Aviation pump testing system

Abstract

The utility model relates to an aviation pump test system, belongs to the technical field of aerospace, and solves the problems that most aviation pump test stands are heavy in structure, high in cost, large in occupied area and incapable of meeting strict experiment conditions required by aviation pump experiments at present. The device comprises a tool unit, an oil receiving tank and an environment test box, the tool unit comprises an aviation pump tool assembly and a motor assembly. The aviation pump tool assembly is used for installing an aviation pump. The motor assembly comprises a high-speed motor used for driving the aviation pump tool assembly. The oil receiving tank is arranged at the lower part of the aviation pump tool assembly and is used for collecting oil leaked during pipeline disassembly and assembly in the aviation pump tool assembly; the environment test box is used for testing the aviation pump at different temperatures, different pressures and different flows. According to the utility model, the service life test meeting the requirements of high-speed driving, high-temperature medium and high-temperature environment of the aviation pump can be realized.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, and in particular to an aviation pump testing system. Background Technology

[0002] Aviation pumps are mostly high-speed driven, using fuel with a maximum temperature of 150°C or lubricating oil with a maximum temperature of 220°C. To ensure normal aircraft operation, aviation pumps need to undergo rigorous life tests under conditions such as high-speed drive and high-temperature media environments. During the test, multiple pipelines need to be properly connected, and it must be ensured that the aviation pump does not leak oil during the experiment.

[0003] Currently, most aviation pump test benches are bulky, expensive, and occupy a large area, and cannot meet the strict experimental conditions required for aviation pump experiments. Utility Model Content

[0004] Based on the above analysis, the present invention aims to provide an aviation pump testing system to solve the problems that most current aviation pump test benches are bulky, costly, and occupy a large area, and cannot meet the strict experimental conditions required for aviation pump experiments.

[0005] The objective of this utility model is mainly achieved through the following technical solutions:

[0006] An aircraft pump testing system includes a tooling unit, an oil receiving tank, and an environmental testing chamber;

[0007] The tooling unit includes an aviation pump tooling assembly and a motor assembly; the aviation pump tooling assembly is used to install the aviation pump; the motor assembly includes a high-speed motor for driving the aviation pump tooling assembly.

[0008] The oil receiving tank is located at the lower part of the aviation pump tooling assembly and is used to collect oil leaked during the disassembly and assembly of the pipelines in the aviation pump test tooling assembly.

[0009] The environmental test chamber is used to test the aviation pump under different temperatures, pressures, and flow rates.

[0010] Furthermore, the tooling unit also includes a working platform, which is provided with multiple oil collection tanks. The bottom of the oil collection tank is provided with an oil leakage hole, which is connected to the oil receiving tank through an oil leakage flow pipe.

[0011] Furthermore, the bottom of the oil receiving tank is provided with an oil drain port, which is connected to an external oil pumping device; the oil receiving tank is provided with a liquid level sensor.

[0012] Furthermore, the tooling unit includes a transmission mounting base; the transmission mounting base is provided with a drive shaft of a motor assembly; the drive shaft is connected to the aircraft pump tooling assembly.

[0013] Furthermore, the tooling unit also includes a torque sensor, which is disposed between the motor assembly and the transmission mounting base.

[0014] Furthermore, the aircraft pump tooling assembly includes an aircraft pump tooling, an aircraft pump suction port, and an aircraft pump return port; one end of the aircraft pump tooling is connected to the aircraft pump, and the other end is connected to the transmission mounting base;

[0015] The aircraft pump's oil suction port is located on the wall of the oil receiving tank, and the aircraft pump's oil return port is located on the upper part of the aircraft pump; the aircraft pump's oil suction port and the aircraft pump's oil return port are connected to the aircraft pump.

[0016] Furthermore, the aviation pump fixture has an internal accommodating cavity for mounting the aviation pump; the aviation pump fixture has multiple accommodating cavities of different sizes.

[0017] Furthermore, the environmental testing chamber includes a chamber body and a test plate;

[0018] The test plate is disposed on the side of the box; a high-temperature resistant sealing strip is provided at the connection between the test plate and the box;

[0019] The lower part of the box has a notch, the upper end face of the notch forms an angle with the vertical direction, and the upper end face of the oil receiving groove forms an angle with the horizontal direction; the upper end face of the notch is connected to the upper end face of the oil receiving groove.

[0020] Furthermore, the test board is equipped with multiple pressure sensors and pressure measurement interfaces; the pressure sensors and pressure measurement interfaces are located above the air pump and connected to the air pump.

[0021] Furthermore, the environmental testing chamber also includes a slide rail, and the chamber body is mounted on the slide rail.

[0022] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0023] (1) This utility model includes a tooling unit, an oil receiving tank, and an environmental testing chamber. The tooling unit provides tooling for the aviation pump, the oil receiving tank collects oil leaked during the disassembly and assembly of the pipelines in the aviation pump testing tooling assembly, and the environmental testing chamber ensures the overall sealing of the environmental chamber and is used to conduct high-temperature and different pressure tests on the aviation pump. The aviation pump testing system of this utility model meets the life test requirements of high-speed drive, high-temperature media, and high-temperature environment for aviation pumps. The high-speed drive adopts a high-speed motor for direct connection, which is simple and compact in structure, ensuring that the aviation pump can operate reliably for a long time within its lifespan. It is low in cost, occupies a small area, and is convenient to install and use.

[0024] (2) In this utility model, the oil receiving tank is set at the lower part of the aircraft pump to collect the oil leaked during the disassembly of the pipeline in the aircraft pump test fixture assembly when replacing the aircraft pump; the oil receiving tank monitors the oil in the tank through a liquid level sensor. When the liquid level reaches a certain height, the oil is pumped into the hydraulic system to ensure that the oil does not fall to the ground and reduce labor costs; the working platform is equipped with an oil collection tank to collect the oil leaked during the experiment. The bottom of the oil collection tank is equipped with an oil leakage hole, and the leaked oil flows directly into the oil receiving tank through a pipeline; by setting up the oil receiving tank and the oil collection tank on the working platform, combined with the shaft seal sealing structure in the transmission mounting seat, it is ensured that the aircraft pump does not leak oil during high-altitude and ground tests.

[0025] (3) The oil suction port of the aviation pump is located on the wall of the oil receiving tank to meet the low flow resistance requirements of certain models of aviation pumps. The oil return port of the aviation pump is located on the upper environmental test chamber mounting plate of the aviation pump to solve the problem of insufficient space due to the large number of pipelines and facilitate worker operation.

[0026] (4) The internal accommodating cavity of the aviation pump tooling is used to install the aviation pump. The aviation pump tooling has multiple accommodating cavities, which facilitates the quick replacement of the aviation pump and improves the adaptability of the aviation pump tooling to different models of aviation pumps.

[0027] (5) The environmental test chamber integrates multiple inlet and outlet interfaces and pressure measurement interfaces for aviation pumps, which can meet the testing requirements of various multi-interface aviation pumps and the pressure measurement requirements within 100mm of the inlet and outlet of aviation pumps. The test temperature of the environmental test chamber reaches 250℃, which meets the testing requirements of aviation pumps in high-temperature media (fuel with a maximum temperature of 150℃ or lubricating oil with a maximum temperature of 220℃) and environments. A high-temperature sealing strip is provided at the connection between the environmental test chamber and the test plate to ensure that the environmental test chamber remains sealed at high temperatures; there is a notch at the bottom of the chamber, and the upper end face of the notch is at an angle to the vertical direction, and the upper end face of the oil receiving tank is at an angle to the horizontal direction; the upper end face of the notch is connected to the upper end face of the oil receiving tank, thereby ensuring the overall sealing performance after the oil receiving tank and the environmental test chamber are connected.

[0028] (6) The environmental test chamber is movable and can move on the slide rail, making it easy to operate.

[0029] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages will become apparent from the description or be learned by practicing this invention. The objectives and other advantages of this invention can be realized and obtained from the details specifically pointed out in the text and accompanying drawings. Attached Figure Description

[0030] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0031] Figure 1 This is a schematic diagram of the structure of the aviation pump testing system in the embodiment;

[0032] Figure 2 This is one of the structural schematic diagrams of the tooling unit and oil receiving tank in the embodiment;

[0033] Figure 3 This is the second schematic diagram of the tooling unit and oil receiving tank in the embodiment.

[0034] Figure 4 This is a schematic diagram of the tooling unit in the embodiment;

[0035] Figure 5 This is a schematic diagram of the transmission mounting base in an embodiment;

[0036] Figure 6 This is a cross-sectional view of the transmission mounting base in an embodiment.

[0037] Figure label:

[0038] 1-Tooling unit, 11-Working platform, 111-Oil collection tank, 112-Oil leakage hole, 1121-Oil leakage flow pipe, 12-Aircraft pump tooling assembly, 121-Aircraft pump tooling, 1211-Receiving cavity, 122-Aircraft pump oil suction port, 123-Aircraft pump oil return port, 13-Transmission mounting base, 131-Base body, 132-Bearing, 133-First bearing end cover, 1331-First shaft seal, 1332-Second shaft seal, 134-Second bearing end cover, 1341-Third shaft seal, 135-Cooling assembly, 1351-First oil... 1352-Second oil passage, 1353-Third oil passage, 1354-Oil inlet, 1355-Oil outlet, 14-Motor assembly, 141-High-speed motor, 1411-Drive shaft, 142-Coupling, 143-Torque sensor, 2-Oil receiving tank, 21-Oil outlet, 22-Drain valve, 23-Level sensor, 3-Environmental test chamber, 31-Chamber, 311-Operable touch screen, 312-Aircraft pump return oil pipe interface, 313-Visual door, 32-Test board, 321-Pressure sensor, 33-Slide rail, 4-Aircraft pump. Detailed Implementation

[0039] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0040] Example 1

[0041] A specific embodiment of this utility model is as follows: Figure 1 As shown, an aviation pump 4 testing system is disclosed, including a tooling unit 1, an oil receiving tank 2, and an environmental testing chamber 3;

[0042] Tooling unit 1 includes an aircraft pump tooling assembly 12 and a motor assembly 14; the aircraft pump tooling assembly 12 is used to install the aircraft pump 4; the motor assembly 14 includes a high-speed motor 141 for driving the aircraft pump tooling assembly 12.

[0043] The oil collection tank 2 is located at the lower part of the aviation pump tooling assembly 12 and is used to collect the oil leaked during the disassembly and assembly of the pipeline in the aviation pump test tooling assembly 12.

[0044] The aircraft pump tooling assembly 12 is used to install the aircraft pump 4; the environmental test chamber 3 is used to test the aircraft pump 4 under different temperatures, pressures and flow rates.

[0045] This embodiment includes a tooling unit 1, an oil receiving tank 2, and an environmental testing chamber 3. The tooling unit 1 provides tooling for the aircraft pump 4, the oil receiving tank 2 collects oil leaked during pipe disassembly and assembly in the aircraft pump testing tooling assembly 12, and the environmental testing chamber 3 conducts high-temperature and different pressure tests on the aircraft pump 4. The aircraft pump testing system of this embodiment meets the life test requirements of the aircraft pump 4 for high-speed drive, high-temperature media, and high-temperature environment. The high-speed drive uses a high-speed motor 141 for direct connection, resulting in a simple and compact structure that ensures reliable long-term operation of the aircraft pump 4 within its lifespan. Furthermore, its simple and compact structure, low cost, small footprint, and ease of installation and use make it convenient.

[0046] Specifically, such as Figure 2 and Figure 4 As shown, tooling unit 1 includes an aviation pump tooling assembly 12 and a transmission mounting base 13.

[0047] Furthermore, tooling unit 1 also includes a work platform 11. The aviation pump tooling assembly 12 and the transmission mounting base 13 are mounted on the work platform 11.

[0048] like Figure 4 As shown, the upper surface of the working platform 11 is provided with multiple longitudinal T-shaped grooves, which are oil collection tanks 111 for collecting leaked oil. The bottom of the oil collection tank 111 is provided with oil leakage holes 112, which are located on both sides of the working platform 11 near the end of the aviation pump tooling assembly 12. The leaked oil flows directly into the oil receiving tank 2 through the oil leakage flow pipe 1121.

[0049] For ease of operation, the aircraft pump tooling assembly 12 is located at one end of the working platform 11. The aircraft pump tooling assembly 12 includes an aircraft pump tool 121, an aircraft pump suction port 122, and an aircraft pump return port 123.

[0050] The main body of the aircraft pump fixture 121 is a cylindrical structure, with an internal T-shaped accommodating cavity 1211. The T-shaped accommodating cavity 1211 includes a large-diameter end and a small-diameter end. The large-diameter end is used to install the aircraft pump 4, and the small-diameter end is connected to the transmission mounting base 13 via a transmission shaft 1411. The accommodating cavity 1211 of the aircraft pump fixture 121 has various specifications, enabling the testing of different types of aircraft pumps 4.

[0051] The aircraft pump fixture 121 and the transmission mounting base 13 are connected by a flange. Preferably, the flange is a stop flange, and the coaxiality of the installation is ensured to be ≤0.03mm through machining accuracy. During experimental operation, the aircraft pump 4 is installed on the aircraft pump fixture 121. To facilitate the loading and unloading of products by workers, the height of the aircraft pump 4 is set to 750-1000mm.

[0052] The oil suction port 122 of the aircraft pump is located on the wall of the oil receiving tank 2 to meet the low flow resistance requirements of certain models of aircraft pump 4. The oil return port 123 of the aircraft pump is located on the upper test plate 32 of the aircraft pump 4 to solve the problem of insufficient space due to numerous pipelines and to facilitate operator operation.

[0053] The transmission mounting base 13 is located at the end of the working platform 11. The transmission mounting base 13 not only lubricates and cools the bearing 132 inside the transmission mounting base 13, but also prevents leakage of high-temperature media inside the aviation pump 4. The transmission mounting base 13 includes a base body 131, a bearing 132, an end cover assembly, and a cooling assembly 135.

[0054] like Figure 5 and Figure 6 As shown, bearings 132 are disposed at both ends of the drive shaft 1411. The end cover assembly includes a first bearing end cover 133 and a second bearing end cover 134 disposed on both sides of the housing 131. The end cover assembly is provided with shaft seals for sealing the interior of the housing 131. The first bearing end cover 133 is the output shaft end, and has a first shaft seal 1331 and a second shaft seal 1332 disposed opposite to each other to simultaneously meet bidirectional pressure without leakage under both positive and negative pressure. The second bearing end cover 134 is the input shaft end, and has a third shaft seal 1341 disposed thereon. The first shaft seal 1331, the second shaft seal 1332 and the third shaft seal 1341 are high-temperature and high-pressure resistant shaft seals, used to ensure that when a certain positive and negative pressure is generated inside the aviation pump 4, the high-temperature medium inside the aviation pump 4 will not leak into the transmission mounting base 13.

[0055] A sealing ring is provided at the connection between the first bearing end cover 133 and the second bearing end cover 134 and the seat body 131 to enhance the sealing performance of the transmission mounting seat 13.

[0056] The cooling assembly 135 is used to cool the shaft seal to extend its life. The cooling assembly 135 includes an oil inlet 1354, an oil outlet 1355, a first oil passage 1351, a second oil passage 1352, and a third oil passage 1353. The first oil passage 1351, the second oil passage 1352, and the third oil passage 1353 are located inside the housing 131. The first oil passage 1351 and the second oil passage 1352 communicate with the oil inlet 1354, and the third oil passage 1353 communicates with the oil outlet 1355. The first oil passage 1351 and the third oil passage 1353 communicate with the first bearing end cap 133 and the second bearing end cap 134. The second oil passage 1352 communicates with the rotating shaft. The oil inlet 1354 is connected to the oil outlet 1355 via the housing 131, allowing lubricating oil to enter the housing 131 through the oil inlet 1354 to cool and lubricate the bearing 132, and to cool the first bearing end cover 133 and the second bearing end cover 134, before flowing out from the oil outlet 1355. The oil inlet 1354 and the oil outlet 1355 are connected to the lubrication pump station via hoses.

[0057] Lubricating oil enters the housing 131 through the oil inlet 1354. Part of it flows through the first oil passage 1351, through the first bearing end cover 133 and the second bearing end cover 134, and then through the third oil passage 1353 to the oil outlet 1355, cooling the first bearing end cover 133 and the second bearing end cover 134. Another part flows through the second oil passage 1352 through the rotating shaft and is thrown out by centrifugal force under the rotation of the shaft, cooling and lubricating the bearing 132 before flowing to the oil outlet 1355. The oil outlet 1355 is connected to an external oil extraction device to extract the lubricating oil from the housing 131 for recycling.

[0058] By providing a first shaft seal 1331 and a second shaft seal 1332 inside the first bearing end cover 133, and a third shaft seal 1341 inside the second bearing end cover 134, the seat body 131 is sealed, improving the sealing performance and stability of the transmission mounting seat 13 during operation, preventing oil and gas leakage, ensuring that the oil in the transmission mounting seat 13 will not leak during high-speed operation, and preventing gas from being drawn in under the negative pressure of the lubricating oil pump.

[0059] Preferably, the transmission mounting base 13 further includes a temperature sensor, which is installed on the bearing 132 to monitor the temperature of the bearing 132 during operation and transmit the temperature signal to the computer. When the temperature exceeds the set value, the computer will issue an alarm to prevent the bearing 132 from overheating and causing damage to the components.

[0060] Compared to the prior art, the transmission mounting base 13 of this embodiment is internally equipped with a cooling assembly 132. The first oil passage 1351 and the third oil passage 1353 are connected to the first bearing end cover 133 and the second bearing end cover 134. Lubricating oil flows through the first oil passage 1351 and the third oil passage 1353 to cool the bearing 132 end cover and the shaft seal connected to the bearing 132 end cover, thus extending the service life of the shaft seal. The lubricating oil flows through the second oil passage 1352 through the rotating shaft and is thrown out by centrifugal force under the rotation of the shaft, thus cooling and lubricating the bearing 132. A first shaft seal 1331 and a second shaft seal 1332 are provided inside the bearing end cover 133, and a third shaft seal 1341 is provided inside the second bearing end cover 134. This improves the sealing and stability of the mounting base during operation and prevents oil and gas leakage. The temperature of the bearing 132 is monitored during operation by a temperature sensor, and an alarm is triggered in time when the temperature of the bearing 132 is too high to prevent damage to components due to high temperature. Therefore, the transmission mounting base 13 not only lubricates and cools the bearing 132 inside the mounting base, but also prevents the leakage of high-temperature medium inside the aviation pump 4.

[0061] Furthermore, such as Figure 4 As shown, the motor assembly 14 includes a high-speed motor 141 and a coupling 142, which is connected to the output shaft of the high-speed motor 141. For example, to meet the performance testing requirements of the aircraft pump 4 at high speeds, the coupling 142 of the high-speed motor 141 is an expansion-sleeve diaphragm coupling 142.

[0062] Furthermore, the tooling unit 1 also includes a torque sensor 143, which is connected to the transmission mounting base 13 via a coupling 142, and is used to measure the transmission torque value and speed of the motor 141.

[0063] like Figure 3 As shown, the oil collection tank 2 is located at the lower part of the aircraft pump 4 and is used to collect oil leaked during pipeline disassembly when replacing the aircraft pump 4. For example, the tank body of the oil collection tank 2 is made of stainless steel plate.

[0064] The side wall of the oil receiving tank 2 is equipped with the oil suction pipe of the aviation pump 4, which is convenient for disassembly and assembly and prevents leakage.

[0065] The oil leakage flow pipe 1121 connected to the oil leakage hole 112 of the working platform 11 is set at the upper part of the oil receiving tank 2 to collect the oil leaked from the working platform 11 into the oil receiving tank 2.

[0066] like Figure 2As shown, an oil drain port 21 is provided at the bottom of the oil receiving tank 2, and the oil drain port 21 is connected to an external oil pumping device through a pipe. A drain valve 22 is provided on the pipe of the oil drain port 21, and a liquid level sensor 23 is also provided. The host computer software performs closed-loop control with the oil pump through the liquid level sensor 23, and the PLC control cabinet controls the contactor to perform closed-loop control with the oil pump through the liquid level gauge. When the liquid level reaches a certain height, the system is remotely controlled to automatically pump oil into the hydraulic system, ensuring that the oil does not spill and reducing labor costs.

[0067] like Figure 1 As shown, the environmental test chamber 3 includes a chamber body 31, a test plate 32, and a slide rail 33. The chamber body is movable. For example, the chamber body 31 is mounted on the slide rail 33 for easy movement.

[0068] The oil receiving groove 2 is located at the lower part of the housing 31. The lower part of the housing 31 has a notch, the upper surface of which forms an angle with the vertical direction, and the upper surface of the oil receiving groove 2 forms an angle with the horizontal direction; the upper surface of the notch connects with the upper surface of the oil receiving groove 2, thus ensuring the overall sealing of the oil receiving groove 2 and the environmental test chamber 3 after connection, ensuring that the environmental test chamber 3 can be sealed. The test plate 32 and the oil receiving groove are installed on the side of the housing 31 and locked and pressed by a latch-type quick clamp. Furthermore, a high-temperature resistant sealing strip is provided at the connection between the test plate 32 and the housing 31 to keep the interior of the environmental test chamber 3 sealed at high temperatures. The aviation pump fixture 121 extends into the interior of the environmental test chamber 3 through the test plate, allowing the aviation pump 4 to be tested within the sealed environment of the environmental test chamber 3.

[0069] like Figure 2 and Figure 3 As shown, the test board 32 is equipped with an oil return pipe interface for the aviation pump 4, which is connected to the outlet of the aviation pump 4 via a metal hose for easy disassembly.

[0070] The environmental test chamber 3 integrates multiple inlet and outlet interfaces and pressure measurement interfaces for aviation pumps 4, which can meet the testing requirements of various multi-interface aviation pumps 4 and the pressure measurement requirements of aviation pump 4 inlet and outlet within 100mm.

[0071] Compared to existing aviation pump testing systems, the oil collection tank 2 and the oil collection tank 111 of the working platform 11 ensure that the aviation pump 4 does not leak oil during high-altitude and ground tests. The transmission mounting base 13 is equipped with an oil passage, which not only lubricates and cools the bearing 132 inside the mounting base, but also prevents the leakage of high-temperature media inside the aviation pump 4. The medium is fuel oil with a maximum temperature of 150°C or lubricating oil with a maximum design temperature of 220°C, and the maximum design temperature can reach 250°C. The aviation pump 4 testing system of this embodiment can ensure that the aviation pump 4 can operate continuously without failure under high-temperature media and environment conditions, and ensure long-term reliable operation during life tests.

[0072] Example 2

[0073] This embodiment is an improvement on embodiment 1.

[0074] Furthermore, the test board 32 is also equipped with a pressure sensor 321, which is located on the top of the test board 32 and is connected to the aviation pump 4 through a pipeline and a navigation beacon connector. It is used to collect the pressure values ​​at the inlet and outlet of the aviation pump 4. At the same time, it solves the problem that the sensor cannot withstand the high temperature of 200℃, and facilitates centralized disassembly and wiring.

[0075] The test plate 32 is equipped with a navigation beacon connector interface that leads to the outside of the environmental test chamber 3 and is connected to the pressure sensor 321. The navigation beacon connector is equipped with anti-rotation screw holes, which are evenly distributed around the circumference of the connector to prevent the connector from rotating with the mating nut during pipeline disassembly and assembly, thus ensuring the connection of the pipeline and the sealing effect of the environmental test chamber 3.

[0076] An operable touchscreen 311 is installed on the outside of the enclosure 31 of the environmental test chamber 3. It is connected to a host computer via Ethernet and can be operated locally or remotely. The viewing doors 312 on both sides of the environmental test chamber 3 allow observation of the operation status of the aviation pump 4 inside the environmental test chamber 3, as well as to observe whether there are leaks in the pipeline, pipeline vibration, and the state of the oil in the oil tank 2.

[0077] The upper part of the housing 31 is equipped with an exhaust port and an oil-gas separator, which can filter the exhaust fumes in high-temperature environment tests to prevent environmental pollution. The oil-gas removal efficiency is 99.9%.

[0078] Furthermore, a remote control system, including host computer software, is also provided. The host computer software sends commands to the frequency converter, which remotely controls motor 141 to continuously adjust the pump speed. Motor 141 can be set to rotate according to the different rotation directions of the aviation pump 4 via the host computer interface, allowing for life testing of the aviation pump 4. When the oil level in the oil tank 2 reaches a certain height, the host computer software establishes a closed-loop control system with the oil pump through the level gauge. The PLC control cabinet controls the contactor, and through the level gauge and oil pump, remotely controls the automatic pumping of oil into the hydraulic system.

[0079] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. An aircraft pump testing system, characterized in that, It includes a tooling unit (1), an oil receiving tank (2), and an environmental testing chamber (3); The tooling unit (1) includes an aviation pump tooling assembly (12) and a motor assembly (14); the aviation pump tooling assembly (12) is used to install the aviation pump (4); the motor assembly (14) includes a high-speed motor (141) for driving the aviation pump tooling assembly (12); The oil receiving tank (2) is located at the lower part of the aviation pump tooling assembly (12) and is used to collect the oil leaked during the disassembly and assembly of the pipeline in the aviation pump tooling assembly (12). The environmental test chamber (3) is used to test the aviation pump (4) under different temperatures, pressures and flow rates.

2. The aircraft pump testing system according to claim 1, characterized in that, The tooling unit (1) also includes a working platform (11), which is provided with multiple oil collection tanks (111). The bottom of the oil collection tank (111) is provided with an oil leakage hole (112), which is connected to the oil receiving tank (2) through an oil leakage flow pipe (1121).

3. The aircraft pump testing system according to claim 1, characterized in that, The bottom of the oil receiving tank (2) is provided with an oil drain port (21), which is connected to an external oil pumping device; the oil receiving tank (2) is provided with a liquid level sensor (23).

4. The aircraft pump testing system according to claim 1, characterized in that, The tooling unit (1) includes a transmission mounting base (13); the transmission mounting base (13) is provided with a transmission shaft (1411) of a motor assembly (14); the transmission shaft (1411) is connected to the aviation pump tooling assembly (12).

5. The aircraft pump testing system according to claim 4, characterized in that, The tooling unit (1) also includes a torque sensor (143), which is disposed between the motor assembly (14) and the transmission mounting base (13).

6. The aircraft pump testing system according to claim 4, characterized in that, The aircraft pump tooling assembly (12) includes an aircraft pump tooling (121), an aircraft pump suction port (122), and an aircraft pump return port (123); one end of the aircraft pump tooling (121) is connected to the aircraft pump (4), and the other end is connected to the transmission mounting base (13); The aviation pump suction port (122) is located on the wall of the oil receiving tank (2), and the aviation pump return port (123) is located on the upper part of the aviation pump (4); the aviation pump suction port (122) and the aviation pump return port (123) are connected to the aviation pump (4).

7. The aircraft pump testing system according to claim 6, characterized in that, The aviation pump fixture (121) has an internal accommodating cavity (1211) for installing the aviation pump (4); there are multiple aviation pump fixtures (121), and the accommodating cavities (1211) of the multiple aviation pump fixtures (121) have different sizes.

8. The aircraft pump testing system according to claim 1, characterized in that, The environmental test chamber (3) includes a chamber body (31) and a test plate (32); The test plate (32) is disposed on the side of the box (31); a high-temperature resistant sealing strip is provided at the connection between the test plate (32) and the box (31); The lower part of the box (31) has a notch, the upper end face of the notch is at an angle to the vertical direction, and the upper end face of the oil receiving groove (2) is at an angle to the horizontal direction; the upper end face of the notch is connected to the upper end face of the oil receiving groove (2).

9. The aircraft pump testing system according to claim 8, characterized in that, The test board (32) is provided with multiple pressure sensors (321) and pressure measuring interfaces; the pressure sensors (321) and the pressure measuring interfaces are located above the aviation pump (4) and are connected to the aviation pump (4).

10. The aircraft pump testing system according to claim 8, characterized in that, The environmental test chamber (3) also includes a slide rail (33), and the chamber body (31) is mounted on the slide rail (33).

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