Airplane hydraulic system test board

Abstract

The utility model relates to an airplane hydraulic system testboard, and belongs to the technical field of airplane hydraulic system testing. Comprising a shell, a test panel, a switch, a pressure adjusting device, a flow adjusting device, a valve, a test interface and a control module, the switch comprises a power switch and a start-stop switch, the pressure adjusting device comprises a pressure adjusting switch and a pressure digital display meter, and the flow adjusting device comprises a flow adjusting switch and a flow digital display meter. The number of the valves and the number of the test interfaces are both multiple. The test panel is further provided with a change-over switch. The test board can provide corresponding pressure and flow regulation functions and control operation for the test of the hydraulic system of the airplane, so that the hydraulic system can be conveniently subjected to various tests, inspection and troubleshooting, the normal use of the hydraulic system is ensured, and the normal flight of the airplane is ensured.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft hydraulic system testing, in particular to an aircraft hydraulic system testing platform. Background Art

[0002] A hydraulic system refers to the entire set of devices on an aircraft that uses oil as a working medium and relies on oil pressure to drive actuators to perform specific control actions. To ensure the reliable operation of the hydraulic system, and particularly to improve the reliability of the hydraulic power source of the flight control system, most modern large civil aircraft are equipped with two (or more) independent hydraulic systems. Generally speaking, hydraulic systems are used for retraction and extension of landing gear, flaps, and airbrakes, nose wheel steering, door opening and closing, windshield wiper operation, and other functions. They also drive some aileron, elevator, and rudder boosters. An aircraft's hydraulic system plays an important role. During operation, the hydraulic system requires testing, inspection, and troubleshooting to ensure proper operation and flight of the aircraft. Therefore, the present invention provides an aircraft hydraulic system test bench to verify the proper operation of the aircraft's hydraulic system. Summary of the Invention

[0003] To overcome the problems mentioned in the background art, the present invention provides an aircraft hydraulic system test bench. This test bench provides pressure and flow regulation and control functions for aircraft hydraulic system testing, facilitating various tests, inspections, and troubleshooting of the hydraulic system, ensuring the proper operation of the hydraulic system and the proper flight of the aircraft.

[0004] To achieve the above-mentioned purpose, the present invention is implemented through the following technical scheme: an aircraft hydraulic system test bench includes a shell 1, a test panel 2, a switch 3, a pressure regulating device 4, a flow regulating device 5, a valve 6, a test interface 7 and a control module 8, the switch 3 includes a power switch 9 and a start-stop switch 10, the pressure regulating device 4 includes a pressure regulating switch 11 and a pressure digital display 12, the flow regulating device 5 includes a flow regulating switch 13 and a flow digital display 14, the test panel 2 is installed at the front end of the shell 1, the switch 3, pressure regulating device 4, flow regulating device 5, valve 6 and test interface 7 are all installed on the test panel 2, and the valve 6 and test interface 7 each include multiple, a valve body 15 is installed in the shell 1, and the test panel 2 is also provided with a conversion switch 24.

[0005] Furthermore, the aircraft hydraulic system test bench includes two flow meters 16 , including a high-pressure flow meter 17 and a low-pressure flow meter 18 .

[0006] Furthermore, the aircraft hydraulic system test bench includes a pressure display gauge 19, and there are multiple pressure display gauges 19.

[0007] Furthermore, the aircraft hydraulic system test bench includes a warning light 20, and there are multiple warning lights 20.

[0008] Furthermore, the aircraft hydraulic system test bench includes an accumulator 21 , which is installed in the housing 1 .

[0009] Furthermore, the aircraft hydraulic system test bench includes a lighting lamp 22 , a support plate 23 is installed on the top of the housing 1 , and the lighting lamp 22 is installed on the bottom of the support plate 23 .

[0010] Furthermore, the aircraft hydraulic system test bench includes a pressure sensor, and there are multiple pressure sensors.

[0011] Furthermore, an opening 25 is provided on one side of the housing 1 , and the control module 8 is installed in the opening 25 . A side door 26 is provided on one side of the opening 25 .

[0012] Beneficial effects of the utility model:

[0013] The test bench of the utility model can provide corresponding pressure and flow regulation functions and control operations for aircraft hydraulic system testing, and can monitor and display relevant parameters such as pressure and flow in real time. During testing, it can provide functions such as inlet and outlet oil reversing, system pressure protection, and pressure buffering. It is convenient for various tests, inspections, and troubleshooting of the hydraulic system, ensuring the normal use of the hydraulic system and the normal flight of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a structural diagram of the test panel of the utility model.

[0015] Figure 2 It is a schematic structural diagram of the utility model.

[0016] Figure 3 It is a schematic structural diagram of the utility model.

[0017] Figure 4 This is a schematic diagram of the test connection circuit of the utility model.

[0018] Figure numerals: shell 1, test panel 2, switch 3, pressure regulating device 4, flow regulating device 5, valve 6, test interface 7, control module 8, power switch 9, start-stop switch 10, pressure regulating switch 11, pressure digital display 12, flow regulating switch 13, flow digital display 14, valve body 15, flowmeter 16, high-pressure flowmeter 17, low-pressure flowmeter 18, pressure display 19, warning light 20, accumulator 21, lighting lamp 22, support plate 23, conversion switch 24, opening 25, side door 26. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solutions and beneficial effects of the present invention clearer, the preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings to facilitate understanding by technicians.

[0020] like Figure 1-4 The utility model discloses an aircraft hydraulic system test bench, which includes a shell 1, a test panel 2, a switch 3, a pressure regulating device 4, a flow regulating device 5, a valve 6, a test interface 7 and a control module 8. The switch 3, the pressure regulating device 4, the flow regulating device 5, the valve 6 and the valve body 15 are all connected to the control module 8. The switch 3 includes a power switch 9 and a start-stop switch 10. The pressure regulating device 4 includes a pressure regulating switch 11 and a pressure digital display 12. The flow regulating device 5 includes a flow regulating switch 13 and a flow digital display 14. The maximum pressure output of the hydraulic pump station is controlled to the required test value by adjusting the pressure regulating switch, and the output flow of the hydraulic pump station is adjusted to the required test value by adjusting the flow regulating switch. The pressure and flow can be displayed on the pressure digital display and flow digital display respectively. The test panel 2 is installed at the front end of the housing 1. The switch 3, pressure regulating device 4, flow regulating device 5, valve 6 and test interface 7 are all installed on the test panel 2. There are multiple valves 6 and test interface 7. A valve body 15 is installed in the housing 1. A conversion switch 24 is also provided on the test panel 2. The test bench is connected to a 220VAC / 50HZ power supply. The control module is connected to a hydraulic pump station. The hydraulic pump station can be controlled by the control module. The valves include switch valves (GV1-GV7), valves (TY2, TY3), return valves, and valves. Oil valves (HV1-HV4), valves (HV5-HV8), test interfaces include return oil interface (HJ1-HJ4), interface (GJ1-GJ4), interface (LL1-LL4), oil leakage interface (LJ1-LJ4); the hydraulic platform can provide corresponding pressure and flow regulation functions and control operations for aircraft hydraulic system testing, and monitor and display relevant parameters such as pressure and flow in real time. During testing, it can provide inlet and outlet oil reversing, system pressure protection, pressure buffering and other functions; it facilitates various tests, inspections and troubleshooting of the hydraulic system, ensuring the normal use of the hydraulic system and the normal flight of the aircraft.

[0021] The aircraft hydraulic system test bench includes two flow meters 16, including a high-pressure flow meter 17 and a low-pressure flow meter 18; the high-pressure flow meter (LLJ1) has a maximum pressure resistance of 30 MPA and is mainly used for measuring the main oil supply and large-flow return oil flow; the low-pressure flow meter (LLJ2) has a maximum pressure resistance of 2.5 MPA and is mainly used for measuring large-flow oil leakage and small-flow return oil.

[0022] The aircraft hydraulic system test bench includes a pressure display gauge 19, and there are multiple pressure display gauges 19; the pressure display gauge is connected to the control module, and there are multiple pressure display gauges. When the test pressure is adjusted by the valve, the pressure can be displayed by the pressure display gauge.

[0023] The aircraft hydraulic system test bench includes an alarm light 20, and there are multiple alarm lights 20; the alarm lights are connected to the control module, and the alarm lights include an oil inlet abnormality alarm light, an oil supply abnormality alarm light and an oil return abnormality alarm light. The alarm lights are red and light up when an abnormality occurs.

[0024] The aircraft hydraulic system test bench includes an accumulator 21, which is installed on the valve body 15 in the housing 1; the accumulator can provide additional energy in the short term to make the equipment run more stably and efficiently, while reducing wear on system components and facilitating system maintenance.

[0025] The aircraft hydraulic system test bench includes a lighting lamp 22. A support plate 23 is installed on the top of the shell 1, and the lighting lamp 22 is installed at the bottom of the support plate 23. The lighting lamp is connected to the control module and can be turned on during testing to provide lighting for easy testing.

[0026] The aircraft hydraulic system test bench includes a pressure sensor, and there are multiple pressure sensors.

[0027] An opening 25 is provided on one side of the housing 1, and the control module 8 is installed in the opening 25. A side door 26 is provided on one side of the opening 25; the control module, i.e., the controller, is installed in the opening, which makes it easy to open the side door for installation or maintenance.

[0028] Working process:

[0029] The operating principle of this utility model is as follows: During testing, an external power source is connected, power switch 9 is turned on to power up the test bench, and the start / stop switch 10 is pressed to start the hydraulic pump station. Once the hydraulic pump station is operating, the maximum pressure output of the hydraulic pump station is controlled to the required test value by adjusting the pressure regulating switch 11, and the output flow of the hydraulic pump station is adjusted to the required test value by adjusting the flow regulating switch 13. The hydraulic oil provided by the hydraulic pump station is connected to the test interface 7 of the test bench via an oil pipe, providing operating hydraulic oil for the test bench. The hydraulic test bench has three test interfaces for direct pressure supply: test interface GJ1 (corresponding to switch valve GV2), GJ4 (corresponding to switch valve GV5), and GJ5 (corresponding to switch valve GV6). When the switch valve (GV2, GV5, or GV6) is opened, the hydraulic oil provided by the hydraulic pump station is directly supplied to the test piece through the test interface. The real-time pressure of each hydraulic oil line can be measured by a pressure sensor. The test inlet pressure can also be controlled by switching valve GV1. The test bench inlet pressure is displayed on pressure indicator 19. The hydraulic test bench has two pressure-regulated outputs. The regulated supply pressure is output through test interface (GJ2 or GJ3). After the hydraulic pump station supplies pressure, the output pressure can be controlled by adjusting valves (TY2 or TY3). The adjusted pressure can be observed on pressure indicator 19. After adjusting the required pressure for the test piece, open valves (GV3 or GV4). The test bench supplies pressure to the test piece through test interface (GJ2 or GJ3). For reversing operation, open valves GV7 and HV1 and turn switch 24 to complete the test piece switching test. For return operation, open the return valves (HV1-HV4) for normal oil return, and the return oil from the test piece flows back through the return interfaces (HJ1-HJ4). To perform a leak test, close the oil return valve (HV1-HV4), open the oil leak test valve (HV5-HV8), connect a measuring cup to the oil leak interface (LJ1-LJ4), and measure the oil leakage. To perform a flow test, use two separate test loops. When a flow test is required, simply connect a flow meter to the test loop. Connect the flow meter between interfaces LL1, LL2, and LL3, LL4 to display the test flow rate.

[0030] Finally, it should be noted that the above preferred embodiments are only used to illustrate the technical solutions of the present invention and are not limiting. Although the present invention has been described in detail through the above preferred embodiments, those skilled in the art should understand that various changes can be made in form and details without departing from the scope defined by the claims of the present invention.

Claims

1. An aircraft hydraulic system test bench, characterized by: The aircraft hydraulic system test bench comprises a housing (1), a test panel (2), a switch (3), a pressure regulating device (4), a flow regulating device (5), a valve (6), a test interface (7) and a control module (8), wherein the switch (3) comprises a power switch (9) and a start / stop switch (10), the pressure regulating device (4) comprises a pressure regulating switch (11) and a pressure digital display (12), and the flow regulating device (5) comprises a flow regulating switch (13) and a flow digital display (14), the test panel (2) is mounted at the front end of the housing (1), the switch (3), the pressure regulating device (4), the flow regulating device (5), the valve (6) and the test interface (7) are all mounted on the test panel (2), and the valve (6) and the test interface (7) each comprise a plurality, a valve body (15) is mounted in the housing (1), and a conversion switch (24) is further provided on the test panel (2).

2. The aircraft hydraulic system test bench according to claim 1, characterized in that: The aircraft hydraulic system test bench includes a flow meter (16), and the flow meter (16) is two, including a high-pressure flow meter (17) and a low-pressure flow meter (18).

3. The aircraft hydraulic system test bench according to claim 1, characterized in that: The aircraft hydraulic system test bench includes a pressure display gauge (19), and there are multiple pressure display gauges (19).

4. The aircraft hydraulic system test bench according to claim 1, characterized in that: The aircraft hydraulic system test bench comprises a warning light (20), and there are a plurality of the warning lights (20).

5. The aircraft hydraulic system test bench according to claim 1, characterized in that: The aircraft hydraulic system test bench comprises an accumulator (21), and the accumulator (21) is installed in a housing (1).

6. The aircraft hydraulic system test bench according to claim 1, characterized in that: The aircraft hydraulic system test bench includes a lighting lamp (22), a support plate (23) is installed on the top of the housing (1), and the lighting lamp (22) is installed on the bottom of the support plate (23).

7. The aircraft hydraulic system test bench according to claim 1, characterized in that: The aircraft hydraulic system test bench includes a pressure sensor, and there are multiple pressure sensors.

8. The aircraft hydraulic system test bench according to claim 1, characterized in that: An opening (25) is provided on one side of the housing (1), the control module (8) is installed in the opening (25), and a side door (26) is provided on one side of the opening (25).

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