Test device for emergency release test of aircraft in-flight refueling system

Abstract

The utility model discloses a kind of test devices for aircraft in-flight fuel receiving system emergency release test, comprising: gas supply unit, including sequentially connected gas supply bottle, first stop valve and first solenoid valve;Pressure increasing unit, including pressure increasing pump, the input end of the pressure increasing pump is connected with first solenoid valve, the pressure increasing pump is used to the gas pressure of gas supply unit output is pressurized;Test unit, including sequentially connected gas pressure reducer, first pressure sensor, first pressure gauge, second stop valve and second pressure gauge, the gas pressure reducer is connected with the output end of pressure increasing pump;Gas storage unit is arranged between gas pressure reducer and first pressure sensor.Like this, by accurately controlling the pressure of output, the accuracy of test can be well guaranteed, the reliability and safety of in-flight fuel receiving system emergency release test can be well guaranteed, and test can be carried out without external gas cylinder, test operation is simple, test efficiency is high and the transfer, use of device is convenient.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft in-flight refueling technology, specifically relating to a test device for emergency release testing of aircraft in-flight refueling systems. Background Technology

[0002] Emergency refueling system deployment is a crucial performance indicator for aircraft refueling systems. The in-flight refueling system, located in the right forward compartment, is deployed during in-flight refueling and retracted after refueling is complete. The emergency deployment test of the in-flight refueling system involves releasing high-pressure gas from a high-pressure cylinder into an actuator, causing the system to deploy into position.

[0003] Existing testing methods are crude in their control, resulting in large errors in the pressure of gas acting on the actuator. They also suffer from inconvenience in operation, low testing efficiency, and certain safety hazards. Utility Model Content

[0004] The purpose of this invention is to provide a test device for emergency release testing of an aircraft in-flight refueling system, in order to solve the problems of large test errors, inconvenient operation, low efficiency, and potential safety hazards.

[0005] This utility model is achieved through the following technical solution: The test apparatus for emergency release testing of aircraft in-flight refueling systems includes: The gas supply unit includes a gas supply cylinder, a first shut-off valve, and a first solenoid valve connected in sequence. The first shut-off valve is used to control the gas supply from the gas supply cylinder. A booster unit includes a booster pump, the input end of which is connected to a first solenoid valve. The booster pump is used to boost the pressure of the gas output from the gas supply unit. The testing unit includes a gas pressure regulator, a first pressure sensor, a first pressure gauge, a second shut-off valve, and a second pressure gauge connected in sequence. The gas pressure regulator is connected to the output end of the booster pump. A gas storage unit is provided between the gas pressure regulator and the first pressure sensor. The gas storage unit includes a third shut-off valve, a gas storage cylinder, and a third pressure gauge for measuring the gas pressure in the gas storage cylinder.

[0006] In some embodiments, the test unit includes a first pressure regulating valve for adjusting the pressure of the gas output by the test unit, the first pressure regulating valve being disposed between a first pressure sensor and a first pressure gauge.

[0007] In some embodiments, the test unit includes a first safety relief valve disposed between a first pressure regulating valve and a first pressure gauge.

[0008] In some embodiments, the test unit includes a second pressure sensor disposed between the second shut-off valve and the second pressure gauge.

[0009] In some embodiments, the system further includes a first exhaust unit, which includes a first exhaust pipe and a fourth shut-off valve disposed on the first exhaust pipe, wherein the first exhaust pipe is connected between the second shut-off valve and the second pressure gauge.

[0010] In some embodiments, the gas supply unit includes a second pressure regulating valve for adjusting the output gas pressure of the gas supply unit, the second pressure regulating valve being disposed between the first shut-off valve and the first solenoid valve.

[0011] In some embodiments, the gas supply unit includes a second safety relief valve disposed between the second pressure regulating valve and the first solenoid valve.

[0012] In some embodiments, the gas supply unit includes a fourth pressure gauge and a fifth pressure gauge, the fourth pressure gauge being disposed between the first shut-off valve and the second pressure regulating valve, and the fifth pressure gauge being disposed between the first solenoid valve and the booster pump.

[0013] In some embodiments, a second exhaust unit is further included, the second exhaust unit including a second exhaust pipe and a fifth shut-off valve disposed on the second exhaust pipe, the second exhaust pipe being connected to the air supply pipe of the air supply unit and the output end of the booster pump, respectively.

[0014] In some embodiments, the first shut-off valve is connected to the gas supply line of the gas supply unit via a quick-connect fitting, and a sixth shut-off valve is provided on the gas supply line.

[0015] Compared with the prior art, this utility model has the following advantages and beneficial effects: This invention can ensure the accuracy of the test by precisely controlling the output pressure, and can ensure the reliability and safety of emergency release tests of aerial refueling systems. It can also be tested without external gas cylinders. The test operation is simple, the test efficiency is high, and the device is easy to transport and use. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings in the embodiments will be briefly described below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the experimental device structure in an embodiment of this utility model.

[0018] in: 1. Gas cylinder, 2. First shut-off valve, 3. Quick-connect fitting, 4. First filter, 5. Sixth shut-off valve, 6. Fourth pressure gauge, 7. Second pressure regulating valve, 8. Fifth shut-off valve, 9. Second safety relief valve, 10. Second filter, 11. First solenoid valve, 12. Fifth pressure gauge, 13. Booster pump, 14. Gas pressure reducer, 15. Third pressure gauge, 16. Third shut-off valve, 17. Gas storage cylinder, 18. First pressure sensor, 19. First pressure regulating valve, 20. First safety relief valve, 21. First pressure gauge, 22. Third filter, 23. Second shut-off valve, 24. Second pressure sensor, 25. Fourth shut-off valve, 26. Second pressure gauge, 27. Product under test. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of this utility model, but not all embodiments.

[0020] Reference Figure 1 In some embodiments of this utility model, a test apparatus for emergency release testing of an aircraft in-flight refueling system includes: The gas supply unit includes a gas supply cylinder 1, a first shut-off valve 2 and a first solenoid valve 11 connected in sequence. The first shut-off valve 2 is used to control the gas supply from the gas supply cylinder. The booster unit includes a booster pump 13, the input end of which is connected to the first solenoid valve 11. The booster pump is used to boost the gas pressure output by the gas supply unit. The test unit includes a gas pressure regulator 14, a first pressure sensor 18, a first pressure gauge 21, a second shut-off valve 23, and a second pressure gauge 26 connected in sequence. The gas pressure regulator 14 is connected to the output end of the booster pump 13. A gas storage unit is provided between the gas pressure regulator and the first pressure sensor. The gas storage unit includes a third shut-off valve 16, a gas storage cylinder 17, and a third pressure gauge 15 for measuring the gas pressure of the gas storage cylinder.

[0021] The first pressure sensor is used to measure the output pressure value of the test pipeline of the test unit. When the first pressure sensor reaches the set upper pressure limit, the control system controls the solenoid valve to close and the booster pump to stop pressurizing. When the first pressure sensor reaches the set lower pressure limit, the control system controls the solenoid valve to open and the booster pump to start pressurizing, so as to achieve precise control of the output gas pressure during the test.

[0022] After the tested product is released in an emergency, the second shut-off valve is closed, and the emergency release performance of the oil receiving system is tested by measuring the pressure change of the second pressure gauge.

[0023] By using a gas storage cylinder to store the pressurized gas, it is possible to conduct experiments even with a gas supply cylinder.

[0024] In some embodiments, the test unit includes a first pressure regulating valve 19 for adjusting the output gas pressure of the test unit. The first pressure regulating valve 19 is disposed between the first pressure sensor 18 and the first pressure gauge 21 to control the output gas pressure.

[0025] In some embodiments, the test unit includes a first safety relief valve 20, which is disposed between the first pressure regulating valve 19 and the first pressure gauge 21. By using the first safety relief valve, when the output air pressure becomes abnormal, emergency pressure relief is provided through the first safety relief valve to ensure the safety of the test.

[0026] In some embodiments, the test unit includes a second pressure sensor 24, which is disposed between the second shut-off valve 23 and the second pressure gauge 26. The second pressure sensor is used to monitor the pressure change after the emergency release of the oil receiving system.

[0027] In some embodiments, a first exhaust unit is also included, which includes a first exhaust pipe and a fourth shut-off valve 25 disposed on the first exhaust pipe. The first exhaust pipe is connected between the second shut-off valve 25 and the second pressure gauge 26 for depressurization after the test is completed.

[0028] In some embodiments, the gas supply unit includes a second pressure regulating valve 7 for adjusting the output gas pressure of the gas supply unit. The second pressure regulating valve 7 is disposed between the first shut-off valve 2 and the first solenoid valve 11. The second pressure regulating valve is used to set and adjust the output gas pressure of the gas supply unit to suit different testing requirements.

[0029] In some embodiments, the gas supply unit includes a second safety relief valve 9, which is disposed between the second pressure regulating valve 7 and the first solenoid valve 11. The second safety relief valve is configured to provide emergency pressure relief when the input gas pressure is abnormal, thereby ensuring the safety of the test.

[0030] In some embodiments, the gas supply unit includes a fourth pressure gauge 6 and a fifth pressure gauge 12. The fourth pressure gauge 6 is disposed between the first shut-off valve 2 and the second pressure regulating valve 7, and the fifth pressure gauge 12 is disposed between the first solenoid valve 11 and the booster pump 13, for accurately measuring the output pressure of the gas supply unit.

[0031] In some embodiments, a second exhaust unit is further included. The second exhaust unit includes a second exhaust pipe and a fifth shut-off valve 8 disposed on the second exhaust pipe. The second exhaust pipe is connected to the air supply pipe of the air supply unit and the output end of the booster pump, respectively, for depressurizing the air supply unit and the booster unit.

[0032] In some embodiments, the first shut-off valve 2 is connected to the gas supply line of the gas supply unit via a quick-connect coupling, and a sixth shut-off valve 5 is installed on the gas supply line. The quick-connect coupling facilitates connection and disconnection with the gas cylinder, meeting the needs of use in cylinder-free scenarios and making testing operations more convenient.

[0033] like Figure 1 As shown, the test apparatus for emergency release testing of an aircraft in-flight refueling system includes, in sequence, a gas supply cylinder 1, a first shut-off valve 2, a quick-connect fitting 3, a first filter 4, a sixth shut-off valve 5, a fourth pressure gauge 6, a second pressure regulating valve 7, a second overflow valve 9, a second filter 10, a first solenoid valve 11, a fifth pressure gauge 12, a booster pump 13, a gas pressure reducer 14, a gas storage cylinder 17, a first pressure sensor 18, a first pressure regulator 19, a first safety overflow valve 20, a first pressure gauge 21, a third filter 22, a second shut-off valve 23, a second pressure sensor 24, and a second pressure gauge 26.

[0034] The product under test 27 is connected to the output of the test unit.

[0035] During the test, the first shut-off valve was opened, and the gas passed through the quick-connect fitting, the first filter, the sixth shut-off valve, and the second filter before entering the booster pump to begin pressurization. Once the pressurized gas reaches the required pressure, it is output from the booster pump, passes through the gas pressure reducer, gas cylinder, third filter, and second shut-off valve, and enters the product under test, allowing for emergency release. At this time, the second shut-off valve is closed, and the pressure holding pressure of the product under test is detected by the measurements of the second pressure sensor and the second pressure gauge to check for any changes, thereby detecting whether the product under test has leaked and realizing the test of emergency release of the aerial refueling system.

[0036] In the description of this utility model, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", and "outer" used to indicate the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship that the utility model product is usually placed in during use. They are only used to facilitate the description of this utility model and to simplify the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0037] Furthermore, the use of terms such as "horizontal" or "vertical" in the description of this utility model does not imply that the component is required to be absolutely horizontal or suspended, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0038] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0039] The above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present utility model shall fall within the protection scope of the present utility model.

Claims

1. A test apparatus for emergency release testing of an aircraft in-flight refueling system, characterized in that, include: The gas supply unit includes a gas supply cylinder, a first shut-off valve, and a first solenoid valve connected in sequence. The first shut-off valve is used to control the gas supply from the gas supply cylinder. A booster unit includes a booster pump, the input end of which is connected to a first solenoid valve. The booster pump is used to boost the pressure of the gas output from the gas supply unit. The testing unit includes a gas pressure regulator, a first pressure sensor, a first pressure gauge, a second shut-off valve, and a second pressure gauge connected in sequence. The gas pressure regulator is connected to the output end of the booster pump. A gas storage unit is provided between the gas pressure regulator and the first pressure sensor. The gas storage unit includes a third shut-off valve, a gas storage cylinder, and a third pressure gauge for measuring the gas pressure in the gas storage cylinder.

2. The test apparatus for emergency release testing of an aircraft in-flight refueling system according to claim 1, characterized in that, The test unit includes a first pressure regulating valve for adjusting the output gas pressure of the test unit, and the first pressure regulating valve is disposed between the first pressure sensor and the first pressure gauge.

3. The test apparatus for emergency release testing of an aircraft in-flight refueling system according to claim 2, characterized in that, The test unit includes a first safety relief valve, which is disposed between a first pressure regulating valve and a first pressure gauge.

4. The test apparatus for emergency release testing of an aircraft in-flight refueling system according to claim 2, characterized in that, The test unit includes a second pressure sensor, which is disposed between the second shut-off valve and the second pressure gauge.

5. The test apparatus for emergency release testing of an aircraft in-flight refueling system according to claim 2, characterized in that, It also includes a first exhaust unit, which includes a first exhaust pipe and a fourth shut-off valve disposed on the first exhaust pipe. The first exhaust pipe is connected between the second shut-off valve and the second pressure gauge.

6. The test apparatus for emergency release testing of an aircraft in-flight refueling system according to claim 1, characterized in that, The gas supply unit includes a second pressure regulating valve for adjusting the output gas pressure of the gas supply unit, and the second pressure regulating valve is disposed between the first shut-off valve and the first solenoid valve.

7. The test apparatus for emergency release testing of an aircraft in-flight refueling system according to claim 6, characterized in that, The gas supply unit includes a second safety relief valve, which is disposed between the second pressure regulating valve and the first solenoid valve.

8. The test apparatus for emergency release testing of an aircraft in-flight refueling system according to claim 6, characterized in that, The gas supply unit includes a fourth pressure gauge and a fifth pressure gauge. The fourth pressure gauge is located between the first shut-off valve and the second pressure regulating valve, and the fifth pressure gauge is located between the first solenoid valve and the booster pump.

9. The test apparatus for emergency release testing of an aircraft in-flight refueling system according to claim 6, characterized in that, It also includes a second exhaust unit, which includes a second exhaust pipe and a fifth shut-off valve installed on the second exhaust pipe. The second exhaust pipe is connected to the air supply pipe of the air supply unit and the output end of the booster pump, respectively.

10. The test apparatus for emergency release testing of an aircraft in-flight refueling system according to claim 1, characterized in that, The first shut-off valve is connected to the gas supply line of the gas supply unit via a quick-connect fitting, and a sixth shut-off valve is installed on the gas supply line.

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