray frame 200 has a screw hole (not shown) that is vertically through and corresponds to the screw 606, and the anti-toppling post 603 is fixed to the tray frame 200 by the engagement of the screw 606 and the screw hole. Because the volume and the weight of aviation oil drum 20 are great, have higher requirement to the fixed effect of preventing empting dog 600, prevent empting post 603 and be fixed in tray framework 200 through the cooperation of screw 606 and screw hole, its fixed mode is simple, and in the in-process that aviation oil filling device 10 removed, prevent empting post 603 and be difficult for becoming flexible, and fixed effectual. In some embodiments, the length of the second end 605 is greater than or equal to 1/6 of the length of the anti-tipping post 603. The length of the second end 605 is set to be proper, so that the second end 605 can penetrate through the lower surface of the tray frame 200 from the upper surface of the tray frame 200, and the second end has a sufficient fixed length, is more firmly fixed, and is not easy to loosen. In some embodiments, the length L2 of the second end 605 ranges from 25mm to 35 mm. In some embodiments, the length L2 of the second end 605 may be 25mm or 27mm or 29mm or 31mm or 33mm or 35mm, with a preferred value of 30 mm.

In some embodiments, the sidewall of the protection layer 602 has an offset through hole 607, the offset through hole 607 is disposed closer to the second end 605 than the first end 604, and the stopper body 601 located at the offset through hole 607 is exposed to the offset through hole 607. The protection layer 602 is provided with a yielding through hole 607, and the stopper body 601 located in the yielding through hole 607 is exposed out of the yielding through hole 607, so as to facilitate the worker to fix the anti-toppling pillar 603 to the tray frame 200 by using the yielding through hole 607 as a fixing support surface with the help of an external fixing tool.

In some embodiments, the vertical distance between the upper and lower edges of the abdicating through-hole 607 is greater than or equal to 1/9 of the length of the anti-tipping post 603. The vertical distance between the upper edge and the lower edge of the abdicating through hole 607 is set properly, so that a sufficient fixing support surface is provided, the fixing support surface is in full contact with an external fixing tool, and the fixing tool is not easy to slide off the anti-toppling column 603 when the anti-toppling column 603 is fixed. In some embodiments, the vertical distance L3 between the upper edge and the lower edge of the abdicating through-hole 607 ranges from 15mm to 25mm (as shown in fig. 25 or 26), which is preferably 20 mm.

In some embodiments, the maximum diameter of the anti-tipping column 603 ranges from 28mm to 36 mm. In some embodiments, the maximum diameter of the anti-tipping post 603 may be 28mm or 30mm or 32mm or 34mm or 36mm, with a preferred value of 32 mm. The maximum diameter that will prevent empting post 603 sets up suitably, guarantees that aviation oil drum 20 has sufficient hardness when empting, can block aviation oil drum 20. In some embodiments, the ratio of the maximum diameter of the anti-tipping column 603 to the maximum outer diameter of the aviation oil drum 20 is in the range of 1/20-1/15, which is 1/18. The proportion setting of the maximum diameter of preventing empting post 603 and the biggest external diameter of boat oil drum 20 is suitable, guarantees when boat oil drum 20 emptys, prevents empting post 603 and can not cause the damage to boat oil drum 20.

In some embodiments, the thickness L4 of the protective layer 602 of the anti-tipping post 603 at the peripheral wall of the stop body 601 ranges from 3mm to 7mm (as shown in FIG. 25). In some embodiments, the thickness L4 of the protective layer 602 on the peripheral wall of the stopper body 601 may be 3mm or 4mm or 5mm or 6mm or 7mm, with a preferred value of 5 mm. The thickness of the protective layer 602 on the peripheral wall of the block main body 601 is set to be proper, so that the contact friction between the cylinder wall of the aviation oil drum 20 and the protective layer 602 on the peripheral wall of the block main body 601 can be prevented. In some embodiments, the thickness L5 of the armor layer 602 of the anti-toppling post 603 on the top wall of the stopper body 601 ranges from 5mm to 15mm (as shown in FIG. 25). In some embodiments, the thickness L5 of the protective layer 602 on the top wall of the stopper body 601 may be 5mm or 7mm or 9mm or 11mm or 13mm or 15mm, with a preferred value of 10 mm. Because the volume and the weight of aviation oil drum 20 are great, when aviation oil drum 20 needs to be placed in oil drum supporting part 201 or aviation oil drum 20 is taken down from oil drum supporting part 201, the bottom of aviation oil drum 20 is easy to contact with the top of anti-toppling column 603 or the number of times of contact is large, so for the protective layer 602 located on the peripheral wall of block main body 601, the thickness of protective layer 602 located on the top wall of block main body 601 is thick, and the thickness of protective layer 602 located on the top wall of block main body 601 is set properly, it can be ensured that protective layer 602 located on the top wall of block main body 601 is not easy to damage, the bottom wall of aviation oil drum 20 is prevented from touching the top of block main body 601, and aviation oil drum 20 is protected.

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-toppling post 603, and the angle of inclination of the first protective layer chamfer 608 with respect to the central axis of the anti-toppling post 603 is less than 45 °. Because the volume and the weight of aviation oil drum 20 are great, when needs place aviation oil drum 20 in oil drum supporting part 201, the top of inoxidizing coating 602 sets up first inoxidizing coating chamfer 608, plays the guide effect, is favorable to placing aviation oil drum 20 in oil drum supporting part 201 fast. Moreover, the inclination angle of the first protective layer chamfer 608 relative to the central axis of the anti-toppling column 603 is smaller than 45 degrees, so that the oil drum 20 can be placed on the oil drum supporting part 201 more quickly.

In the embodiment shown in fig. 1 to 6, the aviation fuel filling apparatus 10 includes a control box 115, the control box 115 is assembled to the tray frame 200, and the control box 115 is disposed close to the first side X1 with respect to the second side X2 and electrically connected to the battery 801. So set up, make control box 115 with place in the setting of keeping apart of the aviation oil drum 20 of oil drum supporting part 201, factor of safety is high. And the control box 115 is close to the vehicle head 101 and is close to the storage battery 801 in the vehicle head 101, so that the control box can be conveniently connected with the storage battery 801, the length of a power cord of the storage battery 801 is reduced, and the whole aviation fuel filling device 10 is compact in structure. As shown in fig. 28, the control box 115 is electrically connected to the battery 801 in a pluggable manner, the control box 115 includes an inverter 804, the oil pump assembly 301 is electrically connected to the inverter 804 in a pluggable manner, and the inverter 804 converts the direct current output from the battery 801 into an alternating current and outputs the alternating current to supply power to the oil pump assembly 301. According to the arrangement, the aviation fuel filling device 10 does not need to be connected with an external power supply, so that the aviation fuel filling device is higher in mobility and more in application scenes. In some embodiments, control box 115 includes an explosion-proof control box for greater safety.

In some embodiments, the control box 115 and the fixing bracket 318 are arranged side by side along the second direction Y, and are staggered from the oil drum supporting portion 201 along the second direction Y. The control box 115, the fixing support 318 and the oil drum supporting part 201 are arranged on the tray frame 200, and occupy a certain space, and if the structure is not compact, the volume of the aviation oil refueling device 10 is large, so that the occupied area of the aviation oil refueling device 10 is large, and the use is limited. Therefore, to ensure that the tray frame 200 and the marine fuel filling apparatus 10 are smaller and more compact, the control box 115 and the fixed bracket 318 are arranged side by side in the second direction Y.

In some embodiments, there is a gap between the control box 115 and the fixing bracket 318, and when the oil pump assembly 301 is not assembled to the aviation oil drum 20, the pump rod 312 is inserted into the receiving tube 502 from one end of the receiving tube 502, and the other end of the receiving tube 502 extends to between the control box 115 and the fixing bracket 318. The receiving pipe 502 extends from the gap between the control box 115 and the fixing bracket 318, thus effectively utilizing the gap between the control box 115 and the fixing bracket 318. The second receiving end 504 thereof is disposed toward the headstock 101. When the plug member 505 needs to be cleaned or cleaned, the truck 100 can be separated from the tray frame 200, and the plug member 505 can be detached from the second receiving end 504, so that the operation of workers is facilitated.

In some embodiments, the control box 115 includes an operation panel 116, and the operation panel 116 is disposed on a side facing away from the oil drum supporting portion 201 in the second direction Y. The operation panel 116 is located on the same side of the receiving bracket 500 as the second direction Y of the tray frame 200. In some embodiments, the operation panel 116 includes an upper electrical interface 117 and an oil pump electrical interface 118, and the upper electrical interface 117 is electrically connected to the power output interface 106 in a pluggable manner. Through the plug-in type electric connection, the disassembly and the connection are convenient. In some embodiments, the top-mount power interface 117 comprises an explosion-proof plug. In some embodiments, power output interface 106 comprises an explosion-proof receptacle. Through setting up explosion-proof plug and explosion-proof socket plug and connect, the security is stronger.

In some embodiments, the top mount electrical interface 117 is disposed proximate to the first side X1 relative to the second side X2. Thus, the length of the connecting line of the control box 115 to the battery 801 can be reduced closer to the power output interface 106. The oil pump power interface 118 is disposed close to the second side X2 relative to the first side X1. By being closer to the oil pump assembly 301, the length of a connecting line of the oil pump assembly 301 and the inverter 804 can be reduced, and the aviation fuel filling device 10 is compact.

In some embodiments, the oil pump assembly 301 includes a power input interface 330 (shown in fig. 3), and the power input interface 330 is electrically connected to the oil pump power interface 118 in a pluggable manner. Through the plug-in type electric connection, the disassembly and the connection are convenient. In some embodiments, power input interface 330 comprises an explosion-proof plug. In some embodiments, the oil pump power interface 118 includes an explosion-proof socket. Through setting up explosion-proof plug and explosion-proof socket plug and connect, the security is stronger.

In some embodiments, the operator panel 116 further includes a wireless remote control switch 119. The wireless remote control switch 119 can realize emergency control of the stop of the oil pump 310. The control box 115 comprises a remote control indicator lamp 120 electrically connected with a wireless remote control switch 119, and the wireless remote control switch 119 is electrically connected with a storage battery 801. The battery 801 may supply power to the wireless remote control switch 119. A remote indicator light 120 is located on the top surface of the control box 115. So set up, be located the more easily position of seeing with remote control pilot lamp 120, can conveniently indicate the staff.

In some embodiments, the operation panel 116 further includes a start switch 121 and a power-on indicator lamp 122, the start switch 121 is disposed near the locomotive 101 with respect to the power-on indicator lamp 122, and the start switch 121 and the power-on indicator lamp 122 are electrically connected to the inverter 804. The start switch 121 is used for controlling the on-off between the inverter 804 and the oil pump assembly 301. The power-on indicator lamp 122 is used for indicating the working state of the start switch 121. When the starting switch 121 is opened, the inverter 804 is connected to the oil pump assembly 301, and the power-on indicator lamp 122 is turned on to indicate that the starting switch 121 is in an open state. When the start switch 121 is turned off, the inverter 804 is disconnected from the oil pump assembly 301, and the power-on indicator lamp 122 is turned off to indicate that the start switch 121 is in the off state.

In some embodiments, the control box 115 includes an emergency pump-off function. Before the work operation, it is necessary to detect the emergency pump-off function of the control box 115. The specific steps are that after the upper installation and power taking interface 117 is connected, the power main switch 107 is turned ON, the wireless remote control switch 119 is pressed to be ON, the starting switch 121 ON the control panel 116 of the control box 115 is pressed (for about more than 3 seconds), the power-ON indicator lamp 122 ON the control panel 116 of the control box 115 is turned ON, and then the oil pump power taking interface 118 supplies power normally. Then, the wireless remote control switch 119 is pressed to be turned OFF, the power-on indicator lamp 122 on the control panel 116 of the control box 115 is turned OFF, and the power-on interface 118 of the oil pump is powered OFF, which indicates that the emergency pump-stopping function of the control box 115 is normal. The test like this, guarantee when emergency appears, control box 115 can realize promptly stopping the pump, promotes the security.

And, when an emergency occurs, the emergency concrete steps include: firstly, turning off the wireless remote control switch 119 and stopping the operation of the oil pump 310; then the refueling coil 308 is retracted, and the switch of the oil pump 310 is turned off; then, the electrostatic conductive reel 322 is retracted; confirming that the supporting feet 203 of the tray frame 200 are lifted above the minimum safety height specified by the refueling site; then towing the navigational oil refueling apparatus 10 away from the hazardous area; finally, the main power switch 107 of the aviation fuel filling device 10 is closed. By means of the arrangement, safety of workers and the aviation fuel filling device 10 can be improved in emergency situations.

Before the aviation fuel filling device 10 is dragged integrally, the power-on indicator lamp 122 of the control panel 116 of the control box 115 is confirmed to be turned off; the support feet 203 of the pallet frame 200 rise above a minimum safe height specified for the fueling field. Before the truck 100 is separated from the pallet frame 200, care should be taken to disconnect the electrical connection between the control box 115 and the head 101 of the truck 100 and to minimize the truck 100. The above considerations ensure safe use of the aviation fuel filling apparatus 10.

In some embodiments, the tray frame 200 is further provided with a safety indication plate 207, which is distributed with the oil drum supporting portion 201 in the second direction Y. The security label plate 207 is used to label security content to comply with security standards.

Referring to fig. 28, the aviation fuel filling apparatus 10 further includes a fuel pump power supply circuit 800, and the fuel pump power supply circuit 800 is electrically connected to the fuel pump assembly 301. In some embodiments, the oil pump power supply circuit 800 includes a rechargeable battery 801, a power conversion circuit 802, and a switch control circuit 803. The battery 801 may provide direct current power, and the power conversion circuit 802 may convert the direct current power output by the battery 801 into alternating current power to power the oil pump assembly 301. In this process, the on-off between the power conversion circuit 802 and the oil pump assembly 301 can be controlled by the switch control circuit 803. It should be noted that, supplying power to the oil pump assembly 301 means supplying power to the motor 311 in the above-described embodiment. When the motor 311 is energized, the oil pump 310 can be driven to operate to perform a refueling operation.

In some embodiments, the power conversion circuit 802 includes an inverter 804, the inverter 804 is electrically connected to the battery 801 and the oil pump assembly 301, respectively, and the inverter 804 converts the direct current output by the battery 801 into alternating current and outputs the alternating current to power the oil pump assembly 301; the switch control circuit 803 includes a control switch 805, the control switch 805 is electrically connected between the battery 801 and the inverter 804, and the control switch 805 is used for controlling the on/off between the inverter 804 and the battery 801. The rechargeable storage battery 801 provided with the oil pump power supply circuit 800 provides direct current, the inverter 804 is used for converting the direct current output by the storage battery 801 into alternating current and outputting the alternating current so as to supply power to the oil pump assembly 301, and the on-off between the inverter 804 and the storage battery 801 is controlled through the control switch 805 of the switch control circuit 803. By the arrangement, the normal operation of the aviation fuel filling device 10 can be ensured, and the on-off between the inverter 804 and the storage battery 801 can be timely turned off through the control switch 805 in case of emergency.

In some embodiments, control switch 805 comprises a mechanical switch. The mechanical switch can be arranged in the control box 115, so that the operation of workers is facilitated. When workers work with the aid of the inverter, the on-off of the inverter 804 and the storage battery 801 can be controlled by operating the mechanical switch, and the mode is safe and reliable. The mechanical switch may be the power main switch 107 in the above-mentioned embodiment, and is disposed on the top surface of the power supply device 104.

In the embodiment shown in fig. 29, the control switch 805 comprises 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 the remote control circuit 807 controls the on/off of the electromagnetic switch according to a control command of the remote controller 806. By arranging the electromagnetic switch, the electromagnetic switch can be turned off in time through remote control of the remote controller 806, and the safety is higher. In some embodiments, the electromagnetic switch includes a relay that is sensitive and can be turned off in a timely manner.

In some embodiments, the remote control 806 includes a transmitter 808, and the remote control circuitry 807 includes a receiver 809 and a controller 810 electrically connected to the receiver 809. The receiver 809 is in communication with the transmitter 808, the receiver 809 is used for receiving a signal from the transmitter 808 and outputting a corresponding electrical signal, the controller 810 comprises a first control port 8101 and is electrically connected with the electromagnetic switch, and the controller 810 controls the electromagnetic switch to be switched on and off through the first control port 8101 according to the electrical signal output by the receiver 809. In some embodiments, the receiver 809 receives a signal from the transmitter 808, which may be indicative of opening or closing, and outputs a corresponding electrical signal indicative of opening or closing, at which time the controller 810 controls the electromagnetic switch to open or close via the first control port 8101. Compared with a mechanical switch, the mode can remotely control the working state of the oil pump assembly 301, operation by workers is not needed, use is more convenient, and manpower can be saved.

In some embodiments, the transmitter 808 comprises an infrared transmitter and the receiver 809 comprises an infrared receiver. The infrared transmitter and the infrared receiver are communicated, so that the remote control can be realized, and the limitation of regions or distances is avoided.

In some embodiments, the remote control circuit 807 further comprises a remote control indicator 120, the remote control indicator 120 is electrically connected to the controller 810, the controller 810 comprises a second control port 8102 electrically connected to the remote control indicator 120, and the controller 810 controls the remote control indicator 120 through the second control port 8102 according to 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 the electrical signal, and the controller 810 controls the remote indicator 120 to indicate the receiving status of the receiver 809. So set up, can conveniently indicate the staff, avoid the staff to operate repeatedly, and can observe the sending and receiving state between transmitter 808 and the receiver 809 through this mode.

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, and the start switch 121 is configured to control on/off between the inverter 804 and the oil pump assembly 301. In some embodiments, the oil pump power supply circuit 800 further includes an upper power indicator 122 electrically connected between the start switch 121 and the oil pump assembly 301, and the upper power indicator 122 is used to indicate the on/off states of the oil pump assembly 301 and the inverter 804. It should be noted that the storage battery 801, the inverter 804, the remote control indicator lamp 120, the starting switch 121, and the power-on indicator lamp 122 included in the oil pump power supply circuit 800 may be the storage battery 801, the inverter 804, the remote control indicator lamp 120, the starting switch 121, and the power-on indicator lamp 122 of the embodiment shown in fig. 1 to fig. 26.

Referring to the embodiment shown in fig. 30 and 31, similar to the embodiment shown in fig. 23 to 26, the main difference is that the anti-toppling block 900 includes a plurality of arc-shaped anti-toppling plates 903, and the anti-toppling plates 903 are distributed at intervals on the edge of the oil drum supporting portion 201. Compared with the anti-toppling column 603, the anti-toppling plate 903 has a large surface area, and when the aviation oil barrel 20 is toppled, the anti-toppling plate has a large contact area with the aviation oil barrel 20, so that the played anti-toppling effect is better. The area of the top of the arc-shaped anti-toppling plate 903 is larger than that of the top of the anti-toppling column 603, so that when the aviation oil barrel 20 is assembled and disassembled, the contact area with the bottom wall of the aviation oil barrel 20 is larger, the supporting force can be provided more uniformly, the aviation oil barrel 20 is not easy to reverse when the aviation oil barrel 20 is assembled or disassembled, and the bottom of the aviation oil barrel 20 is not easy to damage due to the fact that the size and the weight of the aviation oil barrel 20 are larger.

In the embodiment shown in FIG. 30, the distance L6 separating adjacent anti-tipping plates 903 ranges from 50mm to 70 mm. In some embodiments, the distance L6 separating adjacent two anti-tipping plates 903 may be 50mm or 55mm or 60mm or 65mm or 70mm, with a preferred value of 60 mm. In the embodiment shown in FIG. 31, the thickness L7 of the stop body 901 of the anti-tip plate 903 ranges from 20mm to 30 mm. In some embodiments, the thickness L7 of the stop body 901 of the anti-tip plate 903 may be 20mm or 25mm or 30mm, with a preferred value of 25 mm. In some embodiments, the ratio of the thickness of the stopper body 901 of the anti-toppling plate 903 to the thickness of the aviation oil drum 20 is in the range of 15 to 20, and the preferred value is 16.7. In some embodiments, the thickness L8 of the armor layer 902 of the anti-tipping panel 903 at the top wall of the stopper body 901 ranges from 5mm to 15 mm. In some embodiments, the thickness L8 of the protective layer 902 on the top wall of the stopper body 901 may be 5mm or 7mm or 9mm or 11mm or 13mm or 15mm, with a preferred value of 10 mm. In some embodiments, the thickness L9 of the armor layer 902 of the anti-tip plate 903 at the peripheral wall of the stopper body 901 ranges from 1mm to 5 mm. The thickness L9 of the protective layer 902 at the peripheral wall of the block body 901 may be 1mm or 2mm or 3mm or 4mm or 5mm, which is preferably 3 mm. In some embodiments, the top of the shielding layer 902 is provided with a second shielding layer chamfer 908, the second shielding layer chamfer 908 is inclined from the outer sidewall to the inner sidewall of the anti-toppling plate 903 from top to bottom, and the angle of inclination of the second shielding layer chamfer 908 with respect to the vertical direction is less than 45 °. In some embodiments, a plurality of anti-tip plates 903 are welded to the upper surface of the pallet frame 200.

Referring to the embodiment shown in fig. 32, similar to the embodiment shown in fig. 30, the main difference is that the anti-toppling stopper 1000 includes an anti-toppling ring 1003 in a ring shape, and the anti-toppling ring 1003 surrounds the oil drum supporting portion (not shown). The anti-toppling ring 1003 facilitates assembly as compared to a plurality of anti-toppling plates 903 in an arc shape. The surface area of the oil drum is larger, and when the aviation oil drum 20 is dumped, the contact area with the aviation oil drum 20 is large, so that the dumping prevention effect is better, the provided supporting force is more uniform, and the aviation oil drum 20 is not easy to reverse when being assembled or disassembled.

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 overcoat layer is provided with a third overcoat chamfer 1008, the third overcoat chamfer 1008 is inclined from the outer sidewall of the anti-toppling ring 1003 to the inner sidewall direction from top to bottom, and the angle at which the third overcoat chamfer 1008 is inclined with respect to the vertical direction is less than 45 °.

Referring to the embodiment shown in fig. 33, similar to the embodiment shown in fig. 1 to 5, the main difference is that the oil drum supporting portion 201 is disposed close to the first side X1 with respect to the second side X2. So set up, make whole aviation oil filling device 10's focus be close to locomotive 101, stability is better during the removal.

The technical solutions disclosed in the embodiments of the present application can complement each other without generating conflicts.

The above description is only exemplary of the present application and should not be taken as limiting the present application, as any modification, equivalent replacement, or improvement made within the spirit and principle of the present application should be included in the scope of protection of the present application.