A fuselage tank vent system performance verification system and method

Abstract

The application belongs to the technical field of general aviation ground test, and particularly relates to a fuselage oil tank ventilation system performance verification system and method. The system comprises: a fuselage test oil tank for storing test fuel and providing a mounting mechanical interface of the fuselage oil tank ventilation system; a flight environment pressure simulation box for simulating the external environment pressure of an airplane under high-altitude conditions; a fuselage cargo compartment environment pressure simulation box for simulating the internal environment pressure of the fuselage cargo compartment of the airplane; a test control computer for providing a certain human-computer interaction interface, manually inputting a pre-setting of a test parameter change process; a pressure controller connected with the test control computer, for receiving a pressure control instruction issued by the test control computer, directly sending a control instruction to each electric regulating valve, and making the electric regulating valve adjust in real time according to the instruction opening degree; and a pressure sensor connected with the pressure controller, for measuring the internal pressure of the fuselage test oil tank, the internal pressure of the flight environment pressure simulation box and the internal pressure of the fuselage cargo compartment environment pressure simulation box.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of general aviation ground test, and particularly relates to a fuselage oil tank ventilation system performance verification system and method. BACKGROUND

[0002] The fuel storage space of a transport aircraft or a transport and support integrated support aircraft is usually in a wing box structure, but a large refueling aircraft is designed to have a high oil carrying capacity and is provided with a fuselage oil tank in the cargo compartment. An independent ventilation system is installed on the upper part of the fuselage oil tank to prevent the pressure in the fuselage oil tank from being too high or too low during the climb or descent of the aircraft. In the existing test technology, the verification of the oil tank ventilation system is usually performed by verifying the independent components of the system in the factory, ignoring the influence of the structure and size of the fuselage oil tank, the installation position, the fuel quantity in the oil tank and other factors on the working state of the aircraft control system, and lacking comprehensive verification of the cross-linking working performance of the system components. Therefore, the oil tank ventilation system after installation is often inconsistent with the design value. How to solve this inconsistency and how to accurately verify the ventilation performance of the fuselage oil tank through ground test have become key technical problems.

[0003] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the aforementioned deficiencies of the prior art. SUMMARY

[0004] The application aims to provide a fuselage oil tank ventilation system performance verification system and method to solve at least one problem existing in the prior art.

[0005] The technical solution of the application is as follows:

[0006] The first aspect of the application provides a fuselage oil tank ventilation system performance verification system, comprising:

[0007] A fuselage test oil tank for storing test fuel, simulating the internal structure size and structure form of the fuselage oil tank in the actual installed state, and providing a mounting mechanical interface of the fuselage oil tank ventilation system;

[0008] A flight environment pressure simulation box, which is a negative pressure container, is used to simulate the external environment pressure of the aircraft under high altitude conditions. The flight environment pressure simulation box is connected with a vacuum system through a first vacuum pipeline and is in communication with the atmospheric environment through a first normal pressure pipeline. An electric regulating valve M2 is installed on the first vacuum pipeline, and an electric regulating valve M1 is installed on the first normal pressure pipeline.

[0009] The fuselage cargo compartment environment pressure simulation box is a negative pressure container used for simulating the environment pressure in the fuselage cargo compartment of an airplane, is connected with a vacuum system through a second vacuum pipeline, is communicated with the atmospheric environment through a second normal pressure pipeline, and is provided with an electric regulating valve M3 on the second vacuum pipeline and an electric regulating valve M4 on the second normal pressure pipeline.

[0010] A test control computer is configured to provide a certain man-machine interface and manually input a pre-set test parameter change process.

[0011] A pressure controller is connected with the test control computer, configured to receive a pressure control instruction issued by the test control computer and directly send the control instruction to each electric regulating valve so that the electric regulating valve is adjusted in real time according to the instruction opening degree.

[0012] A pressure sensor is connected with the pressure controller, configured to measure the internal pressure of the fuselage test oil tank, the internal pressure of the flight environment pressure simulation box and the internal pressure of the fuselage cargo compartment environment pressure simulation box.

[0013] In at least one embodiment of the present application, the fuselage test oil tank adopts a stainless steel metal oil tank to simulate the real fuselage oil tank structure of an airplane.

[0014] In at least one embodiment of the present application, the vacuum system adopts a vacuum pump group.

[0015] In at least one embodiment of the present application, the gas phase space in the flight environment pressure simulation box is directly communicated with the outlet of a safety valve and the outlet of an electric breather valve on the top of the fuselage test oil tank through a first communication pipeline.

[0016] In at least one embodiment of the present application, the gas phase space in the fuselage cargo compartment environment pressure simulation box is connected with a vacuum valve pressure sensing interface on the top of the fuselage test oil tank through a second communication pipeline.

[0017] In at least one embodiment of the present application, the pressure sensor includes a first pressure sensor P1, a second pressure sensor P2 and a third pressure sensor PX.

[0018] In at least one embodiment of the present application, the first pressure sensor P1 is arranged on the first communication pipeline.

[0019] In at least one embodiment of the present application, the second pressure sensor P2 is arranged on the top of the fuselage cargo compartment environment pressure simulation box.

[0020] In at least one embodiment of the present application, the third pressure sensor PX is arranged inside the fuselage cargo compartment environment pressure simulation box, and the overpressure tube of the third pressure sensor PX is in communication with the fuselage test oil tank.

[0021] The second aspect of the present application provides a method for verifying the performance of a fuselage oil tank ventilation system, based on the fuselage oil tank ventilation system performance verification system as described above, comprising:

[0022] Step 1, system initialization: the test control computer is powered on, the system starts running, and the automatic power-on of the pressure controller, pressure sensor and electric regulating valve is completed;

[0023] Step 2, pressure initial value test self-check: in the initial state, the internal pressure values of the flight environment pressure simulation box and the fuselage cargo compartment environment pressure simulation box are automatically collected, the current value is logically compared with the initial normal value, the pressure initial value test self-check is realized, and after the pressure initial value test self-check is passed, step 3 is entered;

[0024] Step 3, start the vacuum system: the test control computer controls the vacuum pump group to start through remote communication network;

[0025] Step 4, initial steady-state pressure control: according to the initial state of the dynamic pressure change curve, the initial steady-state pressure value is manually input to the test control computer, and the internal pressure of the flight environment pressure simulation box and the fuselage cargo compartment environment pressure simulation box is sucked to the initial target pressure state; if the initial steady-state pressure value converges, the test starts and step 5 is entered; otherwise, the initial steady-state pressure control is continued;

[0026] Step 5, dynamic pressure tracking control: manually confirm the start of the test, the test control computer sends the pressure control time history curve to the pressure controller, the pressure controller adjusts the opening of the electric regulating valve in real time according to the pressure control instruction, and the pressure dynamic stable change is realized by vacuum suction or air supply to the flight environment pressure simulation box and the fuselage cargo compartment environment pressure simulation box; the internal pressure of the fuselage test oil tank, the flight environment pressure simulation box and the fuselage cargo compartment environment pressure simulation box is recorded by the pressure sensor respectively, and the pressure increase value ΔP1 of the fuselage test oil tank relative to the fuselage cargo compartment environment pressure simulation box and the pressure increase value ΔP2 of the fuselage test oil tank relative to the flight environment pressure simulation box are obtained by calculation;

[0027] Step 6, data processing and analysis: export effective data information and automatically generate data charts.

[0028] In at least one embodiment of the present application, in step 2, if it is confirmed that the pressure initial value is correct during the pressure initial value test self-check, the pressure initial value test self-check is passed, and the test control computer enters the pre-test preparation state; otherwise, the pressure controller sends alarm information to the test control computer, and the current test is ended.

[0029] The application has at least the following beneficial technical effects:

[0030] The fuselage oil tank ventilation system performance verification system of the application can simulate the gas pressure change process in the fuselage oil tank during the whole flight process, and ensures that the working performance of the fuselage oil tank ventilation system is accurately verified; the environmental pressure simulation box is controlled by double valves, and the pressure controller can realize rapid and stable control of the gas pressure in the box according to the box pressure sensor. BRIEF DESCRIPTION OF DRAWINGS

[0031] Fig. 1 is a schematic diagram of a fuselage oil tank ventilation system performance verification system according to an embodiment of the application;

[0032] Fig. 2 is a flow chart of a fuselage oil tank ventilation system performance verification method according to an embodiment of the application. DETAILED DESCRIPTION

[0033] To make the purpose, technical scheme and advantages of the application clearer, the technical scheme of the embodiments of the application will be described in more detail below with reference to the drawings of the embodiments of the application. In the drawings, the same or similar reference signs represent the same or similar elements or elements with the same or similar functions throughout. The described embodiments are some of the embodiments of the application, not all. The embodiments described below with reference to the drawings are exemplary and are intended to explain the application, and cannot be understood as a limitation on the application. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the application. The embodiments of the application will be described in detail below with reference to the drawings.

[0034] In the description of the application, it should be understood that the terms "center", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the scope of protection of the application.

[0035] The drawings will be described below in conjunction with the Figs. 1-2 The application will be further described in detail.

[0036] The application provides a fuselage oil tank ventilation system performance verification system, comprising: a fuselage test oil tank, a flight environmental pressure simulation box, a fuselage cargo hold environmental pressure simulation box, a test control computer, a pressure controller and a pressure sensor.

[0037] Specifically, as shown in Fig. 1 The fuselage test oil tank is used for storing test fuel, simulating the internal structural size and structural form of the fuselage oil tank in a real installation state, and providing a mounting mechanical interface of the fuselage oil tank ventilation system; the flight environment pressure simulation tank is a negative pressure container, used for simulating the external environment pressure of the aircraft under high altitude conditions, connected with the vacuum system through a first vacuum pipeline and communicated with the atmospheric environment through a first normal pressure pipeline, and an electric regulating valve M2 is installed on the first vacuum pipeline and an electric regulating valve M1 is installed on the first normal pressure pipeline; the fuselage cargo compartment environment pressure simulation tank is a negative pressure container, used for simulating the internal environment pressure of the fuselage cargo compartment, connected with the vacuum system through a second vacuum pipeline and communicated with the atmospheric environment through a second normal pressure pipeline, and an electric regulating valve M3 is installed on the second vacuum pipeline and an electric regulating valve M4 is installed on the second normal pressure pipeline; the test control computer is used for providing a certain man-machine interactive interface, and the pre-setting of the test parameter change process is manually input; the pressure controller is connected with the test control computer, used for receiving the pressure control instructions issued by the test control computer, and directly sending control instructions to each electric regulating valve to make the electric regulating valve adjust in real time according to the instruction opening degree; the pressure sensor is connected with the pressure controller, used for measuring the internal pressure of the fuselage test oil tank, the internal pressure of the flight environment pressure simulation tank and the internal pressure of the fuselage cargo compartment environment pressure simulation tank.

[0038] In the preferred embodiment of the present application, the fuselage test oil tank adopts a stainless steel metal oil tank to simulate the real fuselage oil tank structure of the aircraft, the vacuum system adopts a high suction capacity vacuum pump set, and the flight environment pressure simulation tank and the fuselage cargo compartment environment pressure simulation tank are simultaneously suctioned, the gaseous phase space in the flight environment pressure simulation tank is directly connected and communicated with the outlet of the safety valve and the outlet of the electric ventilation valve at the top of the fuselage test oil tank through a first communication pipe, and the gaseous phase space in the fuselage cargo compartment environment pressure simulation tank is connected with the anti-vacuum valve pressure sensing interface at the top of the fuselage test oil tank through a second communication pipe. The pressure sensor includes a first pressure sensor P1, a second pressure sensor P2 and a third pressure sensor PX, wherein the first pressure sensor P1 is arranged on the first communication pipe and used for collecting the internal pressure of the flight environment pressure simulation tank, the second pressure sensor P2 is arranged at the top of the fuselage cargo compartment environment pressure simulation tank and used for collecting the internal pressure of the fuselage cargo compartment environment pressure simulation tank, and the third pressure sensor PX is arranged in the fuselage cargo compartment environment pressure simulation tank and used for collecting the internal pressure of the fuselage test oil tank, and the third pressure sensor PX is communicated with the fuselage test oil tank through a pressure measurement pipe.

[0039] The fuselage oil tank ventilation system performance verification system of the application comprises one test control computer, one pressure controller connected with the test control computer, two pressure sensors connected with the pressure controller, one set of flight environment pressure simulation box, one set of fuselage cargo compartment environment pressure simulation box, one set of vacuum system, one set of fuselage test oil tank, and the flight environment pressure simulation box and the fuselage cargo compartment environment pressure simulation box are each provided with two electric regulating valves, one outlet of which is connected with a vacuum pipeline, and the other outlet of which is connected with a laboratory normal pressure environment. The fuselage test oil tank adopts a stainless steel oil tank, the size of the oil tank cavity is consistent with the installation state, can store test fuel, and provides an installation mechanical interface of the fuselage oil tank ventilation system.

[0040] The fuselage oil tank ventilation system performance verification system of the application is manually controlled through a certain man-machine interface provided by the test control computer, the start and stop of the remote vacuum pump group can be controlled, and the pre-set state parameters such as the initial steady-state pressure and the dynamic tracking environment pressure curve can be input. The test control computer receives and displays the pressures P1 and P2 returned by the pressure controller, completes the difference calculation between P1 and the fuselage test oil tank pressure PX, and completes the difference calculation between P2 and the fuselage test oil tank pressure PX. The pressure sensor P1 is used to collect the pressure value of the flight environment pressure simulation box, which is collected by the pressure controller and uploaded and displayed to the test control computer; the pressure sensor P2 is used to collect the pressure value of the fuselage cargo compartment environment pressure simulation box, which is collected by the pressure controller and uploaded and displayed to the test control computer. The fuselage cargo compartment environment pressure simulation box is internally provided with a fuselage oil tank pressure sensor, which is communicated with the fuselage test oil tank through a pressure measuring pipe, and simulates the accurate measurement process of the relative cargo compartment environment pressure increase value PX of the fuselage test oil tank. The pressure controller receives the target pressure control instruction issued by the test control computer, and if the flight environment box pressure P1 is higher than the target value, the opening degree of the electric regulating valve M2 is increased and the opening degree of the electric regulating valve M1 is reduced, otherwise the opposite; if the fuselage cargo compartment environment pressure P2 is higher than the target value, the opening degree of the electric regulating valve M3 is increased and the opening degree of the electric regulating valve M4 is reduced, otherwise the opposite.

[0041] Based on the above fuselage oil tank ventilation system performance verification system, a second aspect of the application provides a fuselage oil tank ventilation system performance verification method, as shown in Fig. 2 The method comprises the following steps:

[0042] Step 1, system initialization: the test control computer is powered on, the system starts to run, and the automatic power-on of the pressure controller, the pressure sensor and the electric regulating valve is completed;

[0043] Step 2, pressure initial value test self-check: initial state, automatically collect the internal pressure values of the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box, compare the current values with the initial normal values, realize pressure initial value test self-check, and enter step 3 after the pressure initial value test self-check is passed; if it is confirmed that the pressure initial value is correct during the pressure initial value test self-check, the pressure initial value test self-check is passed, and the test control computer enters a pre-test preparation state; otherwise, the pressure controller sends alarm information to the test control computer, and the current test is ended;

[0044] Step 3, start the vacuum system: the test control computer controls the vacuum pump group to start through remote communication over a network;

[0045] Step 4, initial steady pressure control: according to the initial state of the dynamic pressure change curve, manually input the steady initial pressure value to the test control computer, and suck the internal pressures of the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box to the initial target pressure state; if the initial steady pressure value converges, the test is started and step 5 is entered; otherwise, continue to wait for the initial steady pressure control;

[0046] Step 5, dynamic pressure tracking control: manually confirm the start of the test, the test control computer sends the pressure control time history curve to the pressure controller, the pressure controller adjusts the opening degree of the electric regulating valve in real time according to the pressure control instruction, and realizes the dynamic stable change of pressure by vacuum suction or air supply to the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box; the internal pressures of the fuselage test tank, the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box are recorded by the pressure sensor respectively, and the pressure increase value ΔP1 of the fuselage test tank relative to the fuselage cargo hold environment pressure simulation box and the pressure increase value ΔP2 of the fuselage test tank relative to the flight environment pressure simulation box are obtained by calculation;

[0047] Step 6, data processing and analysis: export effective data information and automatically generate data charts.

[0048] In an embodiment of the present application, the fuselage oil tank ventilation system performance verification process is as follows:

[0049] Step 1, system initialization: the test control computer is powered on, the application software is opened, and the system automatically powers on the pressure controller, the sensor, the regulating valve and other measurement and control devices.

[0050] Step 2, pressure initial value test self-check: initial state, automatically collect the internal pressure values of the flight environment pressure simulation box and the fuselage cargo environment pressure simulation box, and compare the current value 96kPa with the initial system default normal value 97kPa. When it is confirmed that the error between the pressure initial value and the default normal value is within 1%, the test control command machine enters the preparation state; otherwise, the pressure controller sends alarm information to the test control command machine, and forcibly ends the test.

[0051] Step 3, start the vacuum system: the test control command machine controls the vacuum pump group to start through remote network communication, and performs vacuum suction treatment on the vacuum pipeline. Otherwise, the control system directly ends the test.

[0052] Step 4, initial steady pressure control: manually input the steady initial pressure value to the test control computer, requiring the flight altitude environment pressure to be 23kPa and the fuselage cargo environment pressure to be 70kPa. When the flight altitude environment pressure converges to 23.1kPa and the fuselage cargo environment pressure is 59.5kPa, the test control computer determines that the initial state of the system is stable and convergent, and enters step 5; otherwise, continue to wait for the initial steady pressure control.

[0053] Step 5, dynamic pressure tracking control: manually click the start test button, the test control command machine sends the pressure control time history curve to the pressure controller, the pressure controller adjusts the opening degree of the regulating valve on the pressure simulation box in real time according to the pressure target instruction, and realizes the dynamic stable change of the pressure in the box by vacuum suction or air supplement to the box. During the period, the pressures in the fuselage test tank, the fuselage cargo environment pressure tank and the flight environment pressure tank are recorded by the pressure sensors respectively, and the pressure increase values of the fuselage test tank relative to the fuselage cargo environment pressure and the fuselage test tank relative to the flight environment pressure tank are calculated.

[0054] Table 1

[0055]

[0056] Step 6, data processing and analysis: export effective data information from the test control command machine, and automatically generate data charts.

[0057] The fuselage oil tank ventilation system performance verification system and method can simulate the gas pressure change process in the fuselage oil tank during the whole flight process, and ensure that the working performance of the fuselage oil tank ventilation system is accurately verified. The environmental pressure simulation box adopts double-valve linkage control, and the pressure controller can realize rapid and stable control of the gas pressure in the box according to the box pressure sensor.

[0058] The above merely provides the specific implementation of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of the changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A performance verification system for a fuselage fuel tank ventilation system, characterized in that, include: The fuselage test fuel tank is used to store test fuel, simulates the internal structural dimensions and form of the fuselage fuel tank under actual installed conditions, and provides the mechanical interface for the installation of the fuselage fuel tank ventilation system. The flight environment pressure simulation chamber is a negative pressure container used to simulate the external environmental pressure of an aircraft under high-altitude conditions. The flight environment pressure simulation chamber is connected to the vacuum system through a first vacuum pipeline and connected to the atmospheric environment through a first atmospheric pressure pipeline. An electric regulating valve M2 is installed on the first vacuum pipeline and an electric regulating valve M1 is installed on the first atmospheric pressure pipeline. The fuselage cargo hold environmental pressure simulation chamber is a negative pressure container used to simulate the environmental pressure inside the aircraft fuselage cargo hold. The fuselage cargo hold environmental pressure simulation chamber is connected to the vacuum system through a second vacuum pipeline and connected to the atmospheric environment through a second atmospheric pressure pipeline. An electric regulating valve M3 is installed on the second vacuum pipeline and an electric regulating valve M4 is installed on the second atmospheric pressure pipeline. The test control computer is used to provide a certain human-computer interaction interface, and the test parameters are preset by manual input. The pressure controller is connected to the test control computer and is used to receive pressure control commands issued by the test control computer and directly send control commands to each electric regulating valve, so that the electric regulating valves adjust in real time according to the command opening degree. A pressure sensor, connected to the pressure controller, is used to measure the internal pressure of the fuselage test fuel tank, the internal pressure of the flight environment pressure simulation chamber, and the internal pressure of the fuselage cargo hold environment pressure simulation chamber.

2. The performance verification system for the fuselage fuel tank ventilation system according to claim 1, characterized in that, The test fuel tank is made of stainless steel to simulate the structure of a real aircraft fuselage fuel tank.

3. The performance verification system for the fuselage fuel tank ventilation system according to claim 2, characterized in that, The vacuum system uses a vacuum pump set.

4. The performance verification system for the fuselage fuel tank ventilation system according to claim 3, characterized in that, The gas phase space inside the flight environment pressure simulation chamber is directly connected to the safety valve outlet and the electric vent valve outlet at the top of the fuselage test fuel tank via a first connecting pipe.

5. The performance verification system for the fuselage fuel tank ventilation system according to claim 4, characterized in that, The gas phase space inside the fuselage cargo compartment environmental pressure simulation chamber is connected to the anti-vacuum valve pressure sensing interface on the top of the fuselage test oil tank via a second connecting pipe.

6. The performance verification system for the fuselage fuel tank ventilation system according to claim 5, characterized in that, The pressure sensor includes a first pressure sensor P1, a second pressure sensor P2, and a third pressure sensor PX.

7. The performance verification system for the fuselage fuel tank ventilation system according to claim 6, characterized in that, The first pressure sensor P1 is mounted on the first connecting pipe.

8. The performance verification system for the fuselage fuel tank ventilation system according to claim 7, characterized in that, The second pressure sensor P2 is located on top of the environmental pressure simulation chamber in the fuselage cargo hold.

9. The performance verification system for the fuselage fuel tank ventilation system according to claim 8, characterized in that, The third pressure sensor PX is installed inside the environmental pressure simulation chamber of the fuselage cargo compartment, and the third pressure sensor PX is connected to the fuselage test oil tank through the pressure measuring tube.

10. A method for verifying the performance of a fuselage fuel tank ventilation system, based on the fuselage fuel tank ventilation system performance verification system according to any one of claims 1 to 9, characterized in that, include: Step 1, System Initialization: The test control computer is powered on, the system starts running, and automatically powers on the pressure controller, pressure sensor, and electric regulating valve. Step 2, Initial Pressure Value Test Self-Check: In the initial state, the internal pressure values ​​of the flight environment pressure simulation chamber and the fuselage cargo hold environment pressure simulation chamber are automatically collected. The current value is logically compared with the initial normal value to realize the initial pressure value test self-check. After the initial pressure value test self-check passes, proceed to Step 3. Step 3: Start the vacuum system: The test control computer remotely controls the vacuum pump group to start via network communication; Step 4, Initial Steady-State Pressure Control: Based on the initial state of the dynamic pressure change curve, manually input the initial steady-state pressure value into the test control computer to draw the internal pressure of the flight environment pressure simulation chamber and the fuselage cargo hold environment pressure simulation chamber to the initial target pressure state; if the initial steady-state pressure value converges, the test begins and proceeds to Step 5; otherwise, continue to wait for the initial steady-state pressure control. Step 5, Dynamic Pressure Tracking Control: After manual confirmation of the start of the test, the test control computer sends the pressure control time history curve to the pressure controller. The pressure controller adjusts the opening of the electric regulating valve in real time according to the pressure control command. The pressure is dynamically stabilized by vacuuming or replenishing the flight environment pressure simulation chamber and the fuselage cargo hold environment pressure simulation chamber. The internal pressure of the fuselage test fuel tank, the flight environment pressure simulation chamber, and the fuselage cargo hold environment pressure simulation chamber are recorded by pressure sensors. The pressure increase value ΔP1 in the fuselage test fuel tank relative to the fuselage cargo hold environment pressure simulation chamber and the pressure increase value ΔP2 in the fuselage test fuel tank relative to the flight environment pressure simulation chamber are calculated. Step 6, Data Processing and Analysis: Export valid data information and automatically generate data charts.

11. The method for verifying the performance of the fuselage fuel tank ventilation system according to claim 10, characterized in that, In step 2, during the pressure initial value test self-check, if the pressure initial value is confirmed to be correct, the pressure initial value test self-check passes, and the test control computer enters the test preparation state; otherwise, the pressure controller sends an alarm message to the test control computer and ends the current test.

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