Pressurized oil transportation inspection system

Abstract

The utility model provides a pressurized oil transportation inspection system which comprises an air path system used for supplying air, the air path system adopts an air booster pump as a power source to compress air into air sources with different pressure grades, so that filling and pressurizing of an auxiliary oil tank are achieved, and the pressurized oil transportation inspection system is used for pressure filling of wheel type equipment / rescue air bags. And the hydraulic pumping and discharging system adopts an explosion-proof motor pump set as a power source for pumping and discharging fuel oil of the auxiliary oil tank, and then the hydraulic pumping and discharging system is used for rapidly pumping and discharging oil in the auxiliary oil tank through an oil discharging pipe and a gravity refueling connector. According to the system, rapid pressurization of the auxiliary fuel tank can be achieved under the condition that an aircraft engine is not started, meanwhile, fuel oil in the pressurization fuel tank can be continuously extracted, and rapid troubleshooting and overhauling of the auxiliary fuel tank are facilitated; meanwhile, the pressurization oil transportation inspection system can output an adjustable air source to the outside, and equipment such as tires and rescue air bags can be inflated.

Description

Technical Field

[0001] The utility model belongs to the field of aviation support equipment, and particularly relates to a pressurized fuel transfer inspection system. Background Art

[0002] When a certain type of aircraft is at the station or performing field maneuver operations, it is necessary to provide the required air pressure and flow rate to the 800L auxiliary fuel tank and 1700L auxiliary fuel tank of the aircraft, so as to realize the rapid pressurization of the auxiliary fuel tank without starting the aircraft engine. At the same time, it is also necessary to meet the continuous extraction of the fuel in the pressurized fuel tank to facilitate the rapid troubleshooting and maintenance of the auxiliary fuel tank. In order to meet the above functional requirements, a corresponding system needs to be designed. Content of the Utility Model

[0003] The purpose of the utility model is to provide a pressurized fuel transfer inspection system, which can realize the rapid pressurization of the auxiliary fuel tank without starting the aircraft engine, and at the same time can continuously extract the fuel in the pressurized fuel tank to facilitate the rapid troubleshooting and maintenance of the auxiliary fuel tank; at the same time, the pressurized fuel transfer inspection system can output an adjustable gas source externally, which can inflate equipment such as tires and rescue airbags.

[0004] In order to achieve the above technical features, the purpose of the utility model is realized as follows: A pressurized fuel transfer inspection system includes an air circuit system for supplying gas. The air circuit system uses an air booster pump as a power source to compress air into gas sources of different pressure levels, so as to realize the filling and pressurization of the auxiliary fuel tank and be used for the pressure filling of wheeled equipment / rescue airbags.

[0005] It also includes a hydraulic pumping and draining system. The hydraulic pumping and draining system uses an explosion-proof motor pump set as the power source for pumping and draining the fuel in the auxiliary fuel tank, and is used to quickly pump and drain the oil in the auxiliary fuel tank through the drain pipe and the gravity refueling interface.

[0006] The air circuit system includes an air booster pump. The outlet of the air booster pump is connected to a first one-way valve. A system output switch, an air filter, a pressure reducing valve, and a reduced-pressure gas source switch are sequentially connected to the pipeline after the first one-way valve. The other end of the reduced-pressure gas source switch is connected to a reduced-pressure gas source output port.

[0007] An air source supply pressure switch is connected between the air filter and the pressure reducing valve, and the other end of the air source supply pressure switch is connected to an air source pressure output port.

[0008] A buffer gas cylinder is connected between the first one-way valve and the system output switch.

[0009] A first in-situ metering interface, a first air source pressure gauge, and a first pressure sensor are also connected between the first one-way valve and the system output switch.

[0010] It also includes a factory gas source interface and a standard gas source interface, and the factory gas source interface and the standard gas source interface are respectively connected to the system output switch through one-way valves.

[0011] A first safety valve is connected between the pressure reducing valve and the reduced-pressure gas source switch;

[0012] A second in-situ metering interface, a second gas source pressure gauge and a second pressure sensor are also connected between the pressure reducing valve and the reduced-pressure gas source switch.

[0013] The hydraulic pumping and draining system includes an explosion-proof motor pump set, and the inlet of the explosion-proof motor pump set is connected to the flexible oil bag through a second one-way valve, a first quick-release joint, a second quick-release joint and an oil delivery hose;

[0014] The outlet of the explosion-proof motor pump set is connected to the auxiliary fuel tank through a third quick-release joint.

[0015] A second safety valve is connected in parallel to the explosion-proof motor pump set;

[0016] A third in-situ metering interface and a third pressure sensor are connected between the second one-way valve and the first quick-release joint.

[0017] The utility model has the following beneficial effects:

[0018] 1. The system of the utility model can meet the fuel pumping and draining of an 800L auxiliary fuel tank and a 1700L auxiliary fuel tank of a certain type of aircraft, and the pumping and draining methods can be through the drain pipe and the gravity fuel filling port of the auxiliary fuel tank.

[0019] 2. The system of the utility model is equipped with an air pressurization system, which can fill compressed air meeting the pressure requirements into the auxiliary fuel tank to achieve rapid pressurization.

[0020] 3. The system of the utility model is equipped with an air pressurization branch system, which can realize continuously adjustable gas source output to pressurize the tires of wheeled equipment, rescue air bags and other equipment.

[0021] 4. The system of the utility model has a dual-power supply drive function, which can simultaneously meet the input of AC220V / 50Hz alternating current power supply and DC28V direct current power supply.

[0022] 5. The system of the utility model has a power inversion function, and can output AC220V / 50Hz alternating current power supply voltage by connecting to a ground power vehicle.

[0023] 6. The system of the utility model has a function of digitally displaying the operating pressure and overpressure alarm protection for the system operating mode.

[0024] 7. The system of the utility model has the in-situ metering function of the pressure gauge and the sensor. Description of the Drawings

[0025] The present utility model will be further described below in conjunction with the accompanying drawings and embodiments.

[0026] Figure 1 It is a pneumatic circuit system diagram of the present utility model.

[0027] Figure 2 It is a hydraulic pumping and drainage system diagram of the present utility model.

[0028] Figure 3 It is a process diagram of the booster of the auxiliary fuel tank of the present utility model.

[0029] Figure 4 It is a pressurization process diagram of wheeled equipment / rescue airbags, etc. of the present utility model.

[0030] Figure 5 It is a fuel pumping and drainage process diagram of the gravity fuel filling port of the auxiliary fuel tank of the present utility model.

[0031] Figure 6 It is a fuel pumping and drainage process diagram of the pressurized auxiliary fuel tank of the present utility model.

[0032] In the figure: air booster pump 1, first one-way valve 2, first in-situ metering interface 3, first gas source pressure gauge 4, first pressure sensor 5, buffer gas cylinder 6, system output switch 7, air filter 8, pressure reducing valve 9, second gas source pressure gauge 10, second pressure sensor 11, gas source supply pressure switch 12, decompressed gas source switch 13, first safety valve 14, standard gas source interface 15, factory gas source interface 16, gas source pressure output port 17, decompressed gas source output port 18, third quick-release joint 19, explosion-proof motor pump set 20, second safety valve 21, second one-way valve 22, third pressure sensor 23, third in-situ metering interface 24, first quick-release joint 25, second quick-release joint 26, oil delivery hose 27, flexible oil bag 28, aircraft pneumatic circuit distribution system 29, aircraft 30, booster pipe joint 31, rescue airbag equipment 32, wheeled equipment 33, aircraft fuel filling interface 34, oil delivery pipe joint 35, in-aircraft fuel supply and delivery system 36, gravity fuel filling port 37. Specific Embodiments

[0033] The embodiments of the present utility model will be further described below in conjunction with the accompanying drawings.

[0034] Embodiment 1:

[0035] See Figure 1-6, The pressurized fuel transfer inspection system includes a gas circuit system for supplying gas. The gas circuit system uses an air booster pump 1 as the power source to compress air into gas sources of different pressure levels, thereby achieving filling and pressurization of the auxiliary fuel tank and being used for pressure filling of wheeled equipment / rescue airbags. It also includes a hydraulic pumping and drainage system. The hydraulic pumping and drainage system uses an explosion-proof motor pump set 20 as the power source for pumping and draining the fuel in the auxiliary fuel tank, and is thus used to quickly pump and drain the oil in the auxiliary fuel tank through the drain pipe and the gravity refueling interface. This system can achieve rapid pressurization of the auxiliary fuel tank without starting the aircraft engine, and can continuously extract the fuel in the pressurized fuel tank, facilitating quick troubleshooting and maintenance of the auxiliary fuel tank. At the same time, the pressurized fuel transfer inspection system can output adjustable gas sources and can inflate equipment such as tires and rescue airbags.

[0036] See Figure 1 , Further, the gas circuit system includes an air booster pump 1. The outlet of the air booster pump 1 is connected to a first one-way valve 2. In sequence on the pipeline after the first one-way valve 2 are connected a system output switch 7, a gas filter 8, a pressure reducing valve 9, and a reduced-pressure gas source switch 13. The other end of the reduced-pressure gas source switch 13 is connected to a reduced-pressure gas source output port 18. Between the gas filter 8 and the pressure reducing valve 9 is connected a gas source supply pressure switch 12, and the other end of the gas source supply pressure switch 12 is connected to a gas source pressure output port 17. Through the above gas circuit system, it can be used to supply gas to the auxiliary fuel tank. The air booster pump 1 is used to compress and boost the air of standard air pressure to the system required pressure, with a maximum compressed output pressure of 30 MPa.

[0037] Further, a buffer gas cylinder 6 is connected between the first one-way valve 2 and the system output switch 7;

[0038] Further, a first in-situ metering interface 3, a first gas source pressure gauge 4, and a first pressure sensor 5 are also connected between the first one-way valve 2 and the system output switch 7.

[0039] Further, it also includes a factory gas source interface 16 and a standard gas source interface 15. The factory gas source interface 16 and the standard gas source interface 15 are respectively connected to the system output switch 7 through one-way valves.

[0040] Further, a first safety valve 14 is connected between the pressure reducing valve 9 and the reduced-pressure gas source switch 13;

[0041] Further, a second in-situ metering interface, a second gas source pressure gauge 10, and a second pressure sensor 11 are also connected between the pressure reducing valve 9 and the reduced-pressure gas source switch 13.

[0042] Among them, the first gas source pressure gauge 4 and the second gas source pressure gauge 10 are respectively used to display the standard nitrogen or compressed air input to the system under the power-off condition, so as to realize the power-off emergency operation of the equipment.

[0043] The first pressure sensor 5 and the second pressure sensor 11 are used to monitor the system operating pressure and provide input parameters for system early warning.

[0044] The buffer gas cylinder 6 is used to buffer the output air pressure of the booster pump and store the gas source in advance, and can achieve stable output of the gas source and pressure reduction output in a small range.

[0045] The system output switch 7, the pressure reducing gas source switch 13 and the gas source supply pressure switch 12 are respectively used to control the on-off of the gas circuit of the corresponding branch of the system.

[0046] The pressure reducing valve 9 is used to reduce the pressure of the compressed gas source and output a continuously adjustable low-pressure gas source, 0 - 0.3 MPa, adjustable.

[0047] The first safety valve 14 is used to limit the maximum pressure of the pressure reducing branch and mechanically protect the safe operation of the system.

[0048] Embodiment 2:

[0049] See Figure 2 , the hydraulic pumping and draining system includes an explosion-proof motor pump set 20. The inlet of the explosion-proof motor pump set 20 is connected to the flexible oil bladder 28 through a second one-way valve 22, a first quick-release joint 25, a second quick-release joint 26, and an oil delivery hose 27; the outlet of the explosion-proof motor pump set 20 is connected to the auxiliary fuel tank through a third quick-release joint 19. The hydraulic pumping and draining system uses an explosion-proof motor pump set as the power source for fuel pumping and draining of the auxiliary fuel tank, and can quickly pump and drain the oil in the auxiliary fuel tank through the oil discharge pipe and the gravity refueling interface.

[0050] Further, a second safety valve 21 is connected in parallel to the explosion-proof motor pump set 20;

[0051] Further, a third in-situ metering interface 24 and a third pressure sensor 23 are connected between the second one-way valve 22 and the first quick-release joint 25.

[0052] Among them, the quick-release joint selects a snap-type quick-release structure, which can quickly seal and connect the oil delivery hose.

[0053] The explosion-proof motor pump set 20 selects a vane pump as the power source for fuel pumping and draining, has strong self-priming ability and high fuel pumping efficiency, and the pumping head can reach 5 meters underground relative to the pump outlet.

[0054] The second safety valve 21 is used to limit the maximum pressure of the oil delivery head at the pump outlet, and is initially set to 0.3 MPa.

[0055] The third pressure sensor 23 is used to monitor the oil delivery pressure of the system, and immediately stops the machine and alarms when it exceeds the maximum value.

[0056] The third in-situ metering interface 24 is used for in-situ metering of the pressure sensor.

[0057] Example 3:

[0058] An operation method of a pressurized oil transmission inspection system, which is implemented by using the pressurized oil transmission inspection system, includes:

[0059] Auxiliary fuel tank pressurization control, which is used to perform pressurization operation on the auxiliary fuel tank through the gas circuit system;

[0060] Wheeled equipment / rescue airbag pressurization control, which is used to inflate the wheeled equipment / rescue airbag through the gas circuit system;

[0061] Auxiliary fuel tank fuel pumping and discharging control, which directly pumps and discharges the fuel in the auxiliary fuel tank through the hydraulic pumping and discharging system or indirectly pumps and discharges the fuel in the auxiliary fuel tank through the coordinated operation of the hydraulic pumping and discharging system and the gas circuit system.

[0062] Example 4:

[0063] See Figure 3 , the specific process of pressurizing the auxiliary fuel tank is as follows:

[0064] First, connect the decompression gas source output port 18 of the gas circuit system to the aircraft gas circuit distribution system 29, and the aircraft gas circuit distribution system 29 is connected to the pressurization pipe joint 31 of the aircraft 30;

[0065] Then, start the air booster pump 1, and the compressed gas generated by the air booster pump 1 sequentially passes through the first one-way valve 2, the system output switch 7, the air filter 8, the pressure reducing valve 9, and the decompression gas source switch 13 and enters the aircraft gas circuit distribution system 29, and then the aircraft gas circuit distribution system 29 re-distributes the compressed air into the auxiliary fuel tank to pressurize the auxiliary fuel tank;

[0066] Example 5:

[0067] See Figure 4 , the specific process of pressurizing the wheeled equipment / rescue airbag is as follows:

[0068] First, connect the decompression gas source output port 18 of the gas circuit system to the inlets of both the wheeled equipment 33 and the rescue airbag equipment 32 at the same time;

[0069] Then, start the air booster pump 1, and the compressed gas generated by the air booster pump 1 sequentially passes through the first one-way valve 2, the system output switch 7, the air filter 8, the pressure reducing valve 9, and the decompression gas source switch 13 and enters the wheeled equipment 33 and the rescue airbag equipment 32, so as to meet the emergency pressurization of different equipment.

[0070] Example 6:

[0071] See Figure 5 , the specific process of the auxiliary fuel tank fuel pumping and discharging control is as follows:

[0072] When using the direct pumping and discharging method:

[0073] This method is to pump and drain fuel by connecting to the gravity fuel filling port 37 of the auxiliary fuel tank. This pumping and draining mode requires opening the gravity fuel filling port cover and extending the oil suction hose to the bottom of the auxiliary fuel tank through the adapter assembly for pumping oil. At this time, the conditions for pressurizing the auxiliary fuel tank are not met, and the oil pumping efficiency is moderate.

[0074] During the specific pumping and draining process, connect the third quick-disconnect joint 19 of the hydraulic pumping and draining system to the gravity fuel filling port 37 of the auxiliary fuel tank through the oil suction hose and extend it to the bottom of the auxiliary fuel tank. Then, start the explosion-proof motor pump set 20, and suck the fuel inside the auxiliary fuel tank into the flexible oil bag 28 through the explosion-proof motor pump set 20.

[0075] Example 7:

[0076] See Figure 6 , when the indirect pumping and draining method is adopted:

[0077] First, pressurize the auxiliary fuel tank with compressed air. When the pressurizing air pressure in the auxiliary fuel tank reaches the pressure for delivering fuel to the on-board fuel supply and transfer system 36, the oil in the auxiliary fuel tank is transported to the on-board fuel supply and transfer system 36 through the internal fuel transfer pipeline. At this time, connect to the hydraulic pumping and draining system through the quick-disconnect joint of the aircraft fuel filling interface 34, and then suck out the fuel in the auxiliary fuel tank to achieve the purpose of pressurizing and draining the auxiliary fuel tank. This pumping and draining mode is carried out under the condition of pressurizing the auxiliary fuel tank, and the oil pumping efficiency is relatively high.

[0078] Example 8:

[0079] Main technical parameters:

[0080] 1) Equipment power supply: AC220V / 50Hz, DC28V;

[0081] 2) Maximum oil pumping flow rate: 300 L / min;

[0082] 3) Oil pumping and conveying pressure: ≤0.3 MPa;

[0083] 4) Maximum output pressure of the compressed air booster pump: 30 MPa, adjustable;

[0084] 5) Maximum output flow rate of the compressed air booster pump: 140 L / min;

[0085] 6) Output pressure of the gas decompression branch: (0 - 0.3) MPa, adjustable;

[0086] 7) Continuous working time: ≥3 h;

[0087] 8) Cable length: ≥10 m;

[0088] 9) Oil pipe length: The oil suction pipe connected to the aircraft ≥10 m, and the oil storage and transfer pipe ≤20 m.

[0089] Environmental requirements:

[0090] Working state: Temperature: 10°C to 35°C; Relative humidity: ≤90%;

[0091] Non - working state: Temperature: - 40°C to 55°C.

Claims

1. The boost oil delivery inspection system is characterized by: The invention comprises an air circuit system for supplying air, wherein the air circuit system uses an air booster pump (1) as a power source, thereby compressing air into air sources of different pressure levels, thereby realizing filling and pressurizing of the auxiliary fuel tank, and is used for pressure filling of wheeled equipment / rescue airbags; The invention also comprises a hydraulic pumping system, wherein the hydraulic pumping system uses an explosion-proof motor pump group (20) as a power source for pumping out fuel from the auxiliary fuel tank, thereby realizing rapid pumping out of the oil in the auxiliary fuel tank through the oil drain pipe and the gravity refueling interface.

2. The pressurized oil delivery inspection system according to claim 1, characterized in that: The gas circuit system comprises an air booster pump (1), the outlet of the air booster pump (1) is connected to a first one-way valve (2), the pipeline after the first one-way valve (2) is connected in sequence to a system output switch (7), an air filter (8), a pressure reducing valve (9) and a pressure reducing gas source switch (13), and the other end of the pressure reducing gas source switch (13) is connected to a pressure reducing gas source output port (18); An air source pressure switch (12) is connected between the air filter (8) and the pressure reducing valve (9), and the other end of the air source pressure switch (12) is connected to the air source pressure output port (17).

3. The pressurized oil delivery inspection system according to claim 2, characterized in that: A buffer gas cylinder (6) is connected between the first one-way valve (2) and the system output switch (7); A first in-situ metering interface (3), a first gas source pressure gauge (4) and a first pressure sensor (5) are also connected between the first one-way valve (2) and the system output switch (7).

4. The pressurized oil delivery inspection system according to claim 2, characterized in that: It also includes a factory gas source interface (16) and a standard gas source interface (15), and the factory gas source interface (16) and the standard gas source interface (15) are respectively connected to the system output switch (7) through a one-way valve.

5. The pressurized oil delivery inspection system according to claim 2, characterized in that: A first safety valve (14) is connected between the pressure reducing valve (9) and the pressure reducing gas source switch (13); A second in-situ metering interface, a second gas source pressure gauge (10) and a second pressure sensor (11) are also connected between the pressure reducing valve (9) and the pressure reducing gas source switch (13).

6. The pressurized oil delivery inspection system according to claim 1, characterized in that: The hydraulic pumping system comprises an explosion-proof motor pump unit (20), the inlet of which is connected to the soft oil bag (28) via a second one-way valve (22), a first quick-release joint (25), a second quick-release joint (26), and an oil delivery hose (27); The outlet of the explosion-proof motor pump unit (20) is connected to the auxiliary oil tank via a third quick-release connector (19).

7. The pressurized oil delivery inspection system according to claim 6, characterized in that: The explosion-proof motor pump unit (20) is connected in parallel with a second safety valve (21); A third in-situ metering interface (24) and a third pressure sensor (23) are connected between the second one-way valve (22) and the first quick-release connector (25).

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