Airplane oil pumping and discharging device

Abstract

The utility model relates to an airplane oil pumping and discharging device which comprises a chassis, a power system, a tank body installed on the upper side of the chassis and an oil pumping and discharging pipeline. The oil pumping and discharging pipeline comprises a bottom valve I, a bottom valve II, a bottom valve III and a pump; the bottom valve I, the bottom valve II and the bottom valve III are all mounted at the bottom of the tank body, the other end of the bottom valve I is connected with the ball valve I, three branches are arranged on a passage between the bottom valve I and the ball valve I and are respectively connected with the ball valve II, the pump and the ball valve III, and the other end of the ball valve I is connected with the oil gun I; the other end of the bottom valve II is connected with a ball valve IV, a branch is arranged on a passage between the bottom valve II and the ball valve IV and connected with a ball valve V, the other end of the ball valve IV is connected with a ball valve VI, two branches are arranged on a passage between the ball valve IV and the ball valve VI and connected with the other end of the pump and a ball valve VII respectively, and the other end of the ball valve VI is connected with an oil gun II. And a branch is arranged on the passage between the ball valve VI and the oil drainage reel and is connected with the other end of the ball valve III. The device has no requirement on the parking position of the airplane during operation.

Description

Technical Field

[0001] The utility model relates to the field of aircraft oil extraction equipment, in particular to an aircraft oil extraction device. Background Art

[0002] When an aircraft is parked for maintenance, there will be some unused fuel in the fuel tank. In order to avoid accidents during the maintenance process, this part of the fuel needs to be pumped out before maintenance.

[0003] At present, small equipment is generally used in aircraft residual oil extraction equipment, which only has pipelines and oil extraction pumps, and the oil extraction hose is laid manually. Patent CN 209480018U discloses an aircraft oil extraction tool vehicle, which has two mounting square pipes fixedly connected to the vehicle body platform; a diaphragm pump is installed on the upper end of the mounting square pipe by bolts; the oil inlet at the upper end of the diaphragm pump has an oil extraction joint through the oil inlet pipe connector; the oil outlet at the lower end of the diaphragm pump is connected to the external oil storage equipment through the oil outlet pipe; the diaphragm pump air pressure interface is connected to a pressure reducing valve through an air pipe; the pressure reducing valve is connected to an external compressed air source through an air pipe; during operation, the aircraft can only be docked at a designated location close to the ground oil storage tank; there are problems such as low operating efficiency, high labor intensity, and potential safety hazards. Summary of the invention

[0004] In order to solve the above problems, the utility model proposes an aircraft oil extraction and discharge device, and the specific technical solution is as follows:

[0005] An aircraft oil extraction and discharge device comprises a chassis, a power system, a tank body installed on the upper side of the chassis and an oil extraction and discharge pipeline; the oil extraction and discharge pipeline comprises a bottom valve I, a bottom valve II, a bottom valve III and a pump; the bottom valve I, the bottom valve II and the bottom valve III are all installed at the bottom of the tank body, the other end of the bottom valve I is connected to the ball valve I, three forks are opened on the passage between the bottom valve I and the ball valve I, which are respectively connected to the ball valve II, the pump and the ball valve III, and the other end of the ball valve I is connected to the oil gun I through an oil extraction reel; the other end of the bottom valve II is connected to the ball valve IV, a fork is opened on the passage between the bottom valve II and the ball valve IV, which is connected to the ball valve V, the other end of the ball valve IV is connected to the ball valve VI, two forks are opened on the passage between the ball valve IV and the ball valve VI, which are respectively connected to the other end of the pump and the ball valve VII, the other end of the ball valve VI is connected to the oil gun II through the oil discharge reel, and a fork is opened on the passage between the ball valve VI and the oil discharge reel, which is connected to the other end of the ball valve III.

[0006] Furthermore, it also includes an electrical control system for controlling the oil extraction and discharge pipeline.

[0007] Furthermore, a wave-breaking plate is provided in the tank body, and a breathing valve is installed on the tank body.

[0008] Furthermore, a manhole cover is provided on the upper side of the tank body, and a foldable handrail is installed on the top of the tank body.

[0009] Furthermore, a cab is provided on one side of the tank body.

[0010] Furthermore, bottom valve III, ball valve II, ball valve V and ball valve VII are manual ball valves, ball valve I, ball valve III, ball valve IV and ball valve VI are pneumatic ball valves, bottom valve I is a pneumatic seabed valve, and bottom valve II is a pneumatic high liquid level bottom valve.

[0011] Furthermore, the oil gun I is a pressure oil gun, and the oil gun II is a gravity oil gun.

[0012] Furthermore, a compensator, a filter separator and a flow meter are installed in sequence on the passage between the pump and the ball valve VI.

[0013] The beneficial effects of the utility model are:

[0014] 1. Connect the oil discharge port of the aircraft through the oil gun Ⅰ, pump out the remaining oil in the aircraft tank, and temporarily store it in the tank of the vehicle. The tank volume is originally larger than the aircraft tank, and the remaining oil of multiple aircraft can be pumped out. There is no requirement for the parking position of the aircraft during operation. When enough residual oil of the aircraft is pumped out and the tank is filled, the vehicle can be moved to the designated ground, connected to the oil storage tank through the hose and oil gun, adjust the control valve, start the pump, and the fuel in the tank can be discharged.

[0015] 3. Connecting this device in series to the oil transfer pipeline can serve as a pump station to provide power for oil transportation and have filtering and metering functions. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0017] 1. Figure 1 It is a structural schematic diagram of the aircraft oil extraction and discharge device of the utility model;

[0018] 2. Figure 2 It is a flow chart of the oil extraction and discharge pipeline of the utility model;

[0019] 3. Figure 3 It is a structural schematic diagram of the tank body of the utility model.

[0020] In the figure: 1. chassis; 2. cab; 3. power system; 4. tank; 5. oil extraction and discharge pipeline; 5.1. bottom valve I; 5.2. bottom valve II; 5.3. bottom valve III; 5.4. ball valve I; 5.5. ball valve II; 5.6. ball valve III; 5.7. ball valve IV; 5.8. ball valve V; 5.9. ball valve VI; 5.10. ball valve VII; 5.11. oil gun I; 5.12. oil gun II; 5.13. oil extraction reel; 5.14. oil discharge reel; 5.15. pump; 5.16. compensator; 5.17. filter separator; 5.18. flow meter; 6. electrical control system. DETAILED DESCRIPTION

[0021] In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present utility model, unless otherwise specified, "multiple" means two or more.

[0022] The utility model provides the following specific embodiments of the aircraft oil extraction and draining device:

[0023] Embodiment 1:

[0024] like Figure 1-3As shown, an aircraft oil extraction and discharge device comprises a chassis 1, a power system 3, a tank body 4 installed on the upper side of the chassis 1 and an oil extraction and discharge pipeline 5, a cab 2 is provided on one side of the tank body 4; the oil extraction and discharge pipeline 5 comprises a bottom valve I 5.1, a bottom valve II 5.2, a bottom valve III 5.3 and a pump 5.15; the bottom valve I 5.1, the bottom valve II 5.2 and the bottom valve III 5.3 are all installed at the bottom of the tank body 4, the other end of the bottom valve I 5.1 is connected to the ball valve I 5.4, three forks are opened on the passage between the bottom valve I 5.1 and the ball valve I 5.4, which are respectively connected to the ball valve II 5.5, the pump 5.15 and the ball valve III 5.6, the other end of the ball valve I 5.4 is connected to the oil gun I 5.11 through the oil extraction reel 5.13; the other end of the bottom valve II 5.2 is connected to the ball valve IV 5.7, the passage between the bottom valve II 5.2 and the ball valve IV 5.7 A fork is opened on the road and connected with ball valve V5.8. In this embodiment, there are two ball valves V5.8; the other end of ball valve IV5.7 is connected with ball valve VI5.9, and two forks are opened on the passage between ball valve IV5.7 and ball valve VI5.9, which are respectively connected with the other end of pump 5.15 and ball valve VII5.10, the other end of ball valve VI5.9 is connected with oil gun II5.12 through oil discharge reel 5.14, and a fork is opened on the passage between ball valve VI5.9 and oil discharge reel 5.14 and connected with the other end of ball valve III5.6; the other end of bottom valve III5.3 is a sinking pipe outlet, the other end of ball valve V5.8 is a tail pressure oil filling interface, the oil discharge reel 5.14 is connected with oil gun II5.12 through a quick connector, and the oil pumping reel 5.13 is connected with oil gun I5.11 through a quick connector.

[0025] Preferably, the pump 5.15 is a centrifugal pump, and a compensator 5.16, a filter separator 5.17 and a flow meter 5.18 are sequentially installed on the passage between the pump 5.15 and the ball valve VI 5.9.

[0026] Preferably, the power system 3 includes an engine, which transmits power to a transfer case through a transmission shaft. The transfer case distributes one of the power to a hydraulic pump, which drives a reel and reels an oil delivery hose. The transfer case transmits power to a pump 5.15 through a pneumatic clutch and a belt drive to provide power for pumping oil.

[0027] Preferably, the tank body 4 has a through-cabin structure, a wave-breaking plate is provided inside the tank body 4, a breathing valve is installed on the tank body 4, a manhole cover is provided on the upper side of the tank body 4, and the manhole cover is used to enter the tank for maintenance; a foldable handrail and a ladder are installed on the top of the tank body 4; the ladder and the foldable handrail are convenient for personnel to go up and down the tank top and provide a certain safety guarantee. A liquid level gauge is also installed on the tank body 4, and the liquid level gauge is used to observe the oil amount in the tank body 4.

[0028] Preferably, bottom valve III 5.3, ball valve II 5.5, ball valve V 5.8 and ball valve VII 5.10 are manual ball valves, ball valve I 5.4, ball valve III 5.6, ball valve IV 5.7 and ball valve VI 5.9 are pneumatic ball valves, bottom valve I 5.1 is a pneumatic sea bottom valve, bottom valve II 5.2 is a pneumatic high liquid level bottom valve, oil gun I 5.11 is a pressure oil gun, and oil gun II 5.12 is a gravity oil gun.

[0029] Preferably, the device also includes an electrical control system 6 installed on the chassis 1 for controlling the oil extraction and discharge pipeline 5. The electrical control system 6 enables the operator to control the equipment during operation, realize the function of oil extraction and discharge and the safety protection function during operation, such as brake interlocking, electrostatic grounding alarm, lighting, and operation status warning during operation.

[0030] When pumping fuel from the aircraft tank, connect the oil gun I5.11 to the aircraft oil drain port, open the bottom valve II5.2, ball valve I5.4 and ball valve IV5.7, start the pump 5.15, and the fuel enters the tank body 4 in the order of "oil pumping reel 5.13→ball valve I5.4→pump 5.15→compensator 5.16→filter separator 5.17→flow meter 5.18→ball valve IV5.7→bottom valve II5.2".

[0031] When draining the fuel in the tank, connect the oil gun II 5.12 to the external equipment, open the bottom valve III 5.3, start the pump 5.15, and the fuel is discharged in the order of "bottom valve II 5.2 → pump 5.15 → compensator 5.16 → filter separator 5.17 → flow meter 5.18 → ball valve VI 5.9 → drain reel 5.14 → oil gun II 5.12".

[0032] When used as a mobile pump 5.15 station, the unused end of the ball valve II 5.5 is used as the inlet of the mobile pump 5.15 station, and the unused end of the ball valve VII 5.10 is used as the outlet of the mobile pump 5.15 station. Open the ball valve II 5.5 and the ball valve VII 5.10, and the fuel flows in the order of "ball valve II 5.5 → centrifugal pump 5.15 → compensator 5.16 → filter separator 5.17 → flow meter 5.18 → ball valve VII 5.10"; on the contrary, if the unused end of the ball valve II 5.5 is used as the outlet of the mobile pump 5.15 station and the unused end of the ball valve VII 5.10 is used as the inlet of the mobile pump 5.15 station, the flow direction is opposite.

[0033] When filling the tank with oil under pressure, connect the external refueling equipment through the tail pressure oil filling interface of the ball valve V5.8 for refueling.

[0034] When the fuel in the pipeline is pumped back, open the bottom valve II 5.2, ball valve III 5.6 and ball valve IV 5.7, turn on the pump 5.15, and the fuel in the pipeline returns to the tank body 4 through "ball valve III 5.6 → centrifugal pump 5.15 → compensator 5.16 → filter separator 5.17 → flow meter 5.18 → ball valve IV 5.7 → bottom valve II 5.2".

[0035] When discharging sewage in the tank, open the bottom valve III5.3 to discharge sewage.

[0036] The device is connected to the oil discharge port of the aircraft through the oil gun I 5.11, and the pump 5.15 extracts the remaining oil in the aircraft tank and temporarily stores it in the tank body 4 of the vehicle. The volume of the tank body 4 is originally larger than the aircraft tank, and the remaining oil of multiple aircraft can be extracted. There is no requirement for the docking position of the aircraft during operation. When enough remaining oil of the aircraft is extracted and the tank body 4 is filled, the vehicle can be moved to the designated ground, and the oil storage tank receiving port is connected through the hose and the oil gun, the control valve is adjusted, and the pump 5.15 is started to discharge the fuel in the tank. The device can be used to extract oil away from the aircraft and to discharge oil away from the ground oil tank, and has high safety. The oil extraction reel 5.13 and the oil discharge reel 5.14 are driven by hydraulic reels and controlled by operating handles, which are easy to operate and have low strength.

[0037] At the same time, other oil equipment can be connected to the oil discharge pipe of this device with the special joint to directly discharge oil to the tank body 4 of this device to empty its own stored oil.

[0038] By connecting the device in series to the oil transfer pipeline, it can be used as a pump 5.15 station to provide power for oil transportation and has filtering and metering functions.

[0039] The above shows and describes the basic principle, main features and advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments, and the above embodiments and descriptions are only for explaining the principle of the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, and these changes and improvements fall within the scope of the utility model to be protected.

Claims

1. An aircraft oil extraction device, characterized in that: It comprises a chassis (1), a power system (3), a tank (4) installed on the upper side of the chassis (1), and an oil extraction and discharge pipeline (5); The oil extraction pipeline (5) includes a bottom valve I (5.1), a bottom valve II (5.2), a bottom valve III (5.3) and a pump (5.15). The bottom valve I (5.1), the bottom valve II (5.2) and the bottom valve III (5.3) are all installed at the bottom of the tank body (4). The other end of the bottom valve I (5.1) is connected to the ball valve I (5.4). Three branches are opened on the passage between the bottom valve I (5.1) and the ball valve I (5.4) and are respectively connected to the ball valve II (5.5), the pump (5.15) and the ball valve III (5.6). The other end of the ball valve I (5.4) is connected to the oil gun I (5.11) through the oil extraction reel (5.13). The other end of the bottom valve II (5.2) is connected to the ball valve IV (5.7), a fork is opened on the passage between the bottom valve II (5.2) and the ball valve IV (5.7) to connect to the ball valve V (5.8), the other end of the ball valve IV (5.7) is connected to the ball valve VI (5.9), two forks are opened on the passage between the ball valve IV (5.7) and the ball valve VI (5.9) to connect to the other end of the pump (5.15) and the ball valve VII (5.10) respectively, the other end of the ball valve VI (5.9) is connected to the oil gun II (5.12) through the oil drain reel (5.14), and a fork is opened on the passage between the ball valve VI (5.9) and the oil drain reel (5.14) to connect to the other end of the ball valve III (5.6).

2. The aircraft oil extraction device according to claim 1, characterized in that: It also includes an electrical control system (6) for controlling the oil extraction and discharge pipeline (5).

3. The aircraft oil extraction device according to claim 1, characterized in that: A wave-breaking plate is arranged inside the tank body (4), and a breathing valve is installed on the tank body (4).

4. The aircraft oil extraction device according to claim 1, characterized in that: A manhole cover is provided on the upper side of the tank body (4), and a foldable handrail is installed on the top of the tank body (4).

5. The aircraft oil extraction device according to claim 1, characterized in that: A cab (2) is provided on one side of the tank body (4).

6. The aircraft oil extraction device according to claim 1, characterized in that: The bottom valve III (5.3), ball valve II (5.5), ball valve V (5.8) and ball valve VII (5.10) are manual ball valves, the ball valve I (5.4), ball valve III (5.6), ball valve IV (5.7) and ball valve VI (5.9) are pneumatic ball valves, the bottom valve I (5.1) is a pneumatic sea bottom valve, and the bottom valve II (5.2) is a pneumatic high liquid level bottom valve.

7. The aircraft oil extraction device according to claim 1, characterized in that: Oil gun Ⅰ (5.11) is a pressure oil gun, and oil gun Ⅱ (5.12) is a gravity oil gun.

8. The aircraft oil extraction device according to claim 1, characterized in that: A compensator (5.16), a filter separator (5.17) and a flow meter (5.18) are also installed in sequence on the passage between the pump (5.15) and the ball valve VI (5.9).

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