CN216009054U - Hydraulic system of aircraft hydraulic fuelling vehicle - Google Patents
Hydraulic system of aircraft hydraulic fuelling vehicle Download PDFInfo
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- CN216009054U CN216009054U CN202122242094.1U CN202122242094U CN216009054U CN 216009054 U CN216009054 U CN 216009054U CN 202122242094 U CN202122242094 U CN 202122242094U CN 216009054 U CN216009054 U CN 216009054U
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Abstract
A hydraulic system of an aircraft hydraulic fuelling vehicle comprising: the oil storage device is used for storing hydraulic oil; the oil pumping device is used for pumping hydraulic oil out and injecting the hydraulic oil into an aircraft hydraulic system; a flow control device for controlling the amount of hydraulic oil injected into the hydraulic system of the aircraft.
Description
Technical Field
The utility model relates to an aircraft filling device especially relates to an aircraft hydraulic pressure refuels and hydraulic system.
Background
The traditional filling mode of the hydraulic oil of the airplane is gravity filling, the labor intensity of crew is high, the hydraulic oil pollution is easily caused, the airplane has faults of automatic air rod reversing, air swinging, brake lateral deviation and failure, short service life of a hydraulic pump and the like due to the oil pollution of a hydraulic system, and the control of the pollution degree of a hydraulic oil source during the oil filling is an effective important measure. In the use process of an airplane, the sealing of a hydraulic system of the airplane is poor, hydraulic oil leaks, the hydraulic oil needs to be supplemented frequently, the hydraulic oil refueling equipment matched with a user at present cannot be used for quantitatively refueling, and crew staff need to observe the liquid level of an oil tank at any time. Therefore, the hydraulic oil refueling truck is designed for supplying hydraulic oil and replenishing oil to the airplane, the hydraulic oil is filtered and cleaned and then is injected into a hydraulic system, and the pollution of the hydraulic oil to the airplane hydraulic system is avoided.
The hydraulic system as the main part of the hydraulic fuelling vehicle has the problems of insufficient cleanliness of added hydraulic oil, complex structure, more parts, high processing and mounting difficulty and the like.
Disclosure of Invention
In order to solve at least one among the above-mentioned technical problem, the utility model provides an aircraft hydraulic pressure tank service truck's hydraulic system, it is when satisfying carrying out accurate refueling to aircraft hydraulic system, has simplified hydraulic system structure and part and has constituteed.
In order to achieve the above purpose, the utility model adopts the following technical scheme: a hydraulic system of an aircraft hydraulic fuelling vehicle comprising:
the oil storage device is used for storing hydraulic oil;
the oil pumping device is used for pumping hydraulic oil out and injecting the hydraulic oil into an aircraft hydraulic system;
a flow control device for controlling the amount of hydraulic oil injected into the hydraulic system of the aircraft.
Preferably, the oil storage device includes the oil tank, set up the level gauge that is arranged in the oil tank and is arranged in carrying out the monitoring to the liquid level of hydraulic oil in the oil tank, set up the fuel outlet valve that is arranged in the oil tank bottom and is used for discharging hydraulic oil, set up the air cleaner that is arranged in going on filtering to the air that gets into in the oil tank at oil tank top and set up on oil tank upper portion and be arranged in the hydraulic oil tank truck the inside hydraulic oil that carries out internal circulation of hydraulic oil system is from the circulation interface.
Preferably, the oil pumping device comprises a hydraulic oil filter, an oil suction valve, a pump assembly, a one-way valve, a filter and an oil filling joint which are sequentially connected through a main oil path, the hydraulic oil filter is located at an oil outlet of the oil tank, and the oil filling joint is used for being connected with an inlet of a hydraulic system of the airplane so as to inject hydraulic oil into the hydraulic system of the airplane.
Preferably, the flow control device comprises a pressure measuring component, a safety valve, a flow meter, a pressure relay and an electromagnetic valve, the pressure measuring component is arranged on an oil path between the filter and the oil filling connector, the flow meter is arranged on an oil path between the pressure measuring component and the oil filling connector, an oil return path inlet is arranged on the oil path between the oil filling connector and the flow meter, an outlet of the oil return path is communicated with the oil tank, one end of the safety valve is communicated with a main oil path between the pressure measuring component and the flow meter, and the other end of the safety valve is communicated with the oil return path; one end of the electromagnetic valve is communicated with the main oil way, the other end of the electromagnetic valve is communicated with the oil return way, and the pressure relay controls the electromagnetic valve to be opened and closed according to the pressure of the main oil way.
Preferably, the hydraulic system further comprises a sampling valve arranged on the oil return path and used for removing the hydraulic oil from the hydraulic system so as to detect the cleanliness of the hydraulic oil.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the principles of the invention.
Fig. 1 shows a schematic diagram of a hydraulic system of a hydraulic fuelling vehicle in accordance with an embodiment of the present invention.
The automatic oil filling device comprises a liquid level meter 1, an oil discharging valve 2, a hydraulic oil filter 3, an oil suction valve 4, a pump assembly 5, a one-way valve 6, a filter 7, a pressure measuring assembly 8, a flow meter 9, a pressure relay 10, an oil filling joint 11, an electromagnetic valve 12, a safety valve 13, a sampling valve 14, an air filter 15, a self-circulation interface 16 and an oil tank 17.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the invention. It should be noted that, for convenience of description, only the parts related to the present invention are shown in the drawings.
In the present invention, the embodiments and the features of the embodiments may be combined with each other without conflict. The present invention will be described in detail with reference to the accompanying drawings in conjunction with embodiments.
As shown in fig. 1, a hydraulic system of an aircraft hydraulic fuelling vehicle comprises: the oil storage device is used for storing hydraulic oil; the oil pumping device is used for pumping hydraulic oil out and injecting the hydraulic oil into an aircraft hydraulic system; a flow control device for controlling the amount of hydraulic oil injected into the hydraulic system of the aircraft.
The oil storage device comprises an oil tank 17, a liquid level meter 1 arranged in the oil tank 17 and used for monitoring the liquid level of hydraulic oil in the oil tank, an oil drain valve 2 arranged at the bottom of the oil tank and used for draining the hydraulic oil, an air filter 15 arranged at the top of the oil tank and used for filtering air discharged from the oil tank, and a hydraulic oil self-circulation interface 16 arranged on the upper part of the oil tank and used for internally circulating the hydraulic oil in the oil tank in a hydraulic oil refueling truck hydraulic oil system.
Preferably, the oil pumping device comprises a hydraulic oil filter 3, an oil suction valve 4, a pump assembly 5, a one-way valve 6, a filter 7 and an oil filling joint 11 which are sequentially connected through a main oil path, wherein the hydraulic oil filter 3 is positioned at an oil outlet of the oil tank 17, and the oil filling joint 11 is used for being connected with an inlet of a hydraulic system of the airplane so as to inject hydraulic oil into the hydraulic system of the airplane.
Preferably, the flow rate control device comprises a pressure measuring assembly 8, a safety valve 13, a flow meter 9, a pressure relay 10 and a solenoid valve 12, wherein the pressure measuring assembly 8 is arranged on a main oil path between the filter 7 and the oil filling connector 11, the flow meter 9 is arranged on the main oil path between the pressure measuring assembly 8 and the oil filling connector 11, an oil return path inlet is arranged on the main oil path between the oil filling connector 11 and the flow meter 9, an outlet of the oil return path is communicated with the oil tank 17, one end of the safety valve 13 is communicated with the main oil path between the pressure measuring assembly 8 and the flow meter 9, and the other end of the safety valve 13 is communicated with the oil return path; one end of the electromagnetic valve 12 is communicated with the main oil way, the other end of the electromagnetic valve is communicated with the oil return way, and the pressure relay 10 controls the electromagnetic valve 12 to be opened and closed according to the pressure of the main oil way.
Preferably, the hydraulic system further comprises a sampling valve 14 arranged on the oil return path, and the sampling valve is used for removing the hydraulic oil from the hydraulic system so as to detect the cleanliness of the hydraulic oil.
When hydraulic oil is added to the airplane, the pump assembly 5 is started, and the hydraulic oil is driven by the pump assembly 5 to be pumped to the oil filling connector through the main oil path by the hydraulic oil filter 3 so as to be added to a hydraulic system of the airplane. The pressure measuring assembly detects the pressure of the main oil way, and when the pressure of the main oil way exceeds a certain threshold value, the pressure relay 10 controls the electromagnetic valve 12 to be opened, hydraulic oil in the main oil way is shunted to the backflow oil way, and then the hydraulic oil flows back to the oil tank. Furthermore, when the flow in the main oil line exceeds a safety threshold, the relief valve 13 is opened by the fuelling vehicle control system, returning hydraulic oil to the tank.
This novel design through hydrovalve and solenoid valve and pressure relay has guaranteed the pressure and the flow of the hydraulic oil of joining in the aircraft, has avoided overflowing and extravagant of hydraulic oil, has reduced the risk that hydraulic oil spills over.
Before adding hydraulic oil to the airplane, the pump assembly 5 can be started by connecting the refueling joint 11 with the self-circulation interface 16, the hydraulic oil in the oil tank circulates in the hydraulic system, the hydraulic oil is fully filtered by the fuel filter, and the sampling valve 14 is used for sampling and detecting the hydraulic oil in the hydraulic system, so that the requirement on the purity of the hydraulic oil of the airplane is met.
In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
It should be understood by those skilled in the art that the above embodiments are only for clarity of explanation and are not intended to limit the scope of the present application. Other variations or modifications will occur to those skilled in the art based on the foregoing disclosure and are still within the scope of the present application.
Claims (5)
1. A hydraulic system of an aircraft hydraulic fuelling vehicle comprising:
the oil storage device is used for storing hydraulic oil;
the oil pumping device is used for pumping hydraulic oil out and injecting the hydraulic oil into an aircraft hydraulic system;
a flow control device for controlling the amount of hydraulic oil injected into the hydraulic system of the aircraft.
2. The hydraulic system of claim 1, wherein: the oil storage device comprises an oil tank, a liquid level meter arranged in the oil tank and used for monitoring the liquid level of hydraulic oil in the oil tank, an oil drain valve arranged at the bottom of the oil tank and used for draining the hydraulic oil, an air filter arranged at the top of the oil tank and used for filtering air entering the oil tank and a hydraulic oil self-circulation interface arranged on the upper portion of the oil tank and used for performing internal circulation in the hydraulic oil system of the hydraulic oil refueling truck.
3. The hydraulic system of claim 2, wherein: the oil pumping device comprises a hydraulic oil filter, an oil suction valve, a pump assembly, a one-way valve, a filter and an oil filling connector which are sequentially connected through a main oil way, wherein the hydraulic oil filter is positioned at an oil outlet of the oil tank, and the oil filling connector is used for being connected with an inlet of an airplane hydraulic system so as to inject hydraulic oil into the airplane hydraulic system.
4. A hydraulic system as claimed in claim 3, wherein: the flow control device comprises a pressure measuring component, a safety valve, a flow meter, a pressure relay and an electromagnetic valve, wherein the pressure measuring component is arranged on an oil way between a filter and an oil filling connector, the flow meter is arranged on an oil way between the pressure measuring component and the oil filling connector, an oil return way inlet is arranged on the oil way between the oil filling connector and the flow meter, an outlet of the oil return way is communicated with the oil tank, one end of the safety valve is communicated with a main oil way between the pressure measuring component and the flow meter, and the other end of the safety valve is communicated with the oil return way; one end of the electromagnetic valve is communicated with the main oil way, the other end of the electromagnetic valve is communicated with the oil return way, and the pressure relay controls the electromagnetic valve to be opened and closed according to the pressure of the main oil way.
5. The hydraulic system of claim 4, wherein: the hydraulic system further comprises a sampling valve arranged on the oil return oil way and used for removing the hydraulic oil from the hydraulic system so as to detect the cleanliness of the hydraulic oil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122242094.1U CN216009054U (en) | 2021-09-14 | 2021-09-14 | Hydraulic system of aircraft hydraulic fuelling vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122242094.1U CN216009054U (en) | 2021-09-14 | 2021-09-14 | Hydraulic system of aircraft hydraulic fuelling vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216009054U true CN216009054U (en) | 2022-03-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122242094.1U Active CN216009054U (en) | 2021-09-14 | 2021-09-14 | Hydraulic system of aircraft hydraulic fuelling vehicle |
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| CN (1) | CN216009054U (en) |
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2021
- 2021-09-14 CN CN202122242094.1U patent/CN216009054U/en active Active
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