Aircraft fuel tank pressure refueling oil spill test system and method
By using a high-precision weighing measurement system and distributed pressure monitoring, the problem of accurately measuring the oil spill rate during aircraft fuel tank refueling was solved, enabling accurate measurement of the oil spill rate and real-time monitoring of fuel tank pressure changes, thus improving the level of automation.
Patent Information
- Application Number
- CN202511966359.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-24
- Publication Date
- 2026-02-27
AI Technical Summary
In existing technologies, it is difficult to accurately measure the spill rate during aircraft fuel tank pressure refueling, resulting in large pressure fluctuations and an inability to promptly determine the peak pressure of the fuel tank.
A high-precision weighing measurement system and distributed pressure monitoring are adopted to dynamically calculate the oil spill rate in real time. Data is collected through signal acquisition devices and pressure sensors, and then automatically calculated and stored in conjunction with the test controller.
It enables accurate measurement of the fuel overflow rate from aircraft fuel tanks, improves the level of automation, truly reflects changes in fuel tank pressure, and ensures the safety of aircraft fuel tanks.
Smart Images
Figure CN121573208A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the technical field of aircraft fuel systems, and specifically relates to an aircraft fuel tank pressure refueling overflow test system and method. Background Technology
[0002] Pressure refueling of aircraft fuel tanks is a crucial technique for rapid refueling. However, once an aircraft fuel tank is full, the pressure inside rises rapidly. To ensure the safety of the aircraft fuel tank, it is necessary to measure the pressure changes and the flow rate of spilled fuel during pressure refueling tests. Current technology uses on-site observation of the pressure gauge during the spill process to determine the maximum tank pressure. However, this method results in significant pressure fluctuations, making it difficult to accurately and promptly determine the peak tank pressure and to accurately measure the spill rate.
[0003] Therefore, accurately measuring the oil spill rate is a problem that needs to be solved. Summary of the Invention
[0004] To address the aforementioned issues, this application provides an aircraft fuel tank pressure refueling overflow test system and method to solve the problem of inaccurate measurement of overflow rate in the prior art.
[0005] The technical solution of this application is: a method for testing fuel tank pressure refueling overflow in aircraft, comprising:
[0006] Measurement system power-on initialization;
[0007] Refuel the aircraft fuel tanks until the pressure at the aircraft refueling connector reaches the set value;
[0008] The system collects pressure and mass data of the aircraft fuel tank at different times, calculates the oil spill rate in the aircraft fuel tank, and stores the calculation results for different times, different oil spill rates, and pressure data.
[0009] Set the time target value t final Determine whether the end time of the experiment is not greater than the target time value t. final If yes, then repeat the collection, calculation, and storage of pressure and mass data; if not, stop refueling the aircraft fuel tank and end the test.
[0010] Preferably, the specific method for powering up and initializing the measurement system is as follows: after the system is powered on, the data acquisition unit performs an initial weighing of the oil spill storage container and automatically sets the current weight to zero; the pressure sensor performs an initial self-test to confirm that the pressure sensor is at a normal value.
[0011] Preferably, when refueling the aircraft fuel tank, refueling is carried out through a ground pressure refueling system. The pressure at the aircraft refueling connector is controlled in a closed loop by a test controller. If the pressure at the aircraft refueling connector does not reach the set value, the test controller continuously increases the pressure until the set value is reached.
[0012] Preferably, when collecting pressure and mass data of the aircraft fuel tank at different times, the mass M of fuel in the overflow tank at time t is recorded. t and pressure data P from each pressure measuring point t At the next time t+Δt, record the current fuel mass M in the overflow tank. t+△t and pressure data P from each pressure measuring point t+△t .
[0013] Preferably, when calculating the fuel spill rate in the aircraft fuel tank, the average rate of change V of the fuel mass in the tank over a time interval Δt is calculated. t =(M t+△t -M t ) / Δt, and use this value as the fuel overflow rate at time t and store it in the test controller.
[0014] Preferably, the calculation results for different times, different oil spill rates, and pressure data are stored in columns.
[0015] As another specific implementation, an aircraft fuel tank pressure refueling overflow test system includes a fuel source vehicle simulation device, a pressure refueling component, a test fuel tank, a test controller, and data acquisition elements;
[0016] One end of the fuel source vehicle simulation device is connected to the test controller, and the other end is connected to the pressure refueling component; the fuel source vehicle simulation device is used to provide test aviation fuel at a certain pressure.
[0017] The test oil tank is connected to the pressure filling assembly, and the data acquisition element is located on the test oil tank for data acquisition; the data acquisition element is electrically connected to the test controller.
[0018] Preferably, the acquisition element includes a signal acquisition unit, a pressure sensor, and a weighing sensor; the pressure sensor can acquire the pressure inside the test oil tank, and the signal acquisition unit performs signal conditioning on the electrical signals output by the weighing sensor and the pressure sensor; the weighing sensor is used to measure the total mass of the oil spill recovery container.
[0019] Preferably, the weighing sensors are evenly distributed and installed at the bottom of the oil spill recovery container, and the signal acquisition device can send the conditioned signal to the test controller via a digital bus.
[0020] Preferably, it also includes an overflow recovery container, which is connected to the test fuel tank and is capable of storing a certain amount of test recovered fuel.
[0021] Preferably, it also includes a pressure refueling pipeline simulator, which connects the fuel source vehicle simulator and the test aircraft fuel tank. The dimensions and routing of the pipeline connecting the fuel source vehicle simulator and the test aircraft fuel tank are consistent with the installed state.
[0022] Preferably, the oil source vehicle simulation device comprises an oil tank, a booster pump, a pressure regulating valve, a flow meter, and a pressure regulating controller; the booster pump, pressure regulating valve, and flow meter are connected to the test oil tank via fuel pipelines; the pressure regulating controller is connected to the booster pump, pressure regulating valve, and flow meter and can control the booster pump and pressure regulating valve; and the oil tank is connected to the pressure regulating valve.
[0023] The aircraft fuel tank pressure refueling overflow test system and method of this application have the following advantages:
[0024] By employing a high-precision weighing and measurement system to dynamically calculate the oil spill rate in real time, and simultaneously distributively monitoring the pressure at each measurement point on the fuel tank, this method has significant advantages in terms of accuracy and automation, and truly reflects the changes in the aircraft's fuel tank spill capacity and pressure. Attached Figure Description
[0025] Figure 1 This is a schematic diagram of the overall structure of this application;
[0026] Figure 2 This is a schematic diagram of the overall process of this application.
[0027] 1. Oil reservoir; 2. Pressure regulator; 3. Pressure filling assembly; 4. Test oil tank; 5. Test controller; 6. Signal acquisition unit; 7. Pressure sensor; 8. Weighing sensor. Detailed Implementation
[0028] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.
[0029] The first aspect of this application provides an aircraft fuel tank pressure refueling overflow test system, such as... Figure 1 It includes an oil source vehicle simulation device, a pressure refueling component 3, a test oil tank 4, a test controller 5, and data acquisition elements.
[0030] One end of the fuel source vehicle simulation device is connected to the test controller 5, and the other end is connected to the pressure refueling component 3; the fuel source vehicle simulation device is used to provide aviation fuel for testing at a certain pressure.
[0031] The test oil tank 4 is connected to the pressure filling assembly 3, and the data acquisition element is located on the test oil tank 4 for data acquisition; the data acquisition element is electrically connected to the test controller 5.
[0032] The data acquisition components include a signal acquisition unit 6, a pressure sensor 7, and a weighing sensor 8. The pressure sensor 7 can acquire the pressure inside the test oil tank 4, and the signal acquisition unit 6 performs signal conditioning on the electrical signals output by the weighing sensor 8 and the pressure sensor 7. The weighing sensor 8 is used to measure the total mass of the oil spill recovery container, and a glass sight glass is provided for easy observation.
[0033] Weighing sensors 8 are evenly distributed and installed at the bottom of the oil spill recovery container, and signal acquisition device 6 can send the conditioned signal to test controller 5 via digital bus.
[0034] It also includes an overflow recovery container and a pressure refueling pipeline simulator. The overflow recovery container is an open container connected to the test fuel tank 4, and can store a certain amount of test recovered fuel. The pressure refueling pipeline simulator connects the fuel source vehicle simulator and the test aircraft fuel tank. The dimensions and routing of the pipeline connecting the fuel source vehicle simulator and the test aircraft fuel tank are consistent with the installed state.
[0035] The fuel supply vehicle simulation device consists of a fuel tank 1, a booster pump, a pressure regulating valve, a flow meter, and a pressure regulating controller 2. The booster pump, pressure regulating valve, and flow meter are connected to the test fuel tank 4 via fuel pipelines. The pressure regulating controller 2 is connected to the booster pump, pressure regulating valve, and flow meter and can control the booster pump and pressure regulating valve. The fuel tank 1 is connected to the pressure regulating valve. The pressure regulating controller 2 uses a pressure sensor 7 as feedback and continuously controls the opening of the regulating valve installed in the fuel pipeline to change the fuel pressure and flow rate at the inlet of the pressure refueling connector assembly.
[0036] As another specific implementation method, a method for testing fuel overflow during aircraft fuel tank pressure refueling is provided, such as... Figure 2 ,include:
[0037] Step 1: Power on and initialize the measurement system.
[0038] The specific method for powering up and initializing the measurement system is as follows: After the system is powered on, the data acquisition unit performs an initial weighing of the oil spill storage container and automatically sets the current weight to zero; the pressure sensor performs an initial self-test to confirm that the pressure sensor is at a normal value.
[0039] Step 2: Refuel the aircraft fuel tank until the pressure at the refueling connector reaches the set value.
[0040] When refueling the aircraft's fuel tank, fuel is added to the tank through a ground-based pressure refueling system. The pressure at the aircraft refueling connector is controlled in a closed loop by a test controller. If the pressure at the refueling connector does not reach the set value, the test controller continuously increases the pressure until the set value is reached.
[0041] Step 3: Collect pressure and mass data of the aircraft fuel tank at different times.
[0042] When collecting pressure and mass data of the aircraft fuel tank at different times, record the mass M of fuel in the overflow tank at time t. t and pressure data P from each pressure measuring point t At the next time t+Δt, record the current fuel mass M in the overflow tank. t+△t and pressure data P from each pressure measuring point t+△t .
[0043] Step 4: Calculate the rate of fuel spillage in the aircraft's fuel tank.
[0044] When calculating the rate of fuel spillage in an aircraft fuel tank, the average rate of change V of the fuel mass in the tank over a time interval Δt is determined. t =(M t+△t -M t ) / Δt, and use this value as the fuel overflow rate at time t and store it in the test controller.
[0045] Step 5, analyze the calculation results for different times t and different oil spill rates V. t and pressure P t+△t Data is stored in columns for easy retrieval.
[0046] The details are shown in Table 1:
[0047] Table 1 Data Records
[0048] Serial Number t(s) <![CDATA[V t (kg / min)]]> <![CDATA[P t+△t (kPa)]]> 1 0 0 96 2 0.1 0 96 3 0.2 200 100 4 0.3 316 112 5 0.4 456 120 6 0.5 256 106 7 0.6 120 97
[0049] Step 6, set the target time value t final Determine whether the end time of the experiment is not greater than the target time value t. final If yes, then repeat the collection, calculation, and storage of pressure and mass data; if not, stop refueling the aircraft fuel tank and end the test.
[0050] In summary, this application has the following advantages:
[0051] By employing a high-precision weighing and measurement system to dynamically calculate the oil spill rate in real time, and simultaneously distributively monitoring the pressure at each measurement point on the fuel tank, this method has significant advantages in terms of accuracy and automation, and truly reflects the changes in the aircraft's fuel tank spill capacity and pressure.
[0052] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A method for testing fuel overflow during pressure refueling of an aircraft fuel tank, characterized in that, include: Measurement system power-on initialization; Refuel the aircraft fuel tanks until the pressure at the aircraft refueling connector reaches the set value; The system collects pressure and mass data of the aircraft fuel tank at different times, calculates the oil spill rate in the aircraft fuel tank, and stores the calculation results for different times, different oil spill rates, and pressure data. Set the time target value t final Determine whether the end time of the experiment is not greater than the target time value t. final If yes, then repeat the collection, calculation, and storage of pressure and mass data; if not, stop refueling the aircraft fuel tank and end the test.
2. The aircraft fuel tank pressure refueling overflow test method as described in claim 1, characterized in that, The specific method for powering up and initializing the measurement system is as follows: After the system is powered on, the data acquisition unit performs an initial weighing of the oil spill storage container and automatically sets the current weight to zero; the pressure sensor performs an initial self-test to confirm that the pressure sensor is at a normal value.
3. The aircraft fuel tank pressure refueling overflow test method as described in claim 1, characterized in that, When refueling the aircraft's fuel tank, fuel is added to the tank through a ground-based pressure refueling system. The pressure at the aircraft refueling connector is controlled in a closed loop by a test controller. If the pressure at the refueling connector does not reach the set value, the test controller continuously increases the pressure until the set value is reached.
4. The aircraft fuel tank pressure refueling overflow test method as described in claim 1, characterized in that, When collecting pressure and mass data of the aircraft fuel tank at different times, record the mass M of fuel in the overflow tank at time t. t and pressure data P from each pressure measuring point t At the next time t+Δt, record the current fuel mass M in the overflow tank. t+△t and pressure data P from each pressure measuring point t+△t .
5. The aircraft fuel tank pressure refueling overflow test method as described in claim 4, characterized in that, When calculating the rate of fuel spillage in an aircraft fuel tank, the average rate of change V of the fuel mass in the tank over a time interval Δt is determined. t =(M t+△t -M t ) / Δt, and use this value as the fuel overflow rate at time t and store it in the test controller.
6. The aircraft fuel tank pressure refueling overflow test method as described in claim 5, characterized in that, The calculation results are stored in columns for different times, different oil spill rates and pressure data.
7. An aircraft fuel tank pressure refueling overflow test system, employing the method described in any one of claims 1-6, characterized in that, It includes an oil source vehicle simulation device, a pressure refueling assembly (3), a test oil tank (4), a test controller (5), and data acquisition elements; One end of the fuel source vehicle simulation device is connected to the test controller (5), and the other end is connected to the pressure refueling component (3); the fuel source vehicle simulation device is used to provide test aviation fuel at a certain pressure; The test oil tank (4) is connected to the pressure filling assembly (3), and the data acquisition element is located on the test oil tank (4) for data acquisition; the data acquisition element is electrically connected to the test controller (5).
8. The aircraft fuel tank pressure refueling overflow test system as described in claim 7, characterized in that, The acquisition elements include a signal acquisition unit (6), a pressure sensor (7), and a weighing sensor (8); the pressure sensor (7) can acquire the pressure inside the test oil tank (4), and the signal acquisition unit (6) performs signal conditioning on the electrical signals output by the weighing sensor (8) and the pressure sensor (7); the weighing sensor (8) is used to measure the total mass of the oil spill recovery container.
9. The aircraft fuel tank pressure refueling overflow test system as described in claim 8, characterized in that, The weighing sensors (8) are evenly distributed and installed at the bottom of the oil spill recovery container, and the signal acquisition device (6) can send the conditioned signal to the test controller (5) via a digital bus.
10. The aircraft fuel tank pressure refueling overflow test system as described in claim 7, characterized in that, It also includes an overflow recovery container, which is connected to the test fuel tank (4) and is capable of storing a certain amount of test recovered fuel.
11. The aircraft fuel tank pressure refueling overflow test system as described in claim 7, characterized in that, It also includes a pressure refueling pipeline simulator, which connects the fuel source vehicle simulator and the test aircraft fuel tank. The dimensions and routing of the pipeline connecting the fuel source vehicle simulator and the test aircraft fuel tank are consistent with the installed state.
12. The aircraft fuel tank pressure refueling overflow test system as described in claim 7, characterized in that, The oil source vehicle simulation device consists of an oil tank (1), a booster pump, a pressure regulating valve, a flow meter, and a pressure regulating controller (2); the booster pump, pressure regulating valve, and flow meter are connected to the test oil tank (4) through fuel pipelines; the pressure regulating controller (2) is connected to the booster pump, pressure regulating valve, and flow meter and can control the booster pump and pressure regulating valve; the oil tank (1) is connected to the pressure regulating valve.