Airplane hydraulic oil tank ground supercharger device

Abstract

The utility model relates to an airplane hydraulic oil tank ground supercharger device which comprises a box body, a switch assembly and a display assembly are arranged on the box body, portable assemblies convenient to carry are arranged on the two sides of the box body, and a supercharging connector is arranged at the top of the box body. The gas supply system and the pressure reduction system are distributed in the tank body, and the pressure reduction system injects gas into the oil tank in a two-stage pressure reduction mode so as to ensure that the pressure of the injected gas does not exceed the standard pressure of the oil tank and the oil tank can be rapidly filled with the gas. The aircraft fuel tank is inflated through the first-stage pressure reducing valve and the second-stage pressure reducing valve, rapid inflation can be carried out through the first-stage pressure reducing valve, and pressure is accurately adjusted through the second-stage pressure reducing valve to prevent the aircraft fuel tank from being damaged due to too high pressure; alarm pressure is set through the safety valve, and when the oil tank reaches the alarm pressure, if the deflation valve is not opened, overpressure gas is automatically released through the safety valve.

Description

Technical Field

[0001] This utility model relates to the field of aircraft testing equipment, specifically to a ground pressurization device for aircraft hydraulic oil tanks. Background Technology

[0002] Currently, the equipment used for pressurizing aircraft hydraulic tanks is a comprehensive test bench, a large-scale integrated laboratory device. The control components and air source equipment are integrated, resulting in a bulky size that is inconvenient for relocation and use, and the nitrogen filling and pressure regulation are inaccurate. There is a need to design a miniaturized pressurization device with high-precision, high-stability pressure regulation performance to improve relocation efficiency and ensure stable and reliable operation. Summary of the Invention

[0003] To address the aforementioned technical problems, this utility model proposes a ground-based pressurization device for aircraft hydraulic oil tanks. The technical problem to be solved by this utility model is achieved through the following technical solution:

[0004] A ground pressurization device for aircraft hydraulic oil tanks includes a housing, a switch assembly and a display assembly on the housing, carrying handles on both sides of the housing for easy carrying, and a pressurization interface on the top of the housing.

[0005] It also includes a gas supply system and a pressure reduction system distributed within the tank. The pressure reduction system injects gas into the tank through a two-stage pressure reduction process to ensure that the injected gas pressure does not exceed the standard pressure of the tank and that the tank can be quickly filled.

[0006] The gas supply system includes a gas source connector connected to a gas source, the gas source connector being connected to a gas filter via a pipeline, and the gas filter being connected to a pressure reducing system via a pipeline.

[0007] The pressure reduction system includes a primary pressure reducing valve connected to the air filter via a pipeline, a control component connected to the primary pressure reducing valve via a pipeline, a secondary pressure reducing valve connected to the control component via a pipeline, and a pressure boosting interface connected to the control component via a pipeline.

[0008] The control component is connected to the pressurization interface via a pipeline with a vent valve, and is also connected to a safety valve via a pipeline. The safety valve is connected to the display component.

[0009] The control assembly includes a fast-charging valve connected to a primary pressure reducing valve via a pipeline, and a sealing valve connected to a secondary pressure reducing valve.

[0010] The switching assembly includes a sealing switch connected to a sealing valve, a venting switch connected to a venting valve, and a fast-charging switch connected to a fast-charging valve.

[0011] The beneficial effects of this utility model are as follows: This utility model performs the inflation operation of the aircraft fuel tank through a primary pressure reducing valve and a secondary pressure reducing valve. The primary pressure reducing valve allows for rapid inflation, while the secondary pressure reducing valve allows for precise pressure adjustment to prevent excessive pressure from damaging the aircraft fuel tank. This utility model also features an alarm pressure setting via a safety valve. If the vent valve is not opened when the fuel tank reaches the alarm pressure, the overpressured gas will be automatically released through the safety valve. Attached Figure Description

[0012] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0013] Figure 1 This is a schematic diagram of the pipeline structure of this utility model;

[0014] Figure 2 This is a front view of the present invention;

[0015] Figure 3 This is a rear view of the present invention.

[0016] The diagram shows: 1. Housing; 2. Switch assembly; 3. Display assembly; 4. Handle assembly; 5. Pressure boosting interface; 6. Air supply system; 7. Pressure reducing system; 8. Venting valve; 9. Safety valve; 61. Air source connector; 62. Air filter; 21. Sealing switch; 22. Venting switch; 23. Fast charging switch; 71. Primary pressure reducing valve; 72. Control assembly; 73. Secondary pressure reducing valve; 74. Fast charging valve; 75. Sealing valve. Detailed Implementation

[0017] To enable those skilled in the art to better understand the technical solution of this utility model, the present utility model will be described more clearly and completely below with reference to the accompanying drawings in the embodiments. Of course, the described embodiments are only a part of the present utility model and not all of them. Based on this embodiment, other embodiments obtained by those skilled in the art without creative effort are all within the protection scope of this utility model.

[0018] like Figures 1 to 3 As shown, an aircraft hydraulic oil tank ground pressurization device includes a housing 1, a switch assembly 2 and a display assembly 3 on the housing 1, carrying handles 4 on both sides of the housing 1 for easy carrying, a pressurization port 5 on the top of the housing 1, and the display assembly 3 displays the oil tank pressure.

[0019] It also includes a gas supply system 6 and a pressure reduction system 7 distributed within the housing 1. The pressure reduction system 7 injects gas into the oil tank through a two-stage pressure reduction method to ensure that the injected gas pressure does not exceed the standard pressure of the oil tank and can quickly fill the oil tank.

[0020] The gas supply system 6 includes a gas source connector 61 connected to a gas source. The gas source connector 61 is connected to a gas filter 62 via a pipeline. The gas filter 62 is connected to a pressure reducing system 7 via a pipeline.

[0021] The pressure reduction system 7 includes a primary pressure reducing valve 71 connected to the air filter 62 via a pipeline. The primary pressure reducing valve 71 is connected to a control component 72 via a pipeline. The control component 72 is connected to a secondary pressure reducing valve 73 via a pipeline. The control component 72 is connected to the pressurization interface 5 via a pipeline. Traditional testing equipment only has a primary pressure reducing valve 71, and the delivery pressure is greater than the aircraft fuel tank pressure. It requires manual pressure control, which can easily lead to insufficient or excessive pressure, affecting test data or even damaging the aircraft fuel tank. In this invention, the primary pressure reducing valve 71 and the fast-charging valve 74 work together to quickly inflate the fuel tank. When the pressure approaches the critical value of the aircraft fuel tank pressure, the fast-charging valve 74 is closed and the sealing valve 75 is opened. Gas enters the aircraft fuel tank through the secondary pressure reducing valve 73. The pressure of the secondary pressure reducing valve 73 is set to be equal to the critical pressure of the aircraft fuel tank and the gas is introduced slowly to prevent damage to the aircraft fuel tank due to excessive pressure during the inflation and pressure holding test. At the same time, the inflation pressure can be precisely controlled.

[0022] The control component 72 is connected to the pressurization interface 5 via a pipeline with a vent valve 8 and a safety valve 9, which is connected to the display component 3. After the pressure holding test is completed, the vent valve 8 is opened to release the gas in the aircraft fuel tank. The safety valve 9 is set with an alarm pressure value. If overpressure occurs during the test and the vent valve 8 is not opened, the overpressure gas can be directly discharged through the safety valve 9 to prevent the pressure in the aircraft fuel tank from becoming too high.

[0023] The control component 72 includes a fast-charging valve 74 connected to a primary pressure reducing valve 71 via a pipeline, and a sealing valve 75 connected to a secondary pressure reducing valve 73.

[0024] The switching assembly 2 includes a sealing switch 21 connected to the sealing valve 75, a venting switch 22 connected to the venting valve 8, and a fast charging switch 23 connected to the fast charging valve 74.

[0025] The present invention includes the following embodiments:

[0026] Example 1

[0027] a. Turn off the fast charging switch 23, sealing switch 21, and venting switch 22. Connect the booster port 5 to the fuel tank and the air source connector 61 to the QPC-4 type air-conditioned trailer.

[0028] b. Supply air to the air-conditioned trailer and open the booster sealing switch 21. The booster will pressurize the fuel tank, at which point the fuel tank pressure will increase slowly. To increase the boost speed, slowly open the fast-charging switch 23. Since the fast-charging switch 23 has an intake pressure of 5 MPa, you must use both hand and eye coordination, constantly observing the display component 3. When the display component 3 indicates 0.078 MPa, close the fast-charging switch 23. When the display component 3 indicates 0.082 MPa, close the sealing switch 21. Check the fuel tank booster system's sealing performance at the specified intervals.

[0029] c. After the airtightness test is completed, the air supply to the air-conditioned trailer should be disconnected first, then the venting switch 22 and the sealing switch 21 should be opened, and the pressurization port 5 should be loosened to release the air. When the display component 3 indicates 0 MPa, the air source connector 61 and the pressurization port 5 can be removed.

[0030] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. An aircraft hydraulic fluid tank ground boost apparatus, comprising: Including box (1), be equipped with on the box (1) switch subassembly (2) and display subassembly (3), both sides are equipped with portable subassembly (4) on the box (1) to facilitate carrying, the box (1) top is equipped with booster interface (5); Still including the gas supply system (6) and pressure reducing system (7) distributed in the box (1), the pressure reducing system (7) is injected into the gas tank by two-stage pressure reducing mode, to ensure that the injected gas pressure does not exceed the standard pressure of the oil tank and can quickly fill the oil tank.

2. An apparatus for ground pressurizing an aircraft hydraulic reservoir in accordance with claim 1, wherein: The gas supply system (6) includes a gas source connector (61) connected to a gas source, the gas source connector (61) is connected with a gas filter (62) through a pipeline, and the gas filter (62) is connected with the pressure reducing system (7) through a pipeline.

3. An aircraft hydraulic fluid tank ground boost gauge apparatus as defined in claim 2, wherein: The pressure reducing system (7) includes a primary pressure reducing valve (71) connected to the gas filter (62) through a pipeline, the primary pressure reducing valve (71) is connected with a control assembly (72) through a pipeline, the control assembly (72) is connected with a secondary pressure reducing valve (73) through a pipeline, and the control assembly (72) is connected with the booster interface (5) through a pipeline.

4. An apparatus for ground pressurizing an aircraft hydraulic reservoir in accordance with claim 3, wherein: The control assembly (72) and the booster interface (5) are connected through a pipeline with a gas release valve (8), and are also connected through a pipeline with a safety valve (9), and the safety valve (9) is connected with the display assembly (3).

5. An apparatus for ground pressurizing an aircraft hydraulic reservoir in accordance with claim 4, wherein: The control assembly (72) includes a fast-charging valve (74) connected to the primary pressure reducing valve (71) through a pipeline, and also includes a sealing valve (75) connected to the secondary pressure reducing valve (73).

6. An aircraft hydraulic fluid tank ground boost gauge apparatus as defined in claim 5, wherein: The switch subassembly (2) includes a sealing switch (21) connected to the sealing valve (75), a gas release switch (22) connected to the gas release valve (8), and a fast-charging switch (23) connected to the fast-charging valve (74).

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