Anti-leakage airplane oil pumping connector structure

Abstract

The anti-leakage airplane oil pumping connector structure comprises a positioning base, the positioning base is movably embedded into an airplane oil well mouth, the positioning base is integrally formed by a cambered surface concave part and a positioning ring part, a positioning oil return mechanism is fixedly installed above the positioning ring part, and the positioning oil return mechanism and an oil well oil pipe are movably installed. An installation top ring face is arranged at the top end of the arc-face concave portion, an organ protective cover is fixedly installed on the installation top ring face, and a protective buckle plate is installed on the top of the organ protective cover in a hinged mode. Then, a positioning oil return mechanism and an organ protective cover are matched to perform protective covering on the connecting part of the oil pumping pipe and the wellhead of the oil well, aircraft fuel oil leaked from the oil pumping connecting part can flow back into the oil well through matching of an arc-surface concave part of the positioning base, a first backflow through hole and a second backflow through hole, and aviation fuel oil resources are saved; meanwhile, aviation is prevented from polluting the periphery of the wellhead.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft oil extraction connection, in particular to an anti-leakage aircraft oil extraction connection head structure. Background Art

[0002] At present, fuel refueling for civil aviation aircraft generally uses a pump truck to connect the oil well inside the airport and the aircraft for pumping. However, the connection between the pump truck and the oil well is prone to oil leakage to the surrounding area during pressure relief and disassembly, which will result in a waste of aircraft fuel and also cause pollution to the area around the oil well.

[0003] Therefore, in view of the shortcomings of the prior art, it is necessary to provide a leakage-proof aircraft oil extraction connector structure to solve the shortcomings of the prior art. Utility Model Content

[0004] The purpose of the utility model is to avoid the deficiencies of the prior art and provide an anti-leakage aircraft oil pumping connector structure, which is movably embedded in the aircraft oil well mouth through a positioning base, and then the oil pumping pipe and the oil well mouth are connected with a protective cover in cooperation with a positioning oil return mechanism and an accordion protective cover, and the aircraft fuel leaking from the oil pumping connection part will flow back to the oil well through the arc surface recessed part of the positioning base in cooperation with the first reflux flow hole and the second reflux flow hole, thereby saving aviation fuel resources and avoiding aviation pollution around the well mouth.

[0005] The above-mentioned purpose of the utility model is achieved through the following technical means.

[0006] Provided is a leakage-proof aircraft oil pumping connector structure, comprising a positioning base, the positioning base is movably embedded in the wellhead of the aircraft oil well, the positioning base is formed by an arc surface recessed portion and a positioning ring portion being integrally formed, a positioning oil return mechanism is fixedly installed above the positioning ring portion, the positioning oil return mechanism is movably installed with the oil well oil pipe, a top end of the arc surface recessed portion is provided with an installation top ring surface, an accordion protective cover is fixedly installed on the installation top ring surface, and a protective buckle plate is hingedly installed on the top of the accordion protective cover;

[0007] The positioning oil return mechanism includes a bending hanging casing, the bottom of which is fixedly installed above the positioning ring, and the bending hanging casing is hung on the top of the oil well tubing. A plurality of first return flow holes are opened on the side wall of the bending hanging casing, and a plurality of second return flow holes are opened on the oil well tubing. The number and position of the first return flow holes correspond to those of the second return flow holes. A locking mechanism is also movably installed on the bending hanging casing, and the locking mechanism and the oil well tubing are locked and matched.

[0008] Specifically, the bent hanging sleeve includes an outer fitting portion, a turning portion and an inner fitting portion. The bottom of the outer fitting portion is fixedly installed above the positioning ring portion, the turning portion is hung on the upper edge of the oil well pipe, and a first recirculation hole is opened on the outer fitting portion. The top height of the first recirculation hole is lower than the bottom height of the inner fitting portion, and the bottom height of the first recirculation hole is the same as the top surface height of the positioning ring portion. A filter is installed inside the first recirculation hole.

[0009] Preferably, the locking mechanism includes a movable slot hole, which is provided on the outer fitting portion, an end of the movable slot hole away from the oil well pipe is connected to a plug-in hole, a locking hole is provided on the oil well pipe, a locking column is movably installed inside the plug-in hole, the locking column movably passes through the movable slot hole and extends to the inside of the locking hole to lock with it, an outer ring body is fixedly installed on the outside of the locking column inside the movable slot, and a return spring is installed on the outside of the locking column between the outer ring body and the end of the movable slot hole away from the oil well pipe.

[0010] Specifically, a sealing ring is fixedly mounted on the inner wall of the positioning ring portion.

[0011] Furthermore, a pull ring is fixedly installed on one end of the locking column away from the oil well tubing.

[0012] The utility model embeds the positioning base into the wellhead of the aircraft oil well movably, and then cooperates with the positioning oil return mechanism and the accordion protective cover to set a protective cover on the connection part between the oil pumping pipe and the wellhead of the oil well, so that the aircraft fuel leaking from the oil pumping connection part will flow back to the oil well through the arc surface recessed part of the positioning base in cooperation with the first return flow hole and the second return flow hole, thereby saving aviation fuel resources and avoiding aviation pollution around the wellhead. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The present invention is further described with reference to the accompanying drawings, but the contents in the accompanying drawings do not constitute any limitation to the present invention.

[0014] Figure 1 The utility model is a schematic diagram of a front cross-section of a leakage-proof aircraft oil extraction connector structure.

[0015] Figure 2 The utility model is a three-dimensional structural schematic diagram of a positioning base of a leakage-proof aircraft oil extraction connector structure.

[0016] Figure 3 The utility model is a three-dimensional structural schematic diagram of a bent hanging sleeve of a leakage-proof aircraft oil pumping connector structure.

[0017] Figure 4 The utility model is a leakage-proof aircraft oil pumping connector structure. Figure 1 A is an enlarged schematic diagram.

[0018] Figure 5 The utility model is a top three-dimensional structural schematic diagram of an accordion protective cover of a leakage-proof aircraft oil extraction connector structure.

[0019] from Figures 1 to 5 Including:

[0020] 1. Position the base;

[0021] 101, arc surface recessed portion, 102, positioning ring portion;

[0022] 2. Aircraft oil wellhead;

[0023] 3. Oil well tubing;

[0024] 4. Install the top ring surface;

[0025] 5. Organ protective cover;

[0026] 6. Protective gusset plate;

[0027] 7. Bend and hang the casing;

[0028] 71, outer laminating portion, 72, turning portion, 73, inner laminating portion;

[0029] 8. First recirculation hole;

[0030] 9. Second return hole;

[0031] 10. Movable slots;

[0032] 11. Plug hole;

[0033] 12. Locking hole;

[0034] 13. Locking column;

[0035] 14. Exocyclic body;

[0036] 15. Return spring;

[0037] 16. Sealing ring;

[0038] 17. Pull ring;

[0039] 18. Filter. DETAILED DESCRIPTION

[0040] The utility model is further described in conjunction with the following embodiments.

[0041] Example 1.

[0042] like Figure 1-5As shown, a leakage-proof aircraft oil pumping connector structure includes a positioning base 1, which is movably embedded in the aircraft oil well wellhead 2. The positioning base 1 is made of an arc surface recessed portion 101 and a positioning ring portion 102 formed in one piece. A positioning oil return mechanism is fixedly installed above the positioning ring portion 102. The positioning oil return mechanism is movably installed with the oil well oil pipe 3. The top of the arc surface recessed portion 101 is provided with a mounting top ring surface 4, and an accordion protective cover 5 is fixedly installed on the mounting top ring surface 4. The top of the accordion protective cover 5 is hingedly installed with a protective buckle plate 6.

[0043] The present application is used to provide oil pumping and leakage prevention protection at the wellhead connection of the oil well when the aircraft is refueled with aviation fuel. First, the positioning base 1 is installed inside the aircraft oil well wellhead 2, and then the oil extraction pipe is connected to the aircraft oil well wellhead 2. After the connection is completed, the accordion protective cover 5 is lifted to prevent fuel splashing, and the protective buckle plate 6 is buckled down to fit the connecting head of the oil extraction pipe to prevent impurities from entering from the top. The arc-surface recessed portion 101 of the positioning base 1 can make the leaked aviation fuel flow to the oil well oil pipe 3, and the positioning ring portion 102 can position the positioning oil return mechanism. At the same time, the positioning oil return mechanism is hung on the oil well oil pipe 3 and cooperates with the positioning base 1 to realize the reflux of aviation fuel.

[0044] The positioning oil return mechanism includes a bending hanging sleeve 7, the bottom of which is fixedly installed above the positioning ring 102, and the bending hanging sleeve 7 is hung on the top of the oil well tubing 3. A plurality of first return flow holes 8 are opened on the side wall of the bending hanging sleeve 7, and a plurality of second return flow holes 9 are opened on the oil well tubing 3. The number and position of the first return flow holes 8 and the second return flow holes 9 correspond to each other. A locking mechanism is also movably installed on the bending hanging sleeve 7, and the locking mechanism and the oil well tubing 3 are locked and matched.

[0045] The positioning oil return mechanism is hung on the oil well pipe 3 through the bending hanging sleeve 7, and then connected through the first reflux flow hole 8 and the second reflux flow hole 9, so that the leaked aircraft fuel is refluxed and collected into the oil well, and the entire bending hanging sleeve 7 and the positioning base 1 are positioned and locked through the locking mechanism.

[0046] The bent hanging sleeve 7 includes an outer fitting portion 71, a turning portion 72 and an inner fitting portion 73. The bottom of the outer fitting portion 71 is fixedly installed above the positioning ring portion 102. The turning portion 72 is hung on the upper edge of the oil well pipe 3. A first recirculation hole 8 is opened on the outer fitting portion 71. The top height of the first recirculation hole 8 is lower than the bottom height of the inner fitting portion 73. The bottom height of the first recirculation hole 8 is the same as the top surface height of the positioning ring portion 102. A filter screen 18 is installed inside the first recirculation hole 8.

[0047] The bent hanging sleeve 7 has a first reflux flow hole 8 on the outer fitting portion 71 corresponding to the second reflux flow hole 9 on the oil well pipe 3, so as to realize the recovery of leaked aircraft fuel. At the same time, the bottom height of the inner fitting portion 73 can avoid blocking the second reflux flow hole 9. The bottom height of the first reflux flow hole 8 is the same as the top height of the positioning ring portion 102, so that all the aircraft fuel in the positioning base 1 can be fully refluxed without oil accumulation. The filter screen 18 can prevent impurities from flowing back into the oil well.

[0048] The locking mechanism includes a movable slot 10, which is opened on the outer fitting portion 71. An insert hole 11 is connected to the end of the movable slot 10 away from the oil well pipe 3. A locking hole 12 is opened on the oil well pipe 3. A locking column 13 is movably installed inside the insert hole 11. The locking column 13 movably passes through the movable slot 10 and extends to the inside of the locking hole 12 to lock with it. An outer ring body 14 is fixedly installed on the outside of the locking column 13 inside the movable slot 10. A return spring 15 is installed on the outside of the locking column 13 between the outer ring body 14 and the end of the movable slot 10 away from the oil well pipe 3.

[0049] The locking mechanism achieves locking and unlocking in the locking column 13 by pulling out the locking column 13 , and at the same time generates elasticity through the reset spring 15 , so that in the default state, the locking column 13 can be driven by the elastic force to be inserted into the locking hole 12 .

[0050] A sealing ring 16 is fixedly mounted on the inner wall of the positioning ring portion 102 .

[0051] The sealing ring 16 can prevent leakage from the bottom and improve the return efficiency of the aviation fuel.

[0052] A pull ring 17 is fixedly mounted on one end of the locking column 13 away from the oil well tubing 3 .

[0053] The pull ring 17 can facilitate the pulling of the locking post 13 .

[0054] The utility model movably embeds the positioning base 1 into the aircraft oil well wellhead 2, and then cooperates with the positioning oil return mechanism and the accordion protective cover 5 to provide a protective cover for the connection between the oil pumping pipe and the oil wellhead. The aircraft fuel leaking from the oil pumping connection part will flow back to the oil well through the arc surface recessed part 101 of the positioning base 1 in cooperation with the first reflux flow hole 8 and the second reflux flow hole 9, thereby saving aviation fuel resources and avoiding aviation pollution around the wellhead.

[0055] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the utility model rather than to limit the protection scope of the utility model. Although the utility model is described in detail with reference to the preferred embodiments, ordinary technicians in this field should understand that the technical solution of the utility model can be modified or replaced by equivalents without departing from the essence and scope of the technical solution of the utility model.

Claims

1. A leak-proof aircraft oil pumping connector structure, characterized in that: It includes a positioning base, which is movably embedded in the wellhead of the aircraft oil well. The positioning base is made of an arc surface concave portion and a positioning ring portion formed in one piece. A positioning oil return mechanism is fixedly installed on the top of the positioning ring portion. The positioning oil return mechanism is movably installed with the oil well oil pipe. The top of the arc surface concave portion is provided with a mounting top ring surface, and an accordion protective cover is fixedly installed on the mounting top ring surface. A protective buckle plate is hingedly installed on the top of the accordion protective cover. The positioning oil return mechanism includes a bent hanging sleeve, the bottom of which is fixedly installed above the positioning ring, and the bent hanging sleeve is hung on the top of the oil well tubing. A plurality of first return flow holes are opened on the side wall of the bent hanging sleeve, and a plurality of second return flow holes are opened on the oil well tubing. The number and position of the first return flow holes and the second return flow holes correspond to each other. A locking mechanism is also movably installed on the bent hanging sleeve, and the locking mechanism and the oil well tubing are locked and matched.

2. The anti-leakage aircraft oil pumping connector structure according to claim 1, characterized in that: The bent hanging sleeve includes an outer fitting portion, a turning portion and an inner fitting portion, the bottom of the outer fitting portion is fixedly installed above the positioning ring portion, the turning portion is hung on the upper edge of the oil well pipe, the outer fitting portion is provided with the first recirculation hole, the top height of the first recirculation hole is lower than the bottom height of the inner fitting portion, the bottom height of the first recirculation hole is the same as the top surface height of the positioning ring portion, and a filter is installed inside the first recirculation hole.

3. The anti-leakage aircraft oil pumping connector structure according to claim 2, characterized in that: The locking mechanism includes a movable slot hole, which is opened on the outer fitting portion, and a plug-in hole is connected to the end of the movable slot hole away from the oil well pipe, and a locking hole is opened on the oil well pipe. A locking column is movably installed inside the plug-in hole, and the locking column movably passes through the movable slot hole and extends to the inside of the locking hole to lock with it. An outer ring body is fixedly installed on the outside of the locking column inside the movable slot, and a return spring is installed on the outside of the locking column between the outer ring body and the end of the movable slot hole away from the oil well pipe.

4. The anti-leakage aircraft oil pumping connector structure according to claim 3, characterized in that: A sealing ring is fixedly mounted on the inner wall of the positioning ring portion.

5. The anti-leakage aircraft oil pumping connector structure according to claim 4, characterized in that: A pull ring is fixedly mounted on one end of the locking column away from the oil well tubing.

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