CN222271908U - Aircraft oil extraction device - Google Patents
Aircraft oil extraction device Download PDFInfo
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- CN222271908U CN222271908U CN202420888897.5U CN202420888897U CN222271908U CN 222271908 U CN222271908 U CN 222271908U CN 202420888897 U CN202420888897 U CN 202420888897U CN 222271908 U CN222271908 U CN 222271908U
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Abstract
The utility model relates to an aircraft oil pumping and draining device which comprises a chassis, a power system, a tank body and an oil pumping and draining pipeline, wherein the tank body and the oil pumping and draining pipeline are arranged on the upper side of the chassis, the oil pumping and draining 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 respectively arranged at the bottom of the tank body, the other end of the bottom valve I is connected with a ball valve I, the other end of the bottom valve I is connected with a ball valve II and a pump, the other end of the ball valve I is connected with an oil gun I, the other end of the bottom valve II is connected with a ball valve IV, the other end of the ball valve IV is connected with a ball valve VI, the other end of the ball valve VI is connected with the other end of the pump and the ball valve VII, the other end of the ball valve VI is connected with the oil gun II, and the other end of the ball valve III is connected with the branch passage between the ball valve VI and an oil draining reel. The device has no requirement on the parking position of the airplane during operation.
Description
Technical Field
The utility model relates to the field of airplane oil pumping and discharging equipment, in particular to an airplane oil pumping and discharging device.
Background
When the aircraft is parked and overhauled, part of unused fuel is arranged in the fuel tank, and in order to avoid accidents in the overhauling process, the part of fuel is required to be overhauled after being drawn out.
At present, in the equipment for extracting and discharging the residual oil of an airplane, small-sized equipment is generally adopted, and only a pipeline and an oil pump are provided, so that an oil extracting and discharging rubber pipe is paved manually. The patent CN 209480018U discloses an aircraft oil pumping tool vehicle, wherein two mounting square pipes are fixedly connected to a vehicle body platform, a diaphragm pump is mounted at the upper end of each mounting square pipe through bolts, an oil inlet at the upper end of each diaphragm pump is provided with an oil pumping joint through an oil inlet pipe connecting piece, an oil outlet at the lower end of each diaphragm pump is connected with external oil storage equipment through an oil outlet pipe, an air pressure interface of each diaphragm pump is connected with a pressure reducing valve through an air pipe, the pressure reducing valves are connected with an external compressed air source through air pipes, and an aircraft can only stop at a designated place close to a ground oil storage tank during operation, so that the problems of low operation efficiency, high labor intensity and potential safety hazard exist.
Disclosure of Invention
The utility model provides an aircraft oil pumping and draining device for solving the problems, which comprises the following specific technical scheme:
The oil pumping and discharging device for the aircraft comprises a chassis, a power system, a tank body and an oil pumping and discharging pipeline, wherein the tank body and the oil pumping and discharging pipeline are arranged on the upper side of the chassis, 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 arranged at the bottom of the tank body, the other end of the bottom valve I is connected with a ball valve I, the other end of the bottom valve I is connected with a ball valve II and the ball valve III through an oil pumping reel, the other end of the ball valve I is connected with a ball valve IV through an oil pumping reel, the other end of the bottom valve II is connected with a ball valve V, the other end of the ball valve IV is connected with a ball valve VI through an oil discharging reel, the other end of the ball valve VI is connected with the ball valve II through an oil discharging reel, and the other end of the ball valve III is connected with a branch.
Further, an electrical control system for controlling the oil evacuation line is included.
Further, a wave-proof plate is arranged in the tank body, and a breather valve is arranged on the tank body.
Further, a manhole cover is arranged on the upper side of the tank body, and a foldable handrail is arranged on the top of the tank body.
Further, one side of the tank body is provided with a cab.
Further, the bottom valve III, the ball valve II, the ball valve V and the ball valve VII are manual ball valves, the ball valves I, the ball valve III, the ball valves IV and the ball valves VI are pneumatic ball valves, the bottom valve I is a pneumatic sea bottom valve, and the bottom valve II is a pneumatic high-liquid-level bottom valve.
Further, the oil gun I is a pressure oil gun, and the oil gun II is a gravity oil gun.
Further, a compensator, a filtering separator and a flowmeter are sequentially installed on the passage between the pump and the ball valve VI.
The utility model has the beneficial effects that:
1. The oil gun I is connected with an oil discharge port of the aircraft, residual oil in the oil tank of the aircraft is pumped and pumped, the residual oil is temporarily stored in the tank of the aircraft, the volume of the tank body is larger than that of the oil tank of the aircraft, the residual oil of a plurality of aircraft can be pumped and discharged, no requirement is made on the parking position of the aircraft during operation, after the tank body is filled with enough residual oil of the aircraft, the vehicle can move to the appointed ground, the oil receiving port of the oil storage tank is connected with the oil gun through a rubber pipe, a control valve is regulated, and the pump is started to discharge the internal combustion oil of the tank.
3. The device is connected into a transfer oil pipeline in series, can be used as a pump station to provide power for oil delivery, and has the functions of filtration and metering.
Drawings
In order to more clearly illustrate the embodiments of the utility model or the technical solutions of the prior art, the drawings that are necessary for the description of the embodiments or the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model and that other drawings can be obtained according to these drawings without inventive faculty for a person skilled in the art.
1. FIG. 1 is a schematic view of an aircraft oil extraction device according to the present utility model;
2. FIG. 2 is a flow chart of the oil extraction line of the present utility model;
3. fig. 3 is a schematic structural view of the can body according to the present utility model.
1, Chassis, 2, cab, 3, power system, 4, tank, 5, oil pumping 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 pumping reel, 5.14, oil discharging reel, 5.15, pump, 5.16, compensator, 5.17, filtering separator, 5.18, flowmeter, 6, electric control system.
Detailed Description
In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present utility model and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the present utility model, unless otherwise indicated, the meaning of "a plurality" is two or more.
The utility model provides the following specific embodiments of an aircraft oil extraction device:
Embodiment one:
As shown in figures 1-3, the aircraft oil pumping and draining device comprises a chassis 1, a power system 3, a tank 4 and an oil pumping and draining pipeline 5, wherein the tank 4 and the oil pumping and draining pipeline 5 are arranged on the upper side of the chassis 1, one side of the tank 4 is provided with a cab 2, the oil pumping and draining pipeline 5 comprises a bottom valve I5.1, a bottom valve II5.2, a bottom valve III5.3 and a pump 5.15, the bottom valve I5.1, the bottom valve II5.2 and the bottom valve III5.3 are respectively arranged at the bottom of the tank 4, the other end of the bottom valve I5.1 is connected with a ball valve I5.4, three branch paths are arranged on a path between the bottom valve I5.1 and the ball valve I5.4 and are respectively connected with a ball valve II5.5, a pump 5.15 and a ball valve III5.6, the other end of the ball valve I5.4 is connected with an oil gun I5.11 through an oil pumping reel 5.13, the other end of the ball valve II5.2 is connected with a ball valve IV5.7, a branch path between the bottom valve II.2 and the ball valve IV5.7 is opened on a path between the bottom valve I5.7 and the ball valve IV5.7, the path between the bottom valve I5.1 and the ball valve I5.5.4 is connected with a quick-release ball valve I9.5.5.6, the ball valve is connected with the ball valve I9.5.5.5.9, and the ball valve is connected with the ball valve is respectively, and the ball valve is connected with the ball valve I5.9.9.9.5.5.6, the ball valve, which is connected with the ball valve, the ball valve is respectively, the ball valve is connected with the ball valve through a quick valve, and the ball valve is connected with the ball valve, and the ball valve, the ball valve is the ball valve through the ball valve, and the quick valve, and the ball valve, the valve is the quick-valve, and the valve.
Preferably, the pump 5.15 is a centrifugal pump, and a compensator 5.16, a filtering separator 5.17 and a flowmeter 5.18 are sequentially arranged on a passage between the pump 5.15 and the ball valve VI 5.9.
Preferably, the power system 3 comprises an engine, the engine transfers power to a transfer case through a transmission shaft, the transfer case divides one part of the power to a hydraulic pump, the hydraulic pump drives a reel and coils an oil delivery hose, and the transfer case transfers the power to a pump 5.15 through a pneumatic clutch and belt transmission to provide power for pumping oil.
Preferably, the tank body 4 is of a cabin passing structure, a wave-proof plate is arranged in the tank body 4, a breather valve is arranged on the tank body 4, a manhole cover is arranged on the upper side of the tank body 4 and used for entering the tank for maintenance, a foldable handrail and a ladder stand are arranged at the top of the tank body 4, the ladder stand and the foldable handrail are convenient for people to go up and down the tank top and provide a certain safety guarantee, and a liquid level meter is further arranged on the tank body 4 and used for observing the oil quantity in the tank body 4.
Preferably, the bottom valves III5.3, II5.5, V5.8 and VII5.10 are manual ball valves, the ball valves I5.4, III5.6, IV5.7 and VI5.9 are pneumatic ball valves, the bottom valve I5.1 is a pneumatic subsea valve, and the bottom valve II5.2 is a pneumatic high-level bottom valve. Oil gun I5.11 is a pressure oil gun, and oil gun II5.12 is a gravity oil gun.
Preferably, the device also comprises an electric control system 6 which is arranged on the chassis 1 and used for controlling the oil pumping pipeline 5, and the electric control system 6 is used for controlling equipment operation by operators, and realizing oil pumping function and safety protection function during operation, such as brake interlocking during operation, electrostatic grounding alarm, lighting and operation state alarm.
When the fuel in the oil tank of the airplane is pumped, the oil gun I5.11 is connected with the oil discharge port of the airplane, the bottom valve II5.2, the ball valve I5.4 and the ball valve IV5.7 are opened, and after the pump 5.15 is started, the fuel sequentially enters the tank body 4 through the sequence of pumping reel 5.13, ball valve I5.4, pump 5.15, compensator 5.16, filtering separator 5.17, flowmeter 5.18, ball valve IV5.7 and bottom valve II 5.2.
When the fuel in the tank is discharged, the fuel gun II5.12 is connected with external equipment, the bottom valve III5.3 is opened, the pump 5.15 is started, and the fuel is sequentially discharged from the bottom valve II5.2, the pump 5.15, the compensator 5.16, the filtering separator 5.17, the flowmeter 5.18, the ball valve VI5.9, the fuel discharging reel 5.14 and the fuel gun II.12.
When the fuel oil pump is used as a mobile pump 5.15 station, the empty end of the ball valve II5.5 is used as an inlet of the mobile pump 5.15 station, the empty end of the ball valve VII5.10 is used as an outlet of the mobile pump 5.15 station, the ball valve II5.5 and the ball valve VII5.10 are opened, fuel oil sequentially flows through the sequence of 'ball valve II5.5, centrifugal pump 5.15, compensator 5.16, filtering separator 5.17, flowmeter 5.18 and ball valve VII 5.10', and otherwise, if the empty end of the ball valve II5.5 is used as an outlet of the mobile pump 5.15 station, the empty end of the ball valve VII5.10 is used as an inlet of the mobile pump 5.15 station, the flowing directions are opposite.
When the tank is filled with oil, the oil is filled by connecting an external oil filling device through the tail pressure oil filling interface of the ball valve V5.8.
When the fuel in the pipeline is pumped back, the bottom valve II5.2, the ball valve III5.6 and the ball valve IV5.7 are opened, the pump 5.15 is opened, and the fuel in the pipeline returns to the tank body 4 through the ball valve III5.6, the centrifugal pump 5.15, the compensator 5.16, the filtering separator 5.17, the flowmeter 5.18, the ball valve IV5.7 and the bottom valve II 5.2.
When the sewage is discharged in the tank, the bottom valve III5.3 is opened for sewage discharge.
The device is connected with an aircraft oil drain port through the oil gun I5.11, residual oil in an aircraft oil tank is pumped by the pump 5.15 and temporarily stored in the vehicle tank body 4, the volume of the tank body 4 is larger than that of the aircraft oil tank, residual oil of a plurality of aircraft can be pumped and discharged, no requirement is required on the parking position of the aircraft during operation, when enough aircraft residual oil is pumped and discharged, after the tank body 4 is filled, the vehicle can move to the appointed ground, the oil tank is connected with the oil receiving port through the rubber pipe and the oil gun, the control valve is regulated, the pump 5.15 is started, the tank internal combustion oil can be discharged, the device can be used for pumping oil away from the aircraft and discharging oil away from the ground oil tank, the safety is higher, the oil pumping reel 5.13 and the oil discharging reel 5.14 are driven through the hydraulic reel, and the device is controlled through the operating handle and has convenient operation and low strength.
Meanwhile, other oil equipment can be used for connecting an oil discharge pipe with the special joint of the device, and directly discharging oil to the tank body 4 of the device so as to empty the self-stored oil.
The device is connected into a transfer oil pipeline in series, can be used as a pump 5.15 station to provide power for oil delivery, and has the functions of filtration and metering.
The foregoing has shown and described the basic principles, principal features and advantages of the utility model. It will be understood by those skilled in the art that the present utility model is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present utility model, and various changes and modifications may be made without departing from the spirit and scope of the utility model, which is defined in the appended claims.
Claims (8)
1. The aircraft oil pumping and draining device is characterized by comprising a chassis (1), a power system (3), a tank body (4) arranged on the upper side of the chassis (1) and an oil pumping and draining pipeline (5);
The oil pumping and draining 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), wherein the bottom valve I (5.1), the bottom valve II (5.2) and the bottom valve III (5.3) are all arranged at the bottom of the tank body (4), the other end of the bottom valve I (5.1) is connected with a ball valve I (5.4), three branch ways are respectively arranged on a passage between the bottom valve I (5.1) and the ball valve I (5.4) and are respectively connected with a ball valve II (5.5), a pump (5.15) and a ball valve III (5.6), the other end of the ball valve I (5.4) is connected with an oil gun I (5.11) through an oil pumping reel (5.13), the other end of the bottom valve II (5.2) is connected with a ball valve IV (5.7), a branch way is arranged on a passage between the bottom valve I (5.1) and the ball valve I (5.4) and is connected with a ball valve V (5.8), the other end of the ball valve I (5.7) is connected with a ball valve IV (5.7), and the other end of the ball valve I (5.4) is connected with a ball valve II (9.9.6) and the other end of the ball valve I (5.4) is connected with a ball valve II (9.9.7) through a ball valve, and the other end of the ball valve I (9.6) is connected with the ball valve (9.9.6).
2. An aircraft oil extraction device according to claim 1, further comprising an electrical control system (6) for controlling the oil extraction line (5).
3. The aircraft oil pumping and draining device according to claim 1, wherein a wave-proof plate is arranged in the tank body (4), and a breather valve is arranged on the tank body (4).
4. The aircraft oil pumping and draining device according to claim 1, wherein a manhole cover is arranged on the upper side of the tank body (4), and a foldable handrail is arranged on the top of the tank body (4).
5. An aircraft oil extraction and drainage device according to claim 1, characterized in that one side of the tank (4) is provided with a cab (2).
6. The aircraft oil extraction and drainage device according to claim 1, wherein the bottom valve III (5.3), the ball valve II (5.5), the ball valve V (5.8) and the ball valve VII (5.10) are manual ball valves, the ball valve I (5.4), the ball valve III (5.6), the ball valve IV (5.7) and the 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 and drainage device according to claim 1, wherein the oil gun I (5.11) is a pressure oil gun, and the oil gun II (5.12) is a gravity oil gun.
8. An 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 mounted in this order in the passage between the pump (5.15) and the ball valve VI (5.9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202420888897.5U CN222271908U (en) | 2024-04-26 | 2024-04-26 | Aircraft oil extraction device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202420888897.5U CN222271908U (en) | 2024-04-26 | 2024-04-26 | Aircraft oil extraction device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN222271908U true CN222271908U (en) | 2024-12-31 |
Family
ID=93960802
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202420888897.5U Active CN222271908U (en) | 2024-04-26 | 2024-04-26 | Aircraft oil extraction device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN222271908U (en) |
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2024
- 2024-04-26 CN CN202420888897.5U patent/CN222271908U/en active Active
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Legal Events
| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20250804 Address after: 471000 Henan Province Luoyang City Luo Long District Luo Long High-tech Development Zone Guanlin Avenue West Section Patentee after: Luoyang Lingyu Langchen Automobile Co.,Ltd. Country or region after: China Address before: 471000 No. 966, Guanlin Road, Luolong District, Luoyang City, Henan Province Patentee before: LUOYANG CIMC LINYU AUTOMOBILE Co.,Ltd. Country or region before: China |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20250828 Address after: 471000 No. 966, Guanlin Road, Luolong District, Luoyang City, Henan Province Patentee after: LUOYANG CIMC LINYU AUTOMOBILE Co.,Ltd. Country or region after: China Address before: 471000 Henan Province Luoyang City Luo Long District Luo Long High-tech Development Zone Guanlin Avenue West Section Patentee before: Luoyang Lingyu Langchen Automobile Co.,Ltd. Country or region before: China |
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| TR01 | Transfer of patent right |