Aircraft door testing apparatus, method of testing and hydraulic fluid contamination detection method

Abstract

The application discloses an aircraft door testing device, a testing method thereof and a hydraulic oil pollution degree detection method, relates to the technical field of aircrafts, and provides hydraulic pressure for a cargo compartment door through a hydraulic unit, and a cable unit is used for detecting the state of a travel switch of the cargo compartment door during pressure supply of a hydraulic system, so that the problem that the operation of aircraft door testing is difficult in the prior art is solved. Further, the testing of the aircraft door is completed through pressure maintaining testing and travel switch testing, and a hydraulic oil pollution degree detection method is provided for detecting the pollution degree of hydraulic oil, and the application is suitable for aircraft door detection.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to an aircraft door testing device, a testing method thereof and a hydraulic oil contamination detection method. BACKGROUND

[0002] At present, most of the cargo door testing is performed before the aircraft assembly, and after the testing is qualified, the cargo door assembly is performed. The testing of the individual components is limited to simple manual drive mechanism testing and manual system on-off testing, such as B767 cargo door and B747 cargo door.

[0003] The existing cargo door debugging mainly tests the method of manual testing, that is, after the installation of the door framework, mechanism and cable system is completed, the motor or hydraulic drive is manually driven to operate the mechanism, and the opening and closing state and stroke position of the door latch and door lock mechanism are checked. For the installation test of the cable system, after the installation of the cable system, the on-off test is performed by connecting the cable ends with the positive and negative poles of the ohmmeter. The existing test process is difficult to operate. SUMMARY

[0004] The technical problem solved by the present application is to provide an aircraft door testing device, a testing method thereof and a hydraulic oil contamination detection method, which solves the problem of difficult operation of the aircraft door testing in the prior art.

[0005] The technical solution adopted by the present application to solve the above technical problem is that the aircraft door testing device comprises a hydraulic unit and a cable unit, the hydraulic unit is used to provide hydraulic pressure for the cargo door, and the cable unit is used to detect the state of the travel switch of the cargo door during the pressure supply process of the hydraulic system.

[0006] Further, the hydraulic unit comprises a hydraulic oil tank, an electric pump, a first check valve, an electromagnetic reversing valve, a first throttle valve, a first hydraulic interface, a second hydraulic interface, a second throttle valve, a proportional relief valve, a first relief valve, a second electric pump, a hand pump, a second check valve, a high-pressure stop valve, a third hydraulic interface, and a second relief valve; the electromagnetic reversing valve comprises a first interface, a second interface, a third interface, and a fourth interface, and is used to switch the first interface and the third interface to be communicated or the first interface and the fourth interface to be communicated, and the second interface and the fourth interface to be communicated or the second interface and the third interface to be communicated; the first interface of the electromagnetic reversing valve is connected with one end of the first throttle valve, the other end of the first throttle valve is connected with the first hydraulic interface, the second interface of the electromagnetic reversing valve is connected with one end of the second throttle valve, the other end of the second throttle valve is connected with the second hydraulic interface, the third interface of the electromagnetic reversing valve is connected with an oil outlet of the first check valve, an oil inlet of the first relief valve, and an oil inlet of the proportional relief valve respectively, an oil inlet of the first check valve is connected with an oil outlet of the electric pump, an oil inlet of the electric pump is located in the hydraulic oil tank, the fourth interface of the electromagnetic reversing valve, an oil outlet of the proportional relief valve, and an oil outlet of the first relief valve are connected with an oil inlet of the second electric pump, and an oil outlet of the second electric pump is located in the hydraulic oil tank; one end of the third hydraulic interface is connected with the high-pressure stop valve, the other end of the high-pressure stop valve is connected with an oil outlet of the second check valve and an oil inlet of the second relief valve respectively, an oil inlet of the second check valve is connected with an oil outlet of the hand pump, an oil inlet of the hand pump is located in the hydraulic oil tank, and an oil outlet of the second relief valve is connected with the hydraulic oil tank.

[0007] Further, the hydraulic unit further comprises a high-pressure filter, which is located between the oil outlet of the first check valve and the third interface of the electromagnetic reversing valve, one end of the high-pressure filter is connected with the oil outlet of the first check valve, and the other end of the high-pressure filter is connected with the third interface of the electromagnetic reversing valve, and is used to filter the hydraulic oil.

[0008] Further, the hydraulic unit further comprises a contamination detection unit, which comprises a pressure reducing valve and a contamination detector, one end of the pressure reducing valve is connected with the other end of the high-pressure filter, the other end of the pressure reducing valve is connected with one end of the contamination detector, the other end of the contamination detector is connected with the hydraulic oil tank, and the contamination detector is used to detect the contamination of the hydraulic oil filtered by the high-pressure filter.

[0009] Further, the hydraulic unit further comprises a pressure sensor, which is used to detect the pressure of the other end of the high-pressure filter.

[0010] Further, the hydraulic unit further comprises a shockproof pressure gauge, which is used to detect the pressure of one end of the high-pressure stop valve.

[0011] The aircraft door test method comprises a pressure maintaining test and a travel switch test;

[0012] The pressure maintaining test comprises the following steps:

[0013] S01, connecting one hydraulic port of the aircraft door with the third hydraulic interface, connecting the other hydraulic port of the aircraft door with the first hydraulic interface or the second hydraulic interface, and connecting the cable unit with the travel switch of the aircraft, adjusting the passage of the electromagnetic reversing valve so that the hydraulic oil flows to the one-way valve through the first hydraulic interface or the second hydraulic interface;

[0014] S02, after the hand pump provides the aircraft door with the preset pressure, the high-pressure stop valve is closed, and whether the pressure in the shock-resistant pressure gauge is the same as the preset pressure is observed for a period of time, if yes, the pressure maintaining test is passed, and if no, the pressure maintaining test fails;

[0015] S03, after the pressure maintaining test passes or fails, the passage of the electromagnetic reversing valve is switched, and the hydraulic oil is flowed back to the hydraulic oil tank through the second electric pump;

[0016] The travel switch test comprises the following steps:

[0017] S11, connecting one hydraulic port of the aircraft door with the first hydraulic interface, and connecting the other hydraulic port of the aircraft door with the second hydraulic interface;

[0018] S12, providing the aircraft door with hydraulic pressure by the first electric pump, observing the state of the travel switch, switching the passage of the electromagnetic reversing valve, and continuing to observe the state of the travel switch, if the state of the travel switch is correct, the travel switch test is passed, otherwise, the travel switch test fails;

[0019] S13, after the travel switch test passes or fails, the hydraulic oil is flowed back to the hydraulic oil tank through the second electric pump.

[0020] The hydraulic oil pollution degree detection method comprises the following steps:

[0021] S21, connecting the first hydraulic interface with the second hydraulic interface;

[0022] S22, starting the first electric pump so that the hydraulic oil is flowed back to the oil tank through the second electric pump after passing through the pollution degree detection unit;

[0023] S23, reading the data on the pollution degree detector to obtain the pollution degree of the hydraulic oil.

[0024] The application has the beneficial effects that the aircraft door testing device, the testing method thereof and the hydraulic oil pollution degree detection method provide the aircraft door with hydraulic pressure through the hydraulic unit, and detect the state of the travel switch of the cargo door during the pressure supply process of the hydraulic system through the cable unit, thereby solving the problem of high operation difficulty of the aircraft door testing in the prior art. BRIEF DESCRIPTION OF DRAWINGS

[0025] BRIEF DESCRIPTION OF DRAWINGS Figure 1 FIG. 1 is a structural block diagram of the hydraulic unit in the aircraft door testing device, the testing method thereof and the hydraulic oil pollution degree detection method. DETAILED DESCRIPTION

[0026] The application provides an aircraft door testing device, which comprises a hydraulic unit and a cable unit, the hydraulic unit is used for providing the cargo door with hydraulic pressure, and the cable unit is used for detecting the state of the travel switch of the cargo door during the pressure supply process of the hydraulic system.

[0027] Specifically, the structure of the hydraulic unit is shown in FIG. 1. Figure 1 As shown in FIG. 1, the hydraulic unit comprises a hydraulic oil tank, an electric pump, a first check valve, an electromagnetic reversing valve, a first throttle valve, a first hydraulic interface, a second hydraulic interface, a second throttle valve, a proportional overflow valve, a first overflow valve, a second electric pump, a hand pump, a second check valve, a high-pressure stop valve, a third hydraulic interface and a second overflow valve; the electromagnetic reversing valve comprises a first interface, a second interface, a third interface and a fourth interface, and is used for switching the communication between the first interface and the third interface or the communication between the first interface and the fourth interface, and the communication between the second interface and the fourth interface or the communication between the second interface and the third interface; the first interface of the electromagnetic reversing valve is connected with one end of the first throttle valve, the other end of the first throttle valve is connected with the first hydraulic interface, the second interface of the electromagnetic reversing valve is connected with one end of the second throttle valve, the other end of the second throttle valve is connected with the second hydraulic interface, the third interface of the electromagnetic reversing valve is connected with the oil outlet of the first check valve, the oil inlet of the first overflow valve and the oil inlet of the proportional overflow valve respectively, the oil inlet of the first check valve is connected with the oil outlet of the electric pump, the oil inlet of the electric pump is located in the hydraulic oil tank, the fourth interface of the electromagnetic reversing valve, the oil outlet of the proportional overflow valve and the oil outlet of the first overflow valve are all connected with the oil inlet of the second electric pump, and the oil outlet of the second electric pump is located in the hydraulic oil tank; one end of the third hydraulic interface is connected with the high-pressure stop valve, the other end of the high-pressure stop valve is connected with the oil outlet of the second check valve and the oil inlet of the second overflow valve respectively, the oil inlet of the second check valve is connected with the oil outlet of the hand pump, the oil inlet of the hand pump is located in the hydraulic oil tank, and the oil outlet of the second overflow valve is connected with the hydraulic mailbox.

[0028] Working principle: two of the first, second and third hydraulic interfaces are combined to connect with the hydraulic port of the aircraft door to form a hydraulic channel and complete the corresponding test.

[0029] Further, the hydraulic unit further comprises a high-pressure filter, the high-pressure filter is located between the oil outlet of the first check valve and the third interface of the electromagnetic reversing valve, one end of the high-pressure filter is connected with the oil outlet of the first check valve, the other end of the high-pressure filter is connected with the third interface of the electromagnetic reversing valve, and the high-pressure filter is used for filtering the hydraulic oil.

[0030] Specifically, the high-pressure filter is used for cleaning the hydraulic oil to prevent impurities in the hydraulic oil from entering the hydraulic oil channel in the aircraft door.

[0031] Further, the hydraulic unit further comprises a contamination detection unit, the contamination detection unit comprises a pressure reducing valve and a contamination detector, one end of the pressure reducing valve is connected with the other end of the high-pressure filter, the other end of the pressure reducing valve is connected with one end of the contamination detector, the other end of the contamination detector is connected with the hydraulic oil tank, and the contamination detector is used for detecting the contamination degree of the hydraulic oil filtered by the high-pressure filter.

[0032] Specifically, the contamination detection unit is used for detecting the contamination degree of the hydraulic oil to prevent the hydraulic oil with excessive contamination degree from being continuously used to cause impurities to adhere to the hydraulic channel in the aircraft door.

[0033] Further, the hydraulic unit further comprises a pressure sensor, and the pressure sensor is used for detecting the pressure of the other end of the high-pressure filter.

[0034] Specifically, the proportion of the proportional overflow valve can be adjusted according to the value of the pressure sensor to adapt to different aircraft doors.

[0035] Further, the hydraulic unit further comprises a shock-proof pressure gauge, and the shock-proof pressure gauge is used for detecting the pressure of one end of the high-pressure stop valve.

[0036] Specifically, the high-pressure stop valve cooperates with the first check valve to complete the pressure maintaining test, the shock-proof pressure gauge is used for detecting the hydraulic oil pressure during the pressure maintaining test, and the pressure is controlled through the hand pump.

[0037] The application also provides an aircraft door test method applied to the aircraft door test device, and the method comprises a pressure maintaining test and a travel switch test.

[0038] The pressure maintaining test comprises the following steps.

[0039] S01, connecting one hydraulic port of the aircraft door with the third hydraulic interface, connecting the other hydraulic port of the aircraft door with the first hydraulic interface or the second hydraulic interface, and connecting the cable unit with the travel switch of the aircraft, adjusting the passage of the electromagnetic reversing valve, so that the hydraulic oil flows to the one-way valve through the first hydraulic interface or the second hydraulic interface;

[0040] S02, after the hand pump provides the aircraft door with a preset pressure, the high-pressure cutoff valve is closed, and the pressure in the shock-resistant pressure gauge is observed for a period of time to see if it is the same as the preset pressure, if yes, the pressure holding test is passed, if not, the pressure holding test fails;

[0041] S03, after the pressure holding test passes or fails, the passage of the electromagnetic reversing valve is switched, and the hydraulic oil is returned to the hydraulic oil tank through the second electric pump by the second electric pump;

[0042] The travel switch test comprises the following steps:

[0043] S11, connecting one hydraulic port of the aircraft door with the first hydraulic interface, and connecting the other hydraulic port of the aircraft door with the second hydraulic interface;

[0044] S12, providing the aircraft door with hydraulic pressure by the first electric pump, observing the state of the travel switch, and then switching the passage of the electromagnetic reversing valve, continuing to observe the state of the travel switch, if the state of the travel switch is correct, the travel switch test is passed, otherwise, the travel switch test fails;

[0045] S13, after the travel switch test passes or fails, the hydraulic oil is returned to the hydraulic oil tank through the second electric pump by the second electric pump.

[0046] The application also provides a hydraulic oil pollution degree detection method applied to the aircraft door test equipment, comprising the following steps:

[0047] S21, connecting the first hydraulic interface with the second hydraulic interface;

[0048] S22, starting the first electric pump, so that the hydraulic oil returns to the oil tank through the second electric pump after the pollution degree detection unit;

[0049] S23, reading the data on the pollution degree detector to obtain the pollution degree of the hydraulic oil.

Claims

1. An aircraft door testing device, characterized in that, The system includes a hydraulic unit and a cable unit. The hydraulic unit provides hydraulic pressure to the cargo hatch door, and the cable unit detects the status of the limit switch of the cargo hatch door during hydraulic system pressure supply. The hydraulic unit includes a high-pressure filter, a contamination detection unit, a hydraulic oil tank, an electric pump, a first check valve, a solenoid directional valve, a first throttle valve, a first hydraulic interface, a second hydraulic interface, a second throttle valve, a proportional relief valve, a first relief valve, a second electric pump, a hand pump, a second check valve, a high-pressure shut-off valve, a third hydraulic interface, and a second relief valve. The solenoid directional valve includes a first interface, a second interface, a third interface, and a fourth interface. The solenoid directional valve is used to switch the connection between the first and third interfaces, or between the first and fourth interfaces, and between the second and fourth interfaces, or between the second and third interfaces. The first interface of the solenoid directional valve is connected to one end of the first throttle valve, and the other end of the first throttle valve... One end is connected to the first hydraulic interface; the second interface of the electromagnetic directional valve is connected to one end of the second throttle valve; the other end of the second throttle valve is connected to the second hydraulic interface; the third interface of the electromagnetic directional valve is connected to the outlet of the first check valve, the inlet of the first relief valve, and the inlet of the proportional relief valve, respectively; the inlet of the first check valve is connected to the outlet of the electric pump, which is located inside the hydraulic oil tank; the fourth interface of the electromagnetic directional valve, the outlet of the proportional relief valve, and the outlet of the first relief valve are all connected to the inlet of the second electric pump, which is located inside the hydraulic oil tank; the third hydraulic interface is connected to one end of the high-pressure shut-off valve; the other end of the high-pressure shut-off valve is connected to the outlet of the second check valve and the inlet of the second relief valve, respectively; the inlet of the second check valve is connected to the outlet of the hand-cranked pump, which is located inside the hydraulic oil tank; and the outlet of the second relief valve is connected to the hydraulic oil tank.

2. The aircraft door testing equipment according to claim 1, characterized in that, The high-pressure filter is located between the oil outlet of the first check valve and the third port of the solenoid directional valve. One end of the high-pressure filter is connected to the oil outlet of the first check valve, and the other end of the high-pressure filter is connected to the third port of the solenoid directional valve, and is used to filter the hydraulic oil.

3. The aircraft door testing equipment according to claim 1, characterized in that, The contamination detection unit includes a pressure reducing valve and a contamination detector. One end of the pressure reducing valve is connected to the other end of the high-pressure filter, and the other end of the pressure reducing valve is connected to one end of the contamination detector. The other end of the contamination detector is connected to the hydraulic oil tank. The contamination detector is used to detect the contamination level of the hydraulic oil after it has been filtered by the high-pressure filter.

4. The aircraft door testing equipment according to claim 2 or 3, characterized in that, The hydraulic unit also includes a pressure sensor for detecting the pressure at the other end of the high-pressure filter.

5. The aircraft door testing equipment according to any one of claims 1-3, characterized in that, The hydraulic unit also includes a shock-resistant pressure gauge, which is used to detect the pressure at one end of the high-pressure shut-off valve.

6. An aircraft door testing method, applied to the aircraft door testing equipment described in claim 5, characterized in that, This includes pressure holding tests and limit switch tests; The pressure holding test includes the following steps: S01. Connect one hydraulic port of the aircraft door to the third hydraulic interface, and connect the other hydraulic interface of the aircraft door to the first hydraulic interface or the second hydraulic interface, and connect the cable unit to the limit switch of the aircraft, adjust the passage of the solenoid directional valve so that the hydraulic oil flows to the check valve through the first hydraulic interface or the second hydraulic interface. S02. After using a hand pump to provide the preset pressure hydraulic fluid to the aircraft door, close the high-pressure shut-off valve and observe whether the pressure in the shock-resistant pressure gauge is the same as the preset pressure hydraulic fluid within a certain period of time. If they are the same, the pressure holding test is passed; if they are not the same, the pressure holding test fails. S03. After the pressure holding test passes or fails, switch the passage of the solenoid directional valve and use the second electric pump to return the hydraulic oil to the hydraulic oil tank. The limit switch test includes the following steps: S11. Connect one hydraulic port of the aircraft door to the first hydraulic interface, and connect the other hydraulic port of the aircraft door to the second hydraulic interface. S12. Use the first electric pump to provide hydraulic pressure to the aircraft door and observe the status of the limit switch. Then switch the passage of the solenoid directional valve and continue to observe the status of the limit switch. If the status of the limit switch is correct, the limit switch test is passed; otherwise, the limit switch test fails. S13. After the limit switch test passes or fails, the hydraulic oil is returned to the hydraulic oil tank via the second electric pump.

7. A method for detecting hydraulic oil contamination, applied to the aircraft door testing equipment described in claim 3, characterized in that, Includes the following steps: S21. Connect the first hydraulic interface and the second hydraulic interface; S22. Start the first electric pump so that the hydraulic oil returns to the oil tank via the second electric pump after passing through the contamination detection unit. S23. Read the data from the contamination detector to obtain the contamination level of the hydraulic oil.

Images