Hydraulic control system of liquid cooling cleaning vehicle

Abstract

The utility model discloses a hydraulic control system of a liquid cooling cleaning vehicle, which relates to the technical field of liquid cooling cleaning and comprises an oil tank, an airplane cleaning oil way and a cleaning oil return loop. Two ports of the cleaning oil return loop are connected with an oil tank and an oil return port of an aircraft flushing pipeline respectively, and an oil absorption coarse filter, a centrifugal pump set, an oil absorption fine filter and an electric proportional throttle valve are sequentially arranged on an aircraft cleaning oil way in the flowing direction of oil. The cleaning oil return pipeline is sequentially provided with an air cooling radiator and an oil return filter in the oil backflow direction, the automation degree is high, operation is easy, and reliability and universality are good.

Description

Technical Field

[0001] The utility model relates to the technical field of liquid cooling cleaning, in particular to a hydraulic control system of a liquid cooling cleaning vehicle. Background Art

[0002] Liquid-cooled cleaning vehicles are used on the ground to provide a hydraulic source that meets the requirements for the hydraulic system of a certain aircraft, or the hydraulic system of an aircraft with similar hydraulic parameters. This allows for oil leak testing and related testing, as well as performance inspections, including testing of nose and main takeoff and retraction, nose wheel steering, braking, and flap retraction. Currently, liquid-cooled cleaning vehicles are used for aircraft environmental control. Utility Model Content

[0003] The purpose of the utility model is to overcome the deficiencies of the prior art and provide a hydraulic control system for a liquid-cooled cleaning vehicle, which has a high degree of automation, is easy to operate, and has good reliability and versatility.

[0004] The purpose of the utility model is achieved through the following technical solutions: a hydraulic control system of a liquid-cooled washing vehicle, comprising a fuel tank, an aircraft washing oil circuit and a washing oil return circuit, wherein the two ports of the aircraft washing oil circuit are respectively connected to the fuel tank and the oil inlet port of the aircraft washing pipeline, and the two ports of the washing oil return circuit are respectively connected to the fuel tank and the oil return port of the aircraft washing pipeline, and the aircraft washing oil circuit is provided with an oil suction coarse filter, a centrifugal pump group, an oil suction fine filter, and an electric proportional throttle valve in sequence along the flow direction of the oil, and the washing oil return pipeline is provided with an air-cooled radiator and an oil return filter in sequence along the return direction of the oil.

[0005] Furthermore, it also includes a self-cleaning pipeline, one end of which is connected to the oil outlet end of the aircraft cleaning oil circuit, and the other end is connected to the oil return port of the cleaning oil return circuit.

[0006] Furthermore, the self-cleaning pipeline is provided with a solenoid valve and a manual ball valve, and the solenoid valve and the manual ball valve are connected to the self-cleaning pipeline in parallel.

[0007] Furthermore, it also includes an aircraft drainage circuit, one end of which is connected to the air source, and the other end is connected to the oil inlet port of the aircraft flushing pipeline.

[0008] Furthermore, the aircraft drainage circuit is provided with a filter, a pressure reducing valve, a manual pressure regulating valve, a pressure transmitter, a one-way valve and a needle valve in sequence along the airflow direction.

[0009] Furthermore, it also includes an aircraft filling circuit, the oil outlet end of the aircraft cleaning oil circuit is connected to a three-way ball valve, and the aircraft filling circuit is connected to the three-way ball valve.

[0010] Furthermore, it also includes an oil replenishment circuit, the oil replenishment outlet of the oil replenishment circuit is connected to the oil tank, and the oil replenishment circuit is sequentially provided with a replenishment pump group and an oil replenishment one-way valve along the flow direction of the oil.

[0011] Furthermore, a safety overflow valve and a proportional overflow valve are provided on the aircraft cleaning oil circuit. The safety overflow valve is located between the centrifugal pump group and the oil suction fine filter, and the proportional overflow valve is located between the electric proportional throttle valve and the three-way ball valve. A flow meter and a pressure transmitter a are also provided between the proportional overflow valve and the three-way ball valve.

[0012] Furthermore, the cleaning oil return circuit is provided with an online contamination detector.

[0013] Furthermore, the oil tank is provided with a sampling valve, a temperature transmitter, an oil drain valve and a liquid level gauge.

[0014] The beneficial effects of the utility model are:

[0015] 1. The oil in the fuel tank enters the aircraft flushing pipeline through the aircraft cleaning oil circuit, and then returns to the fuel tank through the cleaning return oil circuit, realizing the circulation cleaning of the aircraft environmental control liquid cooling system pipeline.

[0016] 2. Blow air into the aircraft or external equipment pipeline through the aircraft drainage circuit, so that the residual liquid in the pipeline is discharged into the fuel tank through the cleaning return oil circuit, completing the drainage and cleaning of the equipment pipeline.

[0017] 3. The whole process is hydraulically controlled, with high degree of automation, simple operation, good reliability and versatility. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic diagram of a hydraulic control system of a liquid-cooled cleaning vehicle of the present invention;

[0019] Figure 2 This is a device outline diagram of a hydraulic control system for a liquid-cooled cleaning vehicle according to the present invention;

[0020] In the figure, 1- oil tank, 2- oil suction coarse filter, 4- centrifugal pump group, 5- oil suction fine filter, 6- electric proportional throttle valve, 7- proportional relief valve, 9- flow meter, 11- pressure transmitter a, 12- three-way ball valve, 13- liquid supply port, 14- oil return port, 15- solenoid valve, 16- manual ball valve, 18- online contamination detector, 19- air-cooled radiator, 20- safety relief valve, 21- oil return filter, 22- oil supply check valve, 23- liquid supply pump group, 24- liquid supply port, 25- oil receiving tray, 26- liquid level gauge, 27- temperature transmitter, 28- gas source, 29- pressure reducing valve, 30- manual pressure regulating valve, 31- pressure transmitter, 32- filter, 33- check valve, 34- needle valve, 35- liquid filling port, 36- oil drain valve, 37- sampling valve. DETAILED DESCRIPTION

[0021] Example 1

[0022] like Figure 1 and Figure 2As shown, a hydraulic control system of a liquid-cooled cleaning vehicle comprises a fuel tank 1, an aircraft cleaning oil circuit and a cleaning oil return circuit. The two ports of the aircraft cleaning oil circuit are respectively connected to the fuel tank 1 and the oil inlet port of the aircraft flushing pipeline, that is, the oil outlet end of the aircraft cleaning oil circuit is a liquid supply port 13, and the two ports of the cleaning oil return circuit are respectively connected to the fuel tank 1 and the return oil port of the aircraft flushing pipeline. The return oil port of the cleaning oil return circuit is the return oil port, and an oil receiving pan 25 is provided at the return oil port. An oil suction coarse filter 2, a centrifugal pump group 4, an oil suction fine filter 5, and an electric proportional throttle valve 6 are sequentially provided along the flow direction of the oil in the aircraft cleaning oil circuit. An air-cooled radiator 19 and an oil return filter 21 are sequentially provided along the return direction of the oil in the cleaning oil return pipeline. When cleaning the aircraft's pipelines, the liquid supply port 13 at the end of the aircraft's cleaning oil circuit is connected to the liquid inlet of the aircraft's pipeline to be cleaned, the oil return port of the cleaning oil return circuit is connected to the liquid outlet of the pipeline to be cleaned, the centrifugal pump group 4 is started, the oil in the fuel tank 1 is filtered for the first time through the oil suction coarse filter 2, and then filtered for the second time through the oil suction fine filter 5, and then the oil is pressure-regulated by the electric proportional throttle valve 6 to enter the pipeline to be cleaned for flushing. After flushing is completed, the oil enters the cleaning oil return circuit, is cooled by the air-cooled radiator 19, and is filtered by the return oil filter 21 before returning to the fuel tank 1. In this way, the cyclic flushing of the pipeline to be cleaned is realized, and the circulation is realized by hydraulic means, which has a high degree of automation, simple operation and good reliability. It's worth noting that the aircraft flushing line doesn't refer to a specific line, but rather the line to be cleaned. Simply connecting the two ends of the line to be cleaned to the aircraft's flushing oil circuit and the flushing oil return circuit, respectively, allows for cyclic flushing, enhancing versatility. Centrifugal pump unit 4 utilizes a multi-stage centrifugal pump, whose pressure is regulated by a variable-frequency motor. This can be accomplished using a pressure adjustment knob on the front panel, or by setting the desired pressure directly in the PLC system control program. The PLC then directly controls the inverter to achieve the desired pressure. The pressure adjustment range is linearly adjustable between 0 and 1.5 MPa.

[0023] Furthermore, if Figure 1As shown, the aircraft cleaning oil circuit is equipped with a safety relief valve 20 and a proportional relief valve 7. The safety relief valve 20 is located between the centrifugal pump unit 4 and the oil suction fine filter 5, while the proportional relief valve 7 is located between the electric proportional throttle valve 6 and the three-way ball valve 12. A flow meter 9 and a pressure transmitter a11 are also installed between the proportional relief valve 7 and the three-way ball valve 12. The pressure transmitter a11 measures the oil supply pressure to ensure smooth oil suction by the centrifugal pump unit 4 and hydraulic system safety. When the output pressure of the centrifugal pump unit 4 exceeds the system operating pressure, the safety relief valve 20 and the proportional relief valve 7 open, allowing the oil to overflow back to the tank. To comply with the working medium, military aviation coolant No. 65, all components are sealed to ensure compatibility with this medium. When the test equipment is supplied with pressure, when the oil supply pressure reaches 1.6 MPa, the safety relief valve 20 and the proportional relief valve 7 open to relieve pressure, thereby ensuring the safety of the test equipment. Safety relief valve 20 uses RA series safety relief valve, which is used to limit the pressure of liquid or gas system to prevent the pressure in the system from exceeding the preset safety value (set pressure). When the inlet pressure exceeds the set value, the inlet pressure is relieved through the outlet.

[0024] Furthermore, the cleaning oil return circuit is provided with an online contamination detector 18 for detecting the size and quantity of solid particles in the liquid; a sampling valve 37, a temperature transmitter 27, an oil drain valve 35 and a liquid level meter 26 are provided on the oil tank 1. The temperature transmitter measures the oil temperature in the oil tank 1 and controls the start and stop of the air-cooled radiator 19 according to the oil temperature. When the set temperature is exceeded, an alarm indication is given and the cleaning vehicle is shut down to ensure the safety of the equipment. The temperature transmitter 27 adopts TA-200; when it is necessary to detect the solid contamination degree of the oil in the oil tank 1, the oil sample is collected for testing through the sampling valve 37, which should meet the GJB420B-7 level requirements; the sampling valve 37 adopts an NV stainless steel needle-type stop valve, which can adjust the flow rate and play a throttling and shut-off role.

[0025] Example 2

[0026] Based on the first embodiment, Figure 1As shown, the system also includes a self-cleaning line, one end of which is connected to the oil outlet of the aircraft wash oil circuit and the other end to the oil return port of the wash return oil circuit. A solenoid valve 15 and a manual ball valve 16 are installed in the self-cleaning line, connected in parallel. The solenoid valve 15 and the manual ball valve 16 are connected to the self-cleaning line in parallel. The detection results of an online contamination detector 18 determine whether to activate the self-cleaning line. When the oil cleanliness needs to be improved, the solenoid valve 15 automatically opens or the manual ball valve 16 is manually opened, connecting the aircraft wash oil circuit and the wash return oil circuit, allowing the oil to self-circulate and clean. Oil filters equipped with transmitters (oil fine filter 5, oil coarse filter 2, and return oil filter 21) are installed in the aircraft wash oil circuit and the wash return oil circuit to filter out solid particles, thereby achieving a high particle contamination index. When the contamination level of the test equipment hydraulic system exceeds the standard, the self-cleaning line is connected to enable the system to self-circulate and clean. The oil filter uses a Liming Hydraulics Y-series line filter, installed in the hydraulic system's return oil line. It removes solid particles and colloidal matter from the working medium, effectively controlling contamination. It features a magnetic assembly and an indicator. A self-sealing valve and other devices are incorporated into the filter, eliminating the need for other piping components such as stop valves. To replace or clean the filter element or perform system maintenance, simply unscrew the filter cap (cleaning cover). The self-sealing valve automatically closes, isolating the oil line from the tank and preventing oil from escaping. This makes cleaning, filter element replacement, and system maintenance very convenient.

[0027] Example 3

[0028] Based on the second embodiment, Figure 1 As shown, the aircraft drainage circuit also includes an aircraft drainage circuit, one end of which is connected to the air source 28, and the other end is connected to the oil inlet port of the aircraft flushing pipeline. The aircraft drainage circuit is sequentially provided with a filter 32, a pressure reducing valve 29, a manual pressure regulating valve 30, a pressure transmitter 31, a one-way valve 33 and a needle valve 34 along the air flow direction. The drainage gas is provided by the air source 28. When the pipeline needs to be drained, the air source 28 is started to allow gas to enter the pipeline for blowing liquid, so that the residual liquid in the pipeline is discharged into the oil tank through the cleaning return oil circuit, completing the drainage and cleaning of the equipment pipeline.

[0029] Example 4

[0030] Based on the third embodiment, Figure 1 As shown, it also includes an aircraft filling circuit. The oil outlet end of the aircraft cleaning oil circuit is connected to a three-way ball valve 12. The aircraft filling circuit is connected to the three-way ball valve 12. The end of the aircraft filling circuit is a liquid filling port 35. A small amount of coolant with a small flow rate is added to the aircraft auxiliary fuel tank. The conduction and closing of the aircraft filling circuit are controlled by the three-way ball valve 12.

[0031] Example 5

[0032] Based on the fourth embodiment, Figure 1 As shown, it also includes an oil replenishing circuit, the oil replenishing outlet of the oil replenishing circuit is connected to the oil tank 1, and the oil replenishing circuit is provided with a replenishing pump group 23 and an oil replenishing one-way valve 22 in sequence along the flow direction of the oil. The oil is replenished to the oil tank 1 of the liquid-cooled cleaning vehicle itself, and the oil is sucked into the oil tank 1 by a motor. The liquid level detected by the liquid level meter 26 is used to determine whether the oil tank 1 needs to be replenished.

Claims

1. A hydraulic control system for a liquid-cooled cleaning vehicle, characterized in that: The invention comprises an oil tank (1), an aircraft cleaning oil circuit and a cleaning oil return circuit, wherein the two ports of the aircraft cleaning oil circuit are respectively connected to the oil tank (1) and the oil inlet port of the aircraft flushing pipeline, and the two ports of the cleaning oil return circuit are respectively connected to the oil tank (1) and the oil return port of the aircraft flushing pipeline. An oil suction coarse filter (2), a centrifugal pump group (4), an oil suction fine filter (5), and an electric proportional throttle valve (6) are sequentially arranged along the flow direction of the oil on the aircraft cleaning oil circuit, and an air-cooled radiator (19) and an oil return filter (21) are sequentially arranged along the return direction of the oil on the cleaning oil return pipeline.

2. The hydraulic control system of a liquid-cooled cleaning vehicle according to claim 1, characterized in that: It also includes a self-cleaning pipeline, one end of which is connected to the oil outlet end of the aircraft cleaning oil circuit, and the other end is connected to the oil return port of the cleaning oil return circuit.

3. The hydraulic control system of a liquid-cooled cleaning vehicle according to claim 2, characterized in that: The self-cleaning pipeline is provided with a solenoid valve (15) and a manual ball valve (16), and the solenoid valve (15) and the manual ball valve (16) are connected to the self-cleaning pipeline in parallel.

4. The hydraulic control system of a liquid-cooled cleaning vehicle according to claim 1, characterized in that: It also includes an aircraft drainage circuit, one end of which is connected to an air source (28), and the other end of which is connected to an oil inlet port of the aircraft flushing pipeline.

5. The hydraulic control system of a liquid-cooled cleaning vehicle according to claim 4, characterized in that: The aircraft drainage circuit is provided with a filter (32), a pressure reducing valve (29), a manual pressure regulating valve (30), a pressure transmitter (31), a one-way valve (33) and a needle valve (34) in sequence along the airflow direction.

6. The hydraulic control system of a liquid-cooled cleaning vehicle according to claim 1, characterized in that: It also includes an aircraft filling circuit, wherein the oil outlet end of the aircraft cleaning oil circuit is connected to a three-way ball valve (12), and the aircraft filling circuit is connected to the three-way ball valve (12).

7. The hydraulic control system of a liquid-cooled cleaning vehicle according to claim 1, characterized in that: It also includes an oil replenishment circuit, the oil replenishment outlet of the oil replenishment circuit is connected to the oil tank (1), and the oil replenishment circuit is sequentially provided with a replenishment pump group (23) and an oil replenishment one-way valve (22) along the flow direction of the oil.

8. The hydraulic control system of a liquid-cooled cleaning vehicle according to claim 6, characterized in that: The aircraft cleaning oil circuit is provided with a safety overflow valve (20) and a proportional overflow valve (7). The safety overflow valve (20) is located between the centrifugal pump group (4) and the oil absorption fine filter (5). The proportional overflow valve (7) is located between the electric proportional throttle valve (6) and the three-way ball valve (12). A flow meter (9) and a pressure transmitter a (11) are also provided between the proportional overflow valve (7) and the three-way ball valve (12).

9. The hydraulic control system of a liquid-cooled cleaning vehicle according to claim 1, characterized in that: The cleaning oil return circuit is provided with an online contamination detector (18).

10. The hydraulic control system of a liquid-cooled cleaning vehicle according to claim 1, characterized in that: The oil tank (1) is provided with a sampling valve (37), a temperature transmitter (27), an oil drain valve (35) and a liquid level meter (26).

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