Fuselage oil tank ventilation system performance verification system and method

Abstract

The invention belongs to the technical field of general aviation ground tests, and particularly relates to a fuselage fuel tank ventilation system performance verification system and method. The fuselage test oil tank is used for storing test fuel oil and providing a mounting mechanical interface of a fuselage oil tank ventilation system; the flight environment pressure simulation box is used for simulating the external environment pressure of the airplane under the high-altitude condition; the fuselage warehouse environment pressure simulation box is used for simulating the environment pressure in an aircraft fuselage warehouse; the test control computer is used for providing a certain human-computer interaction interface, and presetting of a test parameter change process is completed through manual input; the pressure controller is connected with the test control computer and is used for receiving a pressure control instruction issued by the test control computer and directly sending a control instruction to each electric control valve, so that the electric control valves are adjusted in real time according to the opening degrees of the instructions; the pressure sensor is connected with the pressure controller and used 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 warehouse environment pressure simulation box.

Description

Technical Field

[0001] The present application belongs to the field of general aviation ground test technology, and in particular, relates to a fuselage fuel tank ventilation system performance verification system and method. Background Art

[0002] The fuel storage space of transport or integrated transport and tanker support aircraft mostly adopts a wing box structure, but large tankers are designed with a higher fuel capacity in mind and install a fuselage fuel tank in the fuselage cargo hold. An independent ventilation system is installed on the upper part of the fuselage fuel tank to prevent the pressure in the fuselage fuel tank from being too high or too low during the aircraft's climb or descent. In existing test technologies, the verification of the fuel tank ventilation system is often carried out through independent verification of the system's discrete components in the finished product factory, ignoring the impact of factors such as the fuselage fuel tank structure and size, installation location, and the amount of fuel in the tank on the working state of the aircraft control system. There is also a lack of comprehensive verification of the cross-linking working performance of the system's discrete components. Therefore, the fuel tank ventilation system after installation is often inconsistent with the design value. How to resolve this inconsistency and how to complete the accurate verification of the fuselage fuel tank ventilation performance through ground testing have become key technical issues.

[0003] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0004] The purpose of the present application is to provide a fuselage fuel tank ventilation system performance verification system and method to solve at least one problem existing in the prior art.

[0005] The technical solution of this application is:

[0006] A first aspect of the present application provides a fuselage fuel tank ventilation system performance verification system, comprising:

[0007] The fuselage test fuel tank is used to store test fuel, simulate the internal structure size and structure form of the fuselage fuel tank under the actual installation state, and provide the installation mechanical interface of the fuselage fuel tank ventilation system;

[0008] The flight environment pressure simulation box is a negative pressure container used to simulate the external environment pressure of the aircraft under high-altitude conditions. The flight environment pressure simulation box is connected to the vacuum system through a first vacuum pipeline and is connected to 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 hold environmental pressure simulation box is a negative pressure container used to simulate the environmental pressure in the fuselage cargo hold of the aircraft. The fuselage cargo hold environmental pressure simulation box is connected to the vacuum system through a second vacuum pipeline and is connected to the atmospheric environment through a second normal 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 normal pressure pipeline.

[0010] The test control computer is used to provide a certain human-computer interaction interface and manually input the pre-setting of the test parameter change process;

[0011] A pressure controller is connected to the test control computer and is used to receive pressure control instructions issued by the test control computer and directly send control instructions to each electric regulating valve so that the electric regulating valve can adjust the opening in real time according to the instruction;

[0012] A pressure sensor is connected to the pressure controller and is used 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 hold environment pressure simulation box.

[0013] In at least one embodiment of the present application, the fuselage test fuel tank uses a stainless steel metal fuel tank to simulate the actual fuselage fuel tank structure of the aircraft.

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

[0015] In at least one embodiment of the present application, the gas phase space in the flight environment pressure simulation box is directly connected to the safety valve outlet and the electric vent valve outlet at the top of the fuselage test oil tank through a first connecting pipe.

[0016] In at least one embodiment of the present application, the gas phase space in the fuselage cargo hold environmental pressure simulation box is connected to the anti-vacuum valve pressure sensing interface on the top of the fuselage test oil tank through a second connecting pipe.

[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 disposed on the first connecting pipe.

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

[0020] In at least one embodiment of the present application, the third pressure sensor PX is disposed inside the fuselage cargo hold environmental pressure simulation box, and the third pressure sensor PX is connected to the fuselage test oil tank through a pressure measuring tube.

[0021] A second aspect of the present application provides a fuselage fuel tank ventilation system performance verification method, based on the fuselage fuel 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 pressure controller, pressure sensor, and electric regulating valve are automatically powered on;

[0023] Step 2, initial pressure value test self-check: In the initial state, automatically collect the internal pressure values ​​of the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box, perform a logical comparison between the current value and the initial normal value, and implement the initial pressure value test self-check. After the initial pressure value test self-check is passed, proceed to step 3;

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

[0025] Step 4, initial steady-state pressure control: according to the initial state of the dynamic pressure change curve, manually input the steady-state initial pressure value into the test control computer, and pump the internal pressure 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-state pressure value converges, start the test and enter step 5; otherwise, continue to wait for the initial steady-state pressure control;

[0026] Step 5, dynamic pressure tracking control: manually confirm to start 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 control valve in real time according to the pressure control command, and realizes the dynamic and stable change of pressure by vacuum suction or air replenishment of the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box; the internal pressures of the fuselage test oil tank, the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box are recorded by pressure sensors respectively, and the pressurization value △P1 of the fuselage test oil tank relative to the fuselage cargo hold environment pressure simulation box and the pressurization value △P2 of the fuselage test oil tank relative to the flight environment pressure simulation box are calculated;

[0027] Step 6: Data processing and analysis: Export valid data information and automatically generate data charts.

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

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

[0030] The fuselage fuel tank ventilation system performance verification system of the present application can realistically simulate the gas pressure change process in the fuselage fuel tank during the entire flight process, ensuring that the working performance of the fuselage fuel tank ventilation system is accurately verified; the environmental pressure simulation box adopts dual-valve linkage control, and the pressure controller can realize rapid and stable control of the gas pressure in the box based on the box pressure sensor. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 is a schematic diagram of a fuselage fuel tank ventilation system performance verification system according to an embodiment of the present application;

[0032] Figure 2 It is a flow chart of a method for verifying the performance of a fuselage fuel tank ventilation system according to one embodiment of the present application. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0034] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0035] The following is combined with Figure 1 to Figure 2 This application is described in further detail.

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

[0037] Specifically, Figure 1 As shown, the fuselage test fuel tank is used to store test fuel, simulates the internal structure size and structure of the fuselage fuel tank under the actual installation state, and provides the installation mechanical interface of the fuselage fuel tank ventilation system; the flight environment pressure simulation box is a negative pressure container, which is used to simulate the external environment pressure of the aircraft under high altitude conditions. The flight environment pressure simulation box is connected to the vacuum system through the first vacuum pipeline, and is connected to the atmospheric environment through the 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; the fuselage cargo hold environment pressure simulation box is a negative pressure container, which is used to simulate the environment pressure inside the aircraft fuselage cargo hold. The fuselage cargo hold environment pressure simulation box is connected to the vacuum system through the second vacuum pipeline. The test control computer is used to provide a certain human-computer interaction interface, and the manual input completes the pre-setting of the test parameter change process; the pressure controller is connected to the test control computer, and is used to receive the pressure control instructions issued by the test control computer, and directly send the control instructions to each electric regulating valve, so that the electric regulating valve can adjust the opening in real time according to the instruction; the pressure sensor is connected to the pressure controller, and is used 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 hold environment pressure simulation box.

[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, and the vacuum system adopts a high suction capacity vacuum pump group to simultaneously suck the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box, and the gas phase space in the flight environment pressure simulation box is directly connected to the safety valve outlet and the electric vent valve outlet at the top of the fuselage test oil tank through a first connecting pipe, and the gas phase space in the fuselage cargo hold environment pressure simulation box is connected to the anti-vacuum valve pressure sensing interface at the top of the fuselage test oil tank through a second connecting 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 connecting pipe, and is used to collect the internal pressure of the flight environment pressure simulation box, the second pressure sensor P2 is arranged on the top of the fuselage cargo hold environment pressure simulation box, and is used to collect the internal pressure of the fuselage cargo hold environment pressure simulation box, and the fuselage cargo hold environment pressure simulation box has a built-in third pressure sensor PX for collecting the internal pressure of the fuselage test oil tank, and the third pressure sensor PX is connected to the fuselage test oil tank through a pressure measuring pipe.

[0039] The fuselage fuel tank ventilation system performance verification system of the present application includes a test control computer, a pressure controller connected to the test control computer, two pressure sensors connected to the pressure controller, a flight environment pressure simulation box, a fuselage cargo compartment environment pressure simulation box, a vacuum system, and a fuselage test fuel tank. The flight environment pressure simulation box and the fuselage cargo compartment environment pressure simulation box are both provided with two electric regulating valves, one of which is connected to the vacuum pipeline at the outlet, and the other is connected to the normal pressure environment of the test room at the outlet. The fuselage test fuel tank adopts a stainless steel tank, and the inner cavity size of the tank is consistent with the installed state, which can store test fuel and provide a mechanical interface for the installation of the fuselage fuel tank ventilation system.

[0040] The fuselage tank ventilation system performance verification system of the present application can control the start and stop of the remote vacuum pump group manually through a certain human-computer interaction interface provided by the test control computer, and can input the state parameters preset by the test, such as the initial steady-state pressure and the dynamic tracking environmental pressure curve. 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 tank pressure PX, and completes the difference calculation between P2 and the fuselage test tank pressure PX. The pressure sensor P1 is used to collect the pressure value of the flight environment pressure simulation box, which is completed by the pressure controller and uploaded to the test control computer for display; the pressure sensor P2 is used to collect the pressure value of the fuselage cargo hold environment pressure simulation box, which is completed by the pressure controller and uploaded to the test control computer for display. A fuselage tank pressure sensor is installed inside the fuselage cargo hold environment pressure simulation box, and the pressure sensor is connected to the fuselage tank through a pressure measuring tube, simulating the accurate measurement process of the fuselage test tank relative to the cargo hold environment pressurization value PX. The pressure controller receives the target pressure control instruction issued by the test control computer. If the pressure P1 of the flight environment box is higher than the target value, the opening of the electric regulating valve M2 is increased and the opening of the electric regulating valve M1 is decreased, otherwise vice versa. If the fuselage cargo hold environment pressure P2 is higher than the target value, the opening of the electric regulating valve M3 is increased and the opening of the electric regulating valve M4 is decreased, otherwise vice versa.

[0041] Based on the above-mentioned fuselage fuel tank ventilation system performance verification system, the second aspect of the present application provides a fuselage fuel tank ventilation system performance verification method, such as Figure 2 As shown, the following steps are included:

[0042] Step 1: System initialization: The test control computer is powered on, the system starts running, and the pressure controller, pressure sensor, and electric regulating valve are automatically powered on;

[0043] Step 2, initial pressure value test self-check: In the initial state, the internal pressure values ​​of the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box are automatically collected, and 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, step 3 is entered; during the initial pressure value test self-check, if it is confirmed that the initial pressure value is correct, the initial pressure value test self-check passes, and the test control computer enters the pre-test preparation state; otherwise, the pressure controller sends an alarm message to the test control computer to end the current test;

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

[0045] Step 4, initial steady-state pressure control: according to the initial state of the dynamic pressure change curve, manually input the steady-state initial pressure value into the test control computer, and pump the internal pressure 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-state pressure value converges, start the test and enter step 5; otherwise, continue to wait for the initial steady-state pressure control;

[0046] Step 5, dynamic pressure tracking control: manually confirm to start 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 control valve in real time according to the pressure control command, and realizes the dynamic and stable change of pressure by vacuum suction or air replenishment of the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box; the internal pressures of the fuselage test oil tank, the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box are recorded by pressure sensors respectively, and the pressurization value △P1 of the fuselage test oil tank relative to the fuselage cargo hold environment pressure simulation box and the pressurization value △P2 of the fuselage test oil tank relative to the flight environment pressure simulation box are calculated;

[0047] Step 6: Data processing and analysis: Export valid data information and automatically generate data charts.

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

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

[0050] Step 2, initial pressure test self-check: In the initial state, automatically collect the internal pressure values ​​of the flight environment pressure simulation box and the fuselage cargo compartment environment pressure simulation box, and perform a logical comparison between the current value 96kPa and the initial system default normal value 97kPa. When it is confirmed that the error between the initial pressure value and the default normal value is within 1%, the test control and command machine enters the ready state; otherwise, the pressure controller sends an alarm message to the test control and command machine, forcing the test to end actively.

[0051] Step 3, start the vacuum system: the test control and command machine controls the vacuum pump group to start through network remote communication, and vacuum the vacuum pipeline. Otherwise, the control system will give an alarm and end the test directly.

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

[0053] Step 5, dynamic pressure tracking control: manually click the operation button to start the test, the test control command machine sends the pressure control time history curve to the pressure controller, the pressure controller adjusts the opening of the regulating valve on the pressure simulation box in real time according to the pressure target instruction, and realizes the dynamic and stable change of the pressure in the box by vacuum suction or air replenishment. During this period, the pressure in the fuselage test tank, the fuselage cargo hold environmental pressure box and the flight environment pressure box are recorded by the pressure sensor respectively, and the pressure increase value △P1 in the fuselage test tank relative to the fuselage cargo hold environmental pressure and the pressure increase value △P2 in the fuselage test tank relative to the flight environment pressure box are calculated.

[0054] Table 1

[0055]

[0056] Step 6: Data processing and analysis: Export valid data information from the test control command machine and automatically generate data charts.

[0057] The fuselage tank ventilation system performance verification system and method of the present application can truly simulate the change process of the gas pressure in the fuselage tank during the entire flight process, ensuring that the working performance of the fuselage 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 based on the box pressure sensor.

[0058] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A fuselage fuel tank ventilation system performance verification system, characterized in that: include: The fuselage test fuel tank is used to store test fuel, simulate the internal structure size and structure form of the fuselage fuel tank under the actual installation state, and provide the installation mechanical interface of the fuselage fuel tank ventilation system; The flight environment pressure simulation box is a negative pressure container used to simulate the external environment pressure of the aircraft under high-altitude conditions. The flight environment pressure simulation box is connected to the vacuum system through a first vacuum pipeline and is connected to 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. The fuselage cargo hold environmental pressure simulation box is a negative pressure container used to simulate the environmental pressure in the fuselage cargo hold of the aircraft. The fuselage cargo hold environmental pressure simulation box is connected to the vacuum system through a second vacuum pipeline and is connected to the atmospheric environment through a second normal 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 normal pressure pipeline. The test control computer is used to provide a certain human-computer interaction interface and manually input the pre-setting of the test parameter change process; A pressure controller is connected to the test control computer and is used to receive pressure control instructions issued by the test control computer and directly send control instructions to each electric regulating valve so that the electric regulating valve can adjust the opening in real time according to the instruction; A pressure sensor is connected to the pressure controller and is used 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 hold environment pressure simulation box.

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

3. The fuselage tank ventilation system performance verification system according to claim 2, characterized in that: The vacuum system adopts a vacuum pump set.

4. The fuselage tank ventilation system performance verification system according to claim 3, characterized in that: The gas phase space in the flight environment pressure simulation box is directly connected to the safety valve outlet and the electric vent valve outlet on the top of the fuselage test oil tank through a first connecting pipe.

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

6. The fuselage tank ventilation system performance verification system according to claim 5, characterized in that: The pressure sensors include a first pressure sensor P1 , a second pressure sensor P2 , and a third pressure sensor PX.

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

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

9. The fuselage tank ventilation system performance verification system according to claim 8, characterized in that: The third pressure sensor PX is disposed inside the fuselage cargo hold environmental pressure simulation box, and the third pressure sensor PX is connected to the fuselage test oil tank through a 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 the pressure controller, pressure sensor, and electric regulating valve are automatically powered on; Step 2, initial pressure value test self-check: In the initial state, automatically collect the internal pressure values ​​of the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box, perform a logical comparison between the current value and the initial normal value, and implement the initial pressure value test self-check. After the initial pressure value test self-check is passed, proceed to step 3; Step 3, start the vacuum system: the test control computer controls the vacuum pump group to start through network remote communication; Step 4, initial steady-state pressure control: according to the initial state of the dynamic pressure change curve, manually input the steady-state initial pressure value into the test control computer, and pump the internal pressure 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-state pressure value converges, start the test and enter step 5; otherwise, continue to wait for the initial steady-state pressure control; Step 5, dynamic pressure tracking control: manually confirm to start 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 control valve in real time according to the pressure control command, and realizes the dynamic and stable change of pressure by vacuum suction or air replenishment of the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box; the internal pressures of the fuselage test oil tank, the flight environment pressure simulation box and the fuselage cargo hold environment pressure simulation box are recorded by pressure sensors respectively, and the pressurization value △P1 of the fuselage test oil tank relative to the fuselage cargo hold environment pressure simulation box and the pressurization value △P2 of the fuselage test oil tank relative to the flight environment pressure simulation box are calculated; Step 6: Data processing and analysis: Export valid data information and automatically generate data charts.

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

Images