A test system for an aircraft ground vent valve

Abstract

The utility model discloses a kind of test systems of aircraft ground ventilation valve, including the gas source system and test pipeline system connected;Test pipeline system includes gas source gas path port valve, gas source gas path port pressure sensor, safety valve, pressure regulating valve, flowmeter and flow regulating valve;The gas outlet of gas source system is connected with the side interface of gas source gas path port valve;Gas source gas path port valve other side interface is connected with pneumatic tee valve first interface by a test pipeline which is sequentially arranged gas source gas path port pressure sensor, safety valve, pressure regulating valve and flowmeter;Pneumatic tee valve second interface and third interface are connected with the front end interface of an special test tool respectively;Special test tool rear end interface is connected with flow regulating valve;The aircraft ground ventilation valve to be tested is installed in each special test tool.The utility model can conveniently and reliably carry out flow resistance test and durability test to aircraft ground ventilation valve, and significantly improve test efficiency.

Description

Technical Field

[0001] This utility model relates to the field of aircraft ventilation system testing technology, and in particular to a testing system for aircraft ground ventilation valves, used for flow resistance testing and durability testing of aircraft ground ventilation valves. Background Technology

[0002] Aircraft ground ventilation valves are an important component of the aircraft environmental control system. During their research and development and production, flow resistance tests and durability tests must be conducted to verify whether they meet the design functional performance and durability requirements.

[0003] The flow resistance test for aircraft ground ventilation valves refers to testing the pressure difference across the valve under simulated operating conditions. The flow resistance test is primarily used to verify whether the flow resistance performance of the aircraft ground ventilation valves meets design specifications.

[0004] The durability test of aircraft ground ventilation valves involves subjecting these valves to multiple opening and closing cycles under simulated operating conditions to verify their reliability and performance. The primary purpose of this durability test is to verify their reliability and performance, expose design and manufacturing defects, and provide a basis for improvement.

[0005] Currently, traditional flow resistance testing of aircraft ground ventilation valves mainly relies on existing aircraft environmental control testing systems and specialized testing fixtures, typically allowing only one valve to be tested at a time. However, depending on the installation requirements, aircraft ground ventilation valves must be able to withstand multiple (e.g., typically over 4000) work cycles. Existing traditional aircraft environmental control testing systems are difficult to automate quickly and require manual operation. Furthermore, traditional dedicated environmental control testing systems for aircraft are often costly, complex, and lack specificity and efficiency in conducting flow resistance and durability tests on aircraft ground ventilation valves.

[0006] Therefore, establishing a dedicated flow resistance and durability testing system for aircraft ground ventilation valves has become an important guarantee technology for the research and development and production of aircraft ground ventilation valves.

[0007] Therefore, there is an urgent need to develop a technology that can solve the above-mentioned technical problems. Utility Model Content

[0008] The purpose of this invention is to address the technical deficiencies of existing technologies by providing a testing system for aircraft ground ventilation valves.

[0009] Therefore, this utility model provides a test system for aircraft ground ventilation valves, including an air source system and a test pipeline system;

[0010] The air supply system is connected to the test pipeline system and is used to output compressed air to the test pipeline system;

[0011] The test piping system includes gas source and gas line port valves, gas source and gas line port pressure sensors, safety valves, pressure regulating valves, flow meters, pneumatic three-way valves, two dedicated test fixtures, and two flow regulating valves;

[0012] The outlet of the gas source system is connected to one side interface of the gas source gas circuit port valve;

[0013] The other side of the gas source air passage port valve is connected to the first port of the pneumatic three-way valve through a test pipeline that is sequentially equipped with a gas source air passage port pressure sensor, a safety valve, a pressure regulating valve and a flow meter;

[0014] The second and third ports of the pneumatic three-way valve are respectively connected to the front end port of a dedicated test fixture;

[0015] The rear interface of each dedicated test fixture is connected to a flow regulating valve.

[0016] Each specialized test fixture contains a sealed ground ventilation valve for the aircraft to be tested.

[0017] As can be seen from the technical solution provided by this utility model above, compared with the prior art, this utility model provides a test system for aircraft ground ventilation valves. It is scientifically designed and can conveniently and reliably conduct flow resistance tests and durability tests on aircraft ground ventilation valves, significantly improving test efficiency and saving test manpower costs, which has great practical significance. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of a test system for an aircraft ground ventilation valve provided by this utility model;

[0019] Figure 2 This is a top view of a test piping system of one embodiment of a test system for an aircraft ground ventilation valve provided by this utility model;

[0020] Figure 3 This is a front view of the test piping system of one embodiment of the test system for an aircraft ground ventilation valve provided by this utility model;

[0021] Figure 4 This is a schematic diagram of the structure of the front-end pipeline of the product installation in a test system for an aircraft ground ventilation valve provided by this utility model;

[0022] Figure 5 This is a schematic diagram of the structure of the rear-end pipeline of an aircraft ground ventilation valve test system provided by this utility model;

[0023] Figure 6 This utility model provides a test system for an aircraft ground ventilation valve, and a three-dimensional structural schematic diagram of an aircraft ground ventilation valve to be tested.

[0024] Figure 7 The present invention provides a test system for an aircraft ground ventilation valve, which is a three-dimensional exploded view of the aircraft ground ventilation valve installed in a product installation pipeline.

[0025] In the diagram, 1-gas source system, 2-test pipeline system, 3-measurement and control system, 4-gas source gas line port valve, 5-gas source gas line port pressure sensor;

[0026] 6-Safety valve, 7-Pressure regulating valve, 8-Flow meter, 9-Pneumatic three-way valve, 10-Absolute pressure transmitter;

[0027] 11-Specialized test fixture; 12-Differential pressure transmitter; 13-Flow regulating valve; 14-Time relay; 15-Data logger.

[0028] 16-Gas circuit controller, 17-Test pipeline system air inlet, 18-Safety valve mounting interface, 19-Flow measurement pipeline, 20-Flow meter mounting interface;

[0029] 21-Absolute pressure transmitter interface; 22-Special tooling inlet bend; 23-Product installation pipeline; 24-Special tooling exhaust bend; 25-Product installation front-end pipeline.

[0030] 26-Product installation back-end piping; 27-Differential pressure transmitter interface; 28-Aircraft ground ventilation valve. Detailed Implementation

[0031] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0032] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0033] In the description of this patent, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "setting" should be interpreted broadly. For example, they can refer to a fixed connection or setting, a detachable connection or setting, or an integral connection or setting. Those skilled in the art can understand the specific meaning of the above terms in this patent according to the specific circumstances.

[0034] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0035] See Figures 1 to 7 This utility model provides a test system for aircraft ground ventilation valves, including an air source system 1 and a test pipeline system 2;

[0036] Air source system 1 is connected to test pipeline system 2 and is used to output compressed air to test pipeline system 2;

[0037] The test pipeline system 2 includes a gas source and gas line port valve 4, a gas source and gas line port pressure sensor 5, a safety valve 6, a pressure regulating valve 7, a flow meter 8, a pneumatic three-way valve 9, two special test fixtures 11, and two flow regulating valves 13;

[0038] The air outlet of the air source system 1 (specifically the air outlet of the air compressor) is connected to one side interface of the air source air passage port valve 4;

[0039] The other side of the gas source air passage port valve 4 is connected to the first port of the pneumatic three-way valve 9 through a test pipeline that is sequentially equipped with a gas source air passage port pressure sensor 5, a safety valve 6, a pressure regulating valve 7 and a flow meter 8.

[0040] The second and third ports of the pneumatic three-way valve 9 are respectively connected to the front end port of a dedicated test fixture 11;

[0041] The rear interface of each dedicated test fixture 11 is connected to a flow regulating valve 13.

[0042] Each dedicated test fixture 11 has a sealed installation of an aircraft ground ventilation valve 28 to be tested.

[0043] It should be noted that the air source system 1 is used to generate high-pressure, high-flow-rate compressed air to supply air to the test pipeline system 2. Specifically, the air source system 1 can be an air compressor or a high-pressure gas cylinder.

[0044] It should be noted that the special test fixture 11 is connected to the external atmospheric environment through the flow regulating valve 13.

[0045] It should be noted that, for this utility model, the airflow generated by the air source system 1 passes through the pressure regulating valve 7, the pneumatic three-way valve 9, the special test fixture 11 and the flow regulating valve 13 in sequence. By adjusting the air source air passage port valve 4, the pressure regulating valve 7 and the flow regulating valve 13, the airflow pressure and flow rate in the air passage are controlled to simulate the airflow state in the aircraft environmental control pipeline.

[0046] It should be noted that the pneumatic three-way valve 9 is used to control the switching of the air path between the two dedicated test fixtures 11. The air source air path port pressure sensor 5 is installed after the air source air path port valve 4 and is used to measure the inlet pressure of the pipeline system 2. The safety valve 6 is installed after the air source air path port pressure sensor 5 and is used to release pressure in the event of an abnormal pressure increase in the test pipeline system 2, ensuring the safety of the test system. The flow meter 8 is installed after the pressure regulating valve 7 and is used to measure the flow rate of the airflow in the test pipeline system 2.

[0047] In practice, the front end of the special test fixture 11 is equipped with an absolute pressure transmitter 10;

[0048] The front and rear ends of the special test fixture 11 are respectively connected to the two test interfaces of the differential pressure transmitter 12;

[0049] It should be noted that the absolute pressure transmitter 10 is installed at the front end of the special test fixture 11 and is used to measure the absolute pressure of each gas path. The differential pressure transmitter 12 is used to measure the pressure difference between the front and rear ends of the test object (i.e., the aircraft ground ventilation valve to be tested) to obtain the flow resistance of the aircraft ground ventilation valve in the working state.

[0050] In this utility model, each special test fixture 11 includes a special fixture air inlet bend 22, a product installation pipeline 23, and a special fixture exhaust bend 24.

[0051] The front and rear ends of the installation pipe 23 of each product are respectively sealed and connected to the rear end of the special tooling intake bend 22 and the front end of the special tooling exhaust bend 24.

[0052] The front end interface of each special tooling air inlet bend 22 is used to be sealed to one of the interfaces of the second and third interfaces included in the pneumatic three-way valve 9 (the front end interfaces of the special tooling air inlet bends 22 of the two special test toolings 11 are respectively connected to the second interface and the third interface).

[0053] Each product installation pipe 23 is sealed with an aircraft ground ventilation valve 28 to be tested.

[0054] For specific implementation details, see [link / reference] Figure 3 As shown, each product installation pipeline 23 includes a product installation front pipeline 25 and a product installation rear pipeline 26;

[0055] The front end interface of the product installation front pipe 25 is sealed and connected to the rear end interface of the special tooling air intake bend 22.

[0056] The rear end interface of the product installation front end pipe 25 and the front end interface of the product installation rear end pipe 26 are respectively sealed and connected to the front and rear ends of the ground ventilation valve 28 of the aircraft to be tested.

[0057] The rear end interface of the product installation rear pipe 26 is sealed and connected to the front end interface of the special tooling exhaust bend 24.

[0058] It should be noted that, see Figure 4 , Figure 5 As shown, the product installation front-end pipe 25 uses front and rear flange connections. The side connecting to the ground ventilation valve of the aircraft under test is designed according to the front-end interface of the aircraft ground ventilation valve. The product installation rear-end pipe 26 uses front and rear flange connections. The end connecting to the ground ventilation valve 28 of the aircraft under test is designed with a sealing gasket mounting groove.

[0059] like Figure 4 , Figure 5 As shown, before the test, based on the structural characteristics of the aircraft ground ventilation valve 28, the product installation front end pipe 25 and the product installation rear end pipe 26 were designed to ensure that the aircraft ground ventilation valve 28 was sealed and installed in the product installation pipe 23.

[0060] Furthermore, a differential pressure transmitter interface 27 is provided on the product installation front-end pipeline 25 and the product installation rear-end pipeline 26 respectively;

[0061] The differential pressure transmitter 12 has two test lines, each connected to a differential pressure transmitter interface 27.

[0062] It should be noted that the differential pressure transmitter interface 27 is used to install the pressure measuring tube of the differential pressure transmitter 12, with one in front of and one behind the ground ventilation valve 28 of the aircraft being tested.

[0063] It should be noted that the special tooling inlet bend 22 is used to simulate the bending state of the aircraft's environmental control piping (e.g., a 122° bend). The product installation pipe 23 is used to install the ground ventilation valve 28 of the aircraft to be tested. The special tooling exhaust bend 24 is used to connect the product installation pipe 23 and the flow control valve 13.

[0064] It should be noted that, for this utility model, the special tooling inlet bend 22 and the special tooling exhaust bend 24 are designed according to the installation state of the aircraft ground ventilation valve, simulating its installation angle to ensure the authenticity of the test boundary. The special tooling inlet bend 22 and the special tooling exhaust bend 24 simulate the actual installation state of the aircraft ground ventilation valve, maintaining the same bending angle as the installation air path.

[0065] It should be noted that, for this utility model, the product installation pipe 23 is designed according to the aircraft ground ventilation valve installation interface to ensure that the product under test can be sealed in the product installation pipe 23 and guarantee the test sealing performance.

[0066] In practice, the straight section of the front end of the special tooling air inlet bend 22 is equipped with an absolute pressure transmitter interface 21.

[0067] An absolute pressure transmitter 10 is installed at interface 21.

[0068] It should be noted that the absolute pressure transmitter interface 21 is used to install the pressure measuring tube of the absolute pressure transmitter 10.

[0069] In this utility model, in its specific implementation, as follows: Figure 2 As shown, the front end of the test pipeline is provided with a test pipeline system air inlet 17;

[0070] The air inlet 17 of the test pipeline system is connected to the other side interface of the air source air passage port valve 4.

[0071] In practice, a safety valve installation interface 18 is provided in the test pipeline between the air inlet 17 of the test pipeline system and the pressure regulating valve 7.

[0072] A safety valve 6 is installed on the safety valve mounting interface 18.

[0073] In this utility model, specifically, the test pipeline section located between the pressure regulating valve 7 and the pneumatic three-way valve 9 is the flow measurement pipeline 19;

[0074] A flow meter mounting interface 20 is provided on the flow measurement pipeline 19;

[0075] A flow meter 8 is installed on the flow meter installation interface 20.

[0076] It should be noted that, to ensure the accuracy of flow measurement, the flow measurement pipeline 19 uses a long straight pipe, the length of which must be no less than 15 times the diameter of the test pipeline, to ensure a relatively stable airflow measured by the flow meter 8. The flow measurement pipeline 19 consists of two parts, a first straight pipe section and a second straight pipe section distributed front and rear, and the connection between the two parts is provided with a flow meter installation interface 20. The flow meter installation interface 20 is used to install the flow meter. The front end of the flow meter installation interface 20 must ensure that the length of the first straight pipe section in the flow measurement pipeline 19 connected to it is greater than 10 times the diameter of the test pipeline, and the rear end of the flow meter installation interface 20 must ensure that the length of the second straight pipe section connected to it is greater than 5 times the diameter of the test pipeline. In this example, a thermal mass flow meter is selected.

[0077] In this utility model, specifically, the experimental system of this utility model also includes a measurement and control system 3;

[0078] The measurement and control system 3 includes a time relay 14, a data logger 15, and a gas circuit controller 16;

[0079] The signal output terminal of the time relay 14 is connected to the signal control terminal of the pneumatic three-way valve 9 in the test pipeline system 2;

[0080] The data signal acquisition terminal of the data logger 15 is connected to the data signal output terminals of the flow meter 8, the absolute pressure transmitter 10, and the differential pressure transmitter 12, respectively.

[0081] The gas circuit controller 16 is connected to the gas source gas circuit port valve 4, the pressure regulating valve 7 and the flow regulating valve 13 respectively, and is used to control the working status (e.g., on / off status) of these valves.

[0082] It should be noted that the time relay 14 is used to control the switching time and frequency of the pneumatic three-way valve 9. The data logger 15 is used to record the data measured by the flow meter 8, the absolute pressure transmitter 10, and the differential pressure transmitter 12. The air circuit controller 16 is used to control the operating status (control the opening and closing status of the valves) of these valves in the test pipeline system 2 by sending control signals to the air source air circuit port valve 4, the pressure regulating valve 7, and the flow regulating valve 13, thereby adjusting the airflow parameters.

[0083] It should be noted that the time relay 14 can control the pneumatic three-way valve 9 to switch the air path between the two sets of special test fixtures 11 at a certain frequency, so that the flow resistance test and durability test of two aircraft ground ventilation valves can be carried out at the same time.

[0084] In terms of specific implementation, the pneumatic controller 16 can be a mature industrial control computer with signal control and data storage functions, which will not be described in detail here. The data logger 15 can be a mature data logger with data acquisition and storage functions, which will not be described in detail here.

[0085] It should be noted that the measurement and control system 3 is used to measure and control airflow parameters and control the conversion of airflow in the passages of the two dedicated test fixtures 11.

[0086] To better understand the technical solution of this utility model, the working process of this utility model is described below.

[0087] I. For example Figure 1 As shown, when conducting the flow resistance test of the aircraft ground ventilation valve, two sets of products (i.e., two sets of aircraft ground ventilation valves) are installed simultaneously in two product installation pipelines 23 (i.e., two sets of ground ventilation valves are installed simultaneously in two special test fixtures 11), the measurement and control system 3 is connected, the pneumatic three-way valve 9 is started, only one test pipeline with special test fixture 11 is opened, and the air source system 1 is started.

[0088] After the air source output stabilizes, simultaneously adjust the air source port valve 4, pressure regulating valve 7, and flow regulating valve 13 to simulate the airflow parameters of the aircraft's environmental control system: ensuring that the airflow pressure measured by the absolute pressure transmitter 10 is within the range of 120 kPa ± 2 kPa, and that the airflow mass flow rate measured by the flow meter 8 is within the range of 1400 kg / h ± 50 kg / h. After the airflow parameters stabilize (i.e., after the airflow reaches the specified airflow parameters and stabilizes), measure the pressure difference between the front and rear ends of the aircraft's ground ventilation valve using the differential pressure transmitter 12, and measure its flow resistance.

[0089] After the measurement is completed, the pneumatic three-way valve 9 can be activated to switch the airflow to another test pipeline with a dedicated test fixture 11. After the airflow parameters meet the requirements and stabilize, the flow resistance of the aircraft ground ventilation valve in the other test pipeline can be tested.

[0090] 2. When conducting the durability test of the aircraft ground ventilation valve, install the two sets of products (i.e., the two sets of aircraft ground ventilation valves) simultaneously in the two-way special test fixture 11, connect the measurement and control system 3, and start the air source system 1.

[0091] After the gas source is stabilized, adjust the gas source port valve 4, pressure regulating valve 7 and flow regulating valve 13 respectively so that the air pressure and flow rate in the pipeline simulate the aircraft environmental control parameters: so that the air pressure measured by the absolute pressure transmitter 10 is within the range of 120kPa±2kPa, and the air mass flow rate measured by the flow meter 8 is within the range of 1400kg / h±50kg / h.

[0092] After the airflow parameters stabilize, the switching time of the time relay 14 is set to control the pneumatic three-way valve 9 to switch on and off according to the preset frequency and number of times (for example, after the airflow reaches the specified airflow parameters and stabilizes, the time relay 14 is set to control the pneumatic three-way valve 9 to switch the passage once every 2 minutes), thereby realizing the timed and frequency switching of the air path in the two sets of test pipelines to achieve the durability test of the aircraft ground ventilation valve for the specified number of times.

[0093] Compared with the prior art, the test system for aircraft ground ventilation valves provided by this utility model has the following beneficial effects:

[0094] 1. The system of this utility model can simulate the working conditions of the ground ventilation valve of an aircraft and test its flow resistance under normal working conditions;

[0095] 2. The system of this utility model establishes multiple test paths, which can simultaneously conduct functional performance tests on multiple (e.g., two) aircraft ground ventilation valves;

[0096] 3. The system of this utility model adopts a gas path conversion design, which can control the conversion frequency and number of conversions of the gas path, thereby improving the experimental efficiency and saving manpower and material resources.

[0097] 4. This utility model designs an aircraft ground ventilation valve flow resistance testing and durability testing system. It simulates the actual installation state of the aircraft ground ventilation valve and the airflow parameters of the ventilation system, allowing for testing of its flow resistance parameters under operating conditions and verification of whether its performance meets design requirements. Through automatic airflow switching, multiple durability tests can be conducted quickly to verify whether its lifespan meets design requirements. This design effectively exposes defects in the product design stage, providing reliable data for product development. Furthermore, the multi-path design and rapid automatic switching improve testing efficiency and reduce testing costs.

[0098] In summary, this invention designs a test system for the flow resistance and durability of aircraft ground ventilation valves by simulating the airflow parameters of aircraft environmental control pipelines. This system replaces the traditional technique of conducting flow resistance and durability tests on aircraft ground ventilation valves within actual aircraft environmental control test systems. The system uses a high-pressure air source, enabling the simulation of higher pressure and larger flow rate airflow parameters, thus offering wider adaptability. The system employs a two-channel design, allowing simultaneous testing of two aircraft ground ventilation valves. Furthermore, the system utilizes an automatic replacement device, enabling automated durability testing of two ground ventilation valves, resulting in higher efficiency and lower cost.

[0099] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.

Claims

1. A testing system for aircraft ground ventilation valves, characterized in that, It includes a gas supply system (1) and a test pipeline system (2); The air supply system (1) is connected to the test pipeline system (2) and is used to output compressed air to the test pipeline system (2); The test pipeline system (2) includes a gas source gas line port valve (4), a gas source gas line port pressure sensor (5), a safety valve (6), a pressure regulating valve (7), a flow meter (8), a pneumatic three-way valve (9), two special test fixtures (11) and two flow regulating valves (13); The outlet of the gas source system (1) is connected to one side interface of the gas source gas path port valve (4); The other side of the gas source gas path port valve (4) is connected to the first port of the pneumatic three-way valve (9) through a test pipeline that is sequentially equipped with a gas source gas path port pressure sensor (5), a safety valve (6), a pressure regulating valve (7) and a flow meter (8); The second and third ports of the pneumatic three-way valve (9) are respectively connected to the front end port of a special test fixture (11); The rear end interface of each dedicated test fixture (11) is connected to a flow regulating valve (13); Each dedicated test fixture (11) has a sealed installation of an aircraft ground ventilation valve (28) to be tested.

2. The test system for aircraft ground ventilation valves as described in claim 1, characterized in that, The front end of the special test fixture (11) is equipped with an absolute pressure transmitter (10); The front and rear ends of the special test fixture (11) are connected to the test interfaces at both ends of the differential pressure transmitter (12).

3. The test system for aircraft ground ventilation valves as described in claim 1, characterized in that, Each special test fixture (11) includes a special fixture inlet bend (22), a product installation pipeline (23), and a special fixture exhaust bend (24); The front and rear ends of each product installation pipe (23) are respectively sealed and connected to the rear end of the special tooling air inlet bend (22) and the front end of the special tooling exhaust bend (24); The front end interface of each special tooling inlet bend (22) is used to be sealed to one of the interfaces of the second and third interfaces of the pneumatic three-way valve (9); Each product installation pipe (23) is sealed with an aircraft ground ventilation valve (28) to be tested.

4. The test system for aircraft ground ventilation valves as described in claim 3, characterized in that, The product installation piping (23) includes the product installation front-end piping (25) and the product installation rear-end piping (26); The front end interface of the product installation front end pipe (25) is sealed and connected to the rear end interface of the special tooling air inlet bend (22); The rear end interface of the product installation front end pipe (25) and the front end interface of the product installation rear end pipe (26) are respectively sealed and connected to the front and rear ends of the aircraft ground ventilation valve (28) to be tested. The rear end interface of the product installation rear pipeline (26) is sealed and connected to the front end interface of the special tooling exhaust bend (24).

5. The test system for aircraft ground ventilation valves as described in claim 4, characterized in that, A differential pressure transmitter interface (27) is provided on the product installation front-end pipeline (25) and the product installation rear-end pipeline (26); The differential pressure transmitter (12) has two test lines, each connected to a differential pressure transmitter interface (27).

6. The test system for aircraft ground ventilation valves as described in claim 3, characterized in that, The front straight section of the special tooling inlet bend (22) is equipped with an absolute pressure transmitter interface (21); An absolute pressure transmitter (10) is installed at the absolute pressure transmitter interface (21).

7. The test system for aircraft ground ventilation valves as described in claim 1, characterized in that, The front end of the test pipeline is provided with an air inlet for the test pipeline system (17); The air inlet (17) of the test pipeline system is connected to the other side interface of the air source air passage port valve (4).

8. The test system for aircraft ground ventilation valves as described in claim 1, characterized in that, A safety valve installation interface (18) is provided between the air inlet (17) of the test pipeline system and the pressure regulating valve (7); A safety valve (6) is installed on the safety valve mounting interface (18).

9. The test system for aircraft ground ventilation valves as described in any one of claims 1 to 8, characterized in that, The test pipeline section located between the pressure regulating valve (7) and the pneumatic three-way valve (9) is the flow measurement pipeline (19); A flow meter installation interface (20) is provided on the flow measurement pipeline (19); A flow meter (8) is installed on the flow meter mounting interface (20).

10. The test system for aircraft ground ventilation valves as described in any one of claims 1 to 9, characterized in that, It also includes the measurement and control system (3); The measurement and control system (3) includes a time relay (14), a data logger (15), and a pneumatic circuit controller (16); The signal output terminal of the time relay (14) is connected to the signal control terminal of the pneumatic three-way valve (9) in the test pipeline system (2); The data signal acquisition terminal of the data logger (15) is connected to the data signal output terminals of the flow meter (8), the absolute pressure transmitter (10), and the differential pressure transmitter (12), respectively. The gas circuit controller (16) is connected to the gas source gas circuit port valve (4), the pressure regulating valve (7) and the flow regulating valve (13), respectively.

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