Method, device and equipment for determining leakage rate of local leakage point of aircraft fuel tank and medium

Abstract

The invention discloses a method, device and equipment for determining the leakage rate of local leakage points of an aircraft fuel tank and a medium. The method comprises the steps that in response to a leakage test request of a reference aircraft fuel tank, reference test parameters of the reference aircraft fuel tank are obtained, and the pressure value of the reference aircraft fuel tank at the maximum pressure bearing position is determined as reference pressure according to the reference test parameters; determining the time when the detection solvent passes through a plurality of standard leak holes with different leakage rates for the first time under the reference pressure as candidate time; according to the first time range, one of the multiple candidate times is determined as reference time, and the leakage rate of the standard leak hole corresponding to the reference time is determined as the reference critical leakage rate of the reference aircraft fuel tank; wherein the critical leakage rate is used for representing the leakage rate of the most serious local leakage point on the aircraft fuel tank. According to the scheme, the critical leakage rate of the local leakage point of the aircraft fuel tank can be quickly and effectively evaluated, and the accuracy of aircraft fuel tank leakage testing is improved.

Description

Technical Field

[0001] This invention relates to the field of product testing technology, and in particular to a method, apparatus, equipment and medium for determining the leakage rate of local leaks in an aircraft fuel tank. Background Technology

[0002] During the final assembly and manufacturing stage of an aircraft, leakage tests must be conducted on the aircraft fuel tanks to ensure their sealing performance, taking into account factors such as product functionality and aircraft safety.

[0003] Aircraft fuel tank leak testing generally consists of two phases. The first phase uses compressed air or inert gases such as helium, employing differential pressure testing or other equivalent methods to evaluate the overall fuel tank leakage rate. The second phase uses a liquid solvent (usually aviation fuel permitted for aircraft refueling) as the test medium, employing a combination of penetrant testing and direct visual inspection or spraying a tracer (usually a foaming agent) to locate localized leaks.

[0004] However, the penetration testing method can only determine the location of local leaks, not the leakage rate of those local leaks. If the overall leakage rate of the fuel tank is used to assess whether the aircraft fuel tank meets the product testing requirements, there may be cases where the overall leakage rate meets the requirements but the local leakage rate does not, resulting in inaccurate product testing results. Summary of the Invention

[0005] This invention provides a method, apparatus, equipment, and medium for determining the leakage rate of local leaks in aircraft fuel tanks. It can quickly and effectively assess the critical leakage rate of local leaks in aircraft fuel tanks, and helps to improve the accuracy of aircraft fuel tank leakage test results.

[0006] According to one aspect of the present invention, a method for determining the leakage rate of local leak points in an aircraft fuel tank is provided, the method comprising:

[0007] In response to a leak test request for a reference aircraft fuel tank, reference test parameters for the reference aircraft fuel tank are obtained, and the pressure value of the reference aircraft fuel tank at the maximum pressure point is determined as the reference pressure based on the reference test parameters; wherein, the test parameters include test time, detection solvent density, gravitational acceleration, and maximum liquid level height;

[0008] The time when the detection solvent first drips through multiple standard leaks with different leakage rates at the reference pressure is determined as the candidate time.

[0009] Based on a first time range, one of the candidate times is determined as a reference time, and the leakage rate of the standard leak corresponding to the reference time is determined as the reference critical leakage rate of the reference aircraft fuel tank; wherein, the first time range is determined based on the test time of the reference aircraft fuel tank, and the critical leakage rate is used to characterize the leakage rate of the most serious local leak point on the aircraft fuel tank.

[0010] According to another aspect of the present invention, an apparatus for determining the leakage rate of a local leak point in an aircraft fuel tank is provided, the apparatus comprising:

[0011] The reference pressure determination module is used to respond to a leak test request of a reference aircraft fuel tank, acquire reference test parameters of the reference aircraft fuel tank, and determine the pressure value of the reference aircraft fuel tank at the maximum pressure bearing point as the reference pressure based on the reference test parameters; wherein, the test parameters include test time, detection solvent density, gravitational acceleration, and maximum liquid level height;

[0012] The candidate time determination module is used to determine the time when the detection solvent first drips through multiple standard leaks with different leakage rates under the reference pressure as the candidate time.

[0013] The reference leakage rate determination module is used to determine one of the candidate times from a plurality of time ranges as a reference time based on a first time range, and to determine the leakage rate of the standard leak corresponding to the reference time as the reference critical leakage rate of the reference aircraft fuel tank; wherein, the first time range is determined based on the test time of the reference aircraft fuel tank, and the critical leakage rate is used to characterize the leakage rate of the most serious local leak point on the aircraft fuel tank.

[0014] According to another aspect of the present invention, an electronic device is provided, the electronic device comprising:

[0015] At least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores a computer program executable by the at least one processor, the computer program being executed by the at least one processor to enable the at least one processor to perform the method for determining the leakage rate of local leaks in an aircraft fuel tank according to any embodiment of the present invention.

[0016] According to another aspect of the present invention, a computer-readable storage medium is provided, the computer-readable storage medium storing computer instructions for causing a processor to execute and implement the method for determining the leakage rate of local leak points in an aircraft fuel tank according to any embodiment of the present invention.

[0017] The technical solution of this invention, in response to a leak test request for a reference aircraft fuel tank, firstly obtains reference test parameters for the reference aircraft fuel tank, and determines the pressure value at the maximum pressure point of the reference aircraft fuel tank as the reference pressure based on the reference test parameters. The test parameters include test time, solvent density, gravitational acceleration, and maximum liquid level height. Then, the time when the solvent first drips through multiple standard leak holes with different leakage rates under the reference pressure is determined as a candidate time. Subsequently, a reference time is selected from the multiple candidate times based on a first time range, and the leakage rate of the standard leak hole corresponding to the reference time is determined as the reference critical leakage rate of the reference aircraft fuel tank. The first time range is determined based on the test time of the reference aircraft fuel tank, and the critical leakage rate is used to characterize the leakage rate of the most severely leaking local leak point on the aircraft fuel tank. This technical solution can quickly and effectively assess the critical leakage rate of local leak points in aircraft fuel tanks based on the permeation method, achieving a semi-quantitative assessment of the leakage rate of local leak points in aircraft fuel tanks, which helps improve the accuracy of aircraft fuel tank leak test results.

[0018] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of the present invention, nor is it intended to limit the scope of the invention. Other features of the invention will become readily apparent from the following description. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a flowchart of a method for determining the leakage rate of a local leak point in an aircraft fuel tank according to an embodiment of the present invention;

[0021] Figure 2 This is a schematic diagram of a leakage rate testing system for local leak points in an aircraft fuel tank according to an embodiment of the present invention;

[0022] Figure 3 This is a flowchart of another method for determining the leakage rate of a local leak point in an aircraft fuel tank according to an embodiment of the present invention;

[0023] Figure 4 This is a flowchart illustrating a method for determining the leakage rate of a local leak point in an aircraft fuel tank according to an embodiment of the present invention.

[0024] Figure 5This is a schematic diagram of a device for determining the leakage rate of a local leak point in an aircraft fuel tank according to an embodiment of the present invention;

[0025] Figure 6 This is a schematic diagram of the structure of an electronic device that implements a method for determining the leakage rate of a local leak point in an aircraft fuel tank according to an embodiment of the present invention.

[0026] Figure label:

[0027] 1. Sealed container; 2. Standard leak hole; 5. Air source; 11. Inflation port; 12. Scale; 14. Pressure sensor adapter; 15. Liquid filling / maintenance port; 17. Support base; 18. Standard leak hole adapter; 21. Transparent baffle; 31. Pressure reducing valve; 32. Inflation pipeline; 41. Pressure gauge; 42. Camera; 43. Level. Detailed Implementation

[0028] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0029] It should be noted that the terms "first," "second," "target," etc., used in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0030] Example 1

[0031] Figure 1This is a flowchart illustrating a method for determining the leakage rate of a localized leak point in an aircraft fuel tank, as provided in Embodiment 1 of the present invention. This embodiment is applicable to situations requiring rapid and effective assessment of the leakage rate of a localized leak point in an aircraft fuel tank. This method can be executed by an aircraft fuel tank localized leak point leakage rate determination device, which can be implemented in hardware and / or software and can be configured in an electronic device with data processing capabilities. Figure 1 As shown, the method includes:

[0032] S110, in response to a leak test request for a reference aircraft fuel tank, obtains reference test parameters for the reference aircraft fuel tank, and determines the pressure value of the reference aircraft fuel tank at the maximum pressure point as the reference pressure based on the reference test parameters.

[0033] The reference aircraft fuel tank can refer to an aircraft fuel tank awaiting leak testing. A leak test request is an operational command requesting an aircraft fuel tank leak test, which can be triggered through an interactive interface. Reference test parameters refer to the test parameters corresponding to the reference aircraft fuel tank, specifically including test time (generally limited by the aircraft fuel tank design specifications), test solvent density, gravitational acceleration, and maximum liquid level. The test solvent is a liquid solvent and can be aviation fuel permitted for aircraft refueling. Reference pressure refers to the pressure of the reference aircraft fuel tank at its maximum pressure point.

[0034] In this embodiment, when a leak test request for the reference aircraft's fuel tank is detected, the leak test request is first parsed to obtain the reference test parameters for the reference aircraft's fuel tank, including the test time. Detecting solvent density Gravitational acceleration and maximum liquid level height Then, based on the reference test parameters, the pressure value of the reference aircraft fuel tank at the maximum pressure point is determined as the reference pressure. Optionally, the pressure value of a reference aircraft fuel tank at its maximum pressure point can be determined based on reference test parameters, including: determining the reference pressure based on the product of the tested solvent density, gravitational acceleration, and maximum liquid level height of the reference aircraft fuel tank. Specifically, the reference pressure can be calculated using the following formula: .

[0035] S120, determine the time when the detection solvent first drips through multiple standard leaks with different leakage rates under the reference pressure as the candidate time.

[0036] In this embodiment, a pre-built aircraft fuel tank partial leak rate testing system can be used to determine the candidate time. The candidate time refers to the time when the solvent first drips through multiple standard leaks with different leakage rates at a reference pressure; each standard leak corresponds to one candidate time. Furthermore, the pressure can be established by either creating a liquid column pressure at a specified height or by filling a sealed container with clean air to create a gas pressure equivalent to the liquid column pressure at the specified height.

[0037] See Figure 2 The test system mainly includes a gas source 5, a sealed container 1, a standard leak 2, a pressure regulating unit, and a monitoring and recording unit. The gas source 5 provides the necessary flow of air to the sealed container 1, and can be an air compressor or supplied by a fixed facility. A gas filter can be installed between the gas source and the pressure regulating unit. The sealed container 1 is equipped with an inflation port 11, a standard leak adapter 18, a pressure sensor adapter 14, a liquid filling / maintenance port 15, and a drain port, each with a corresponding protective (sealing) cap. Preferably, a shut-off valve can be installed at each port of the sealed container to control the opening and closing of the ports, improving operational convenience. The sealed container 1 is equipped with a support base 17, and the base legs are adjustable. The sealed container 1 can be integrated with or separately equipped with a level 43 and a scale 12. The base legs are adjusted to keep the container level according to the display of the level 43. The liquid level of the test solvent added to the sealed container 1 is obtained according to the indication of the scale 12. The standard leak 2 is an open, passive leak, with a capillary tube as the core, which can be replaced by a glass wire. The standard leak 2 is connected to the standard leak adapter 18 of the sealed container 1. A transparent baffle 21 is provided around the standard leak 2 to reduce airflow disturbance to the droplets formed at the outlet of the standard leak core. The pressure regulating unit is equipped with a pressure reducing valve 31, whose input end is connected to the gas source 5 via an inflation line 32, and whose output end is connected to the inflation port 11 of the sealed container 1. Preferably, the pressure regulating unit is a digitally displayed pressure reducing valve that can automatically correct the output pressure value to maintain a constant value. The monitoring and recording unit includes a pressure gauge 41 and a camera device 42 (such as a webcam) with data storage function. The pressure gauge 41 is connected to the pressure sensor adapter 14 of the sealed container 1 to monitor the gas pressure in the sealed container 1. The camera device 42 with data storage function is used to continuously monitor and record the pressure indication value on the pressure gauge 41 and the image of droplet formation and dripping at the outlet of the standard leak core.

[0038] Specifically, the experimental procedure is as follows: (1) Install standard leak hole 2 on standard leak hole adapter 18 of sealed container 1, and install pressure gauge 41 on pressure sensor adapter 14. It should be noted that in order to improve experimental efficiency, multiple standard leak holes with different leakage rates can be installed at the same time. (2) Open the liquid filling / maintenance port 15 of sealed container 1, add aircraft fuel tank leak detection solvent to sealed container 1, and close liquid filling / maintenance port 15. (3) Read the scale 12 of sealed container 1 to obtain the height of the solvent liquid level in sealed container 1, and calculate the inflation pressure. Among them, the inflation pressure is the reference pressure. (4) Connect the gas inlet end of the pressure reducing valve 31 to the gas source 5 through the gas filling pipe 32, and connect the gas outlet end of the pressure reducing valve 31 to the gas filling port 11 of the closed container 1 through the gas filling pipe 32. (5) Adjust the support base 17 according to the indication of the level instrument 43 to keep the closed container 1 level; and remove the protective cover of the standard leak hole 2, and place a transparent baffle 21 around the standard leak hole 2. (6) Adjust the camera device 42 with data storage function so that the pressure value displayed by the pressure gauge 41 and the core of the standard leak hole 2 can be fully and clearly presented in the camera screen, and turn on the camera device 42 with data storage function. (7) Turn on the gas source 5, adjust the pressure reducing valve 31 to make its outlet pressure reach the filling pressure, open the shut-off valve at the gas filling port 11, observe the pressure display value of the pressure gauge 41, and when the filling pressure is reached, close the shut-off valve at the port 11, open the shut-off valve on the standard leak hole adapter 18 and record the test start time. After observing the first droplet occurrence at each standard leak, record the corresponding test end time. After the experiment is completed, based on the experiment end time... With the start time of the experiment The difference can be used to obtain the candidate time corresponding to each standard leak.

[0039] S130, determine one of the multiple candidate times from the first time range as the reference time, and determine the leakage rate of the standard leak corresponding to the reference time as the reference critical leakage rate of the reference aircraft fuel tank.

[0040] The first time range is determined based on the test time of a reference aircraft fuel tank, and the critical leakage rate is used to characterize the leakage rate of the most severe local leak point on the aircraft fuel tank. The first time range can refer to the acceptable time range corresponding to the reference aircraft fuel tank. The reference critical leakage rate can refer to the critical leakage rate corresponding to the reference aircraft fuel tank, and can be used to characterize the leakage rate of the most severe local leak point on the reference aircraft fuel tank. The reference time can refer to a candidate time that meets the first time range and is closest to the test time of the reference aircraft fuel tank.

[0041] In this embodiment, optionally, the lower limit of the time range is set to the aircraft fuel tank test time, and the upper limit is set to 1.05 times the aircraft fuel tank test time. For example, assuming the aircraft fuel tank test time is... Then the time range can be set to [ By setting a reasonable time range, acceptable tolerance can be provided while ensuring the accuracy of leak testing.

[0042] In this embodiment, after obtaining the candidate time corresponding to each standard leak, a time that meets the first time range can be determined from multiple candidate times. If only one candidate time meets the first time range, it is directly determined as the reference time. If multiple candidate times meet the first time range, the candidate time closest to the test time of the reference aircraft fuel tank is selected as the reference time. The leakage rate of the standard leak corresponding to the reference time can then be determined as the reference critical leakage rate of the reference aircraft fuel tank. This yields the leakage rate of the most severely leaking local leak point on the reference aircraft fuel tank, achieving a semi-quantitative assessment of the leakage rate of local leak points in the aircraft fuel tank.

[0043] The technical solution of this invention, in response to a leak test request for a reference aircraft fuel tank, firstly obtains reference test parameters for the reference aircraft fuel tank, and determines the pressure value at the maximum pressure point of the reference aircraft fuel tank as the reference pressure based on the reference test parameters. The test parameters include test time, solvent density, gravitational acceleration, and maximum liquid level height. Then, the time when the solvent first drips through multiple standard leak holes with different leakage rates under the reference pressure is determined as a candidate time. Subsequently, a reference time is selected from the multiple candidate times based on a first time range, and the leakage rate of the standard leak hole corresponding to the reference time is determined as the reference critical leakage rate of the reference aircraft fuel tank. The first time range is determined based on the test time of the reference aircraft fuel tank, and the critical leakage rate is used to characterize the leakage rate of the most severely leaking local leak point on the aircraft fuel tank. This technical solution can quickly and effectively assess the critical leakage rate of local leak points in aircraft fuel tanks based on the permeation method, achieving a semi-quantitative assessment of the leakage rate of local leak points in aircraft fuel tanks, which helps improve the accuracy of aircraft fuel tank leak test results.

[0044] Example 2

[0045] Figure 3This is a flowchart of a method for determining the leakage rate of a local leak point in an aircraft fuel tank according to Embodiment 2 of the present invention. This embodiment is an optimization based on the above embodiment. Specifically, the optimization includes: after determining the leakage rate of the standard leak corresponding to the reference time as the reference critical leakage rate of the reference aircraft fuel tank, obtaining the maximum pressure value that the reference aircraft fuel tank can withstand as the limit pressure; wherein, the limit pressure is greater than the reference pressure; determining a pressure range based on the reference pressure and the limit pressure, selecting multiple pressure values ​​within the pressure range, and using the reference pressure, the limit pressure, and the selected multiple pressure values ​​as candidate pressures; determining the time when the detection solvent first drips through the standard leak corresponding to the reference critical leakage rate at each candidate pressure as the target time; and using the least squares method to fit the candidate pressures at each target time to obtain the pressure-time curve corresponding to the reference critical leakage rate.

[0046] like Figure 3 As shown, the method in this embodiment specifically includes the following steps:

[0047] S210, in response to a leak test request for a reference aircraft fuel tank, obtains reference test parameters for the reference aircraft fuel tank, and determines the pressure value of the reference aircraft fuel tank at the maximum pressure point as the reference pressure based on the reference test parameters.

[0048] The test parameters include test time, solvent density, gravitational acceleration, and maximum liquid level.

[0049] S220, determine the time when the detection solvent first drips through multiple standard leaks with different leakage rates under reference pressure as the candidate time.

[0050] S230, based on the first time range, select one from multiple candidate times as the reference time, and determine the leakage rate of the standard leak corresponding to the reference time as the reference critical leakage rate of the reference aircraft fuel tank.

[0051] The first time range is determined based on the test time of a reference aircraft fuel tank, and the critical leakage rate is used to characterize the leakage rate of the most severe local leak point on the aircraft fuel tank. Furthermore, the specific implementation methods of S210-S230 can be found in the detailed description in the above embodiments, and will not be repeated here.

[0052] S240, obtain the maximum pressure value that the reference aircraft fuel tank can withstand as the ultimate pressure.

[0053] The ultimate pressure is determined based on the aircraft fuel tank design specifications, and the ultimate pressure is greater than the reference pressure.

[0054] S250 determines the pressure range based on the reference pressure and the ultimate pressure, selects multiple pressure values ​​within the pressure range, and uses the reference pressure, the ultimate pressure, and the selected multiple pressure values ​​as candidate pressures.

[0055] In this embodiment, the ultimate pressure of the reference aircraft fuel tank is obtained. and reference pressure Then, a pressure range can be determined based on the two factors. Then, using equal or unequal intervals in [ Select multiple pressure values ​​on the [screen] and [then]... , And multiple pressure values ​​were selected as candidate pressures. It should be noted that, in order to ensure the accuracy of subsequent curve fitting, at least 5 pressure values ​​should be selected as candidate pressures.

[0056] S260, determine the time when the detection solvent first drips through the standard leak corresponding to the reference critical leakage rate at each candidate pressure as the target time.

[0057] In this embodiment, based on a pre-built aircraft fuel tank local leak rate test system, the time when the test solvent first drips through the standard leak corresponding to the reference critical leak rate at each candidate pressure (determined by the difference between the test end time and the test start time) can be used as the target time. One candidate pressure... Corresponding to a target time This yielded multiple experimental data pairs ( ).

[0058] S270, the least squares method is used to fit the candidate pressure at each target time to obtain the pressure-time curve corresponding to the reference critical leakage rate.

[0059] In this embodiment, after obtaining multiple experimental data pairs ( After that, the least squares method can be used for all ( Data fitting is performed to obtain the pressure-time curve (i.e., Pt curve) corresponding to the reference critical leakage rate, thereby obtaining the relationship between pressure, time, and critical leakage rate.

[0060] In this embodiment, optionally, after fitting the candidate pressures at each target time using the least squares method to obtain the pressure-time curve corresponding to the reference critical leakage rate, the method further includes: in response to a leakage test request from the target aircraft fuel tank, obtaining the target test parameters of the target aircraft fuel tank; determining the pressure value at the maximum pressure bearing point of the target aircraft fuel tank as the target pressure based on the target test parameters; querying the pressure-time curve corresponding to the reference critical leakage rate based on the target pressure and the test time in the target test parameters to obtain the data query result; if the data query result is successful, then the reference critical leakage rate is determined as the target critical leakage rate of the target aircraft fuel tank.

[0061] The target aircraft fuel tank can refer to any aircraft fuel tank other than the reference aircraft fuel tank awaiting leak testing. Target test parameters can refer to the test parameters corresponding to the target aircraft fuel tank, specifically including test time, solvent density, gravitational acceleration, and maximum liquid level. Target pressure can refer to the pressure of the target aircraft fuel tank at its maximum pressure point. Target critical leakage rate can refer to the critical leakage rate corresponding to the target aircraft fuel tank. Data query results include successful or unsuccessful query.

[0062] In this embodiment, when a leak test request for the target aircraft's fuel tank is detected, the leak test request is first parsed to obtain the target test parameters for the target aircraft's fuel tank (including test time, detection solvent density, gravitational acceleration, and maximum liquid level height). Then, based on the target test parameters, the formula is used... The pressure at the maximum pressure point of the target aircraft's fuel tank is determined as the target pressure. Then, based on the target pressure and the test time in the target test parameters, the pressure-time curve corresponding to the reference critical leakage rate is retrieved to obtain the data query result. If the data point formed by the target pressure and the test time in the target test parameters lies on the pressure-time curve corresponding to the reference critical leakage rate, the data query result is considered successful, and the reference critical leakage rate can be directly determined as the target critical leakage rate of the target aircraft's fuel tank. In this case, no experiment is required; the target critical leakage rate of the target aircraft's fuel tank can be determined simply by querying the curve, thereby significantly shortening the leakage test time and improving the leakage test efficiency.

[0063] Figure 4 This is a flowchart illustrating a method for determining the leakage rate of localized leaks in an aircraft fuel tank, as provided by the present invention. (See also...) Figure 4 First, obtain the temperature of the aircraft fuel tank. Detection of solvent density Local gravitational acceleration Maximum liquid level in aircraft fuel tanks Calculate the pressure value at the point of maximum pressure bearing of the aircraft fuel tank. (Gauge pressure). Then obtain the test time of the aircraft fuel tank. ,Record The time it takes for the solvent to first drip through the standard leak L under pressure. .like Then Leakage rate of the corresponding standard leak L As the critical leakage rate of aircraft fuel tanks. If Select a standard leak with a lower leakage rate and repeat the test; if Select a standard leak with a higher leakage rate and repeat the test until the requirement is met. After determining the critical leakage rate of the aircraft fuel tank, it is also necessary to obtain the maximum pressure that the aircraft fuel tank can withstand. and in and Select several from between ( ). And then record each The time it takes for the solvent to first drip through the standard leak L under pressure. Then, the least squares method is used to plot the pressure-time (Pt) curve, which serves as the basis for curve lookup in subsequent leak tests.

[0064] In this embodiment, optionally, the method further includes: if the data query result is a query failure, determining the time when the detection solvent first drips through multiple standard leaks with different leakage rates under the target pressure; determining the target critical leakage rate of the target aircraft fuel tank based on the leakage rate of the standard leaks corresponding to the time that meets the second time range; wherein the second time range is determined based on the test time of the target aircraft fuel tank.

[0065] In this embodiment, if the data point formed by the target pressure and the test time in the target test parameters is not located on the pressure-time curve corresponding to the reference critical leakage rate, the data query result is determined to be a query failure. In this case, the target critical leakage rate of the target aircraft fuel tank needs to be determined by testing using a pre-built aircraft fuel tank local leak rate test system. Specifically, firstly, the time when the detection solvent first drips through multiple standard leaks with different leakage rates under the target pressure is determined. Then, the time that meets the second time range (determined based on the test time of the target aircraft fuel tank) is searched, and the time closest to the test time of the target aircraft fuel tank is selected. The leakage rate of the standard leak corresponding to this time is determined as the target critical leakage rate of the target aircraft fuel tank. Furthermore, the pressure-time curve corresponding to the target critical leakage rate can be determined by referring to the implementation method of S240-S270 to provide a more sufficient curve reference for subsequent leakage tests.

[0066] The technical solution of this invention, after determining the leakage rate of the standard leak corresponding to the reference time as the reference critical leakage rate of the reference aircraft fuel tank, obtains the maximum pressure value that the reference aircraft fuel tank can withstand as the ultimate pressure; wherein, the ultimate pressure is greater than the reference pressure; a pressure range is determined based on the reference pressure and the ultimate pressure, and multiple pressure values ​​are selected within the pressure range, with the reference pressure, the ultimate pressure, and the selected multiple pressure values ​​serving as candidate pressures; the time when the detection solvent first drips through the standard leak corresponding to the reference critical leakage rate at each candidate pressure is determined as the target time; the least squares method is used to fit the candidate pressures at each target time to obtain the pressure-time curve corresponding to the reference critical leakage rate. This technical solution can quickly and effectively assess the critical leakage rate of local leaks in aircraft fuel tanks based on the permeation method, achieving a semi-quantitative assessment of the leakage rate of local leaks in aircraft fuel tanks, improving the accuracy of aircraft fuel tank leakage test results, and establishing a pressure-time curve under the reference critical leakage rate, providing a curve lookup basis for subsequent leakage tests, helping to shorten leakage test time and improve leakage test efficiency.

[0067] In this embodiment, optionally, the method further includes: if the critical leakage rate is greater than a preset leakage rate threshold, then the test result of the corresponding aircraft fuel tank is determined to be a failure of the leakage test; if the critical leakage rate is less than or equal to the preset leakage rate threshold, then the test result of the corresponding aircraft fuel tank is determined to be a success of the leakage test.

[0068] In this embodiment, after determining the critical leakage rate corresponding to the aircraft fuel tank, the critical leakage rate can be compared with a preset leakage rate threshold (which can be set according to actual needs), and the test result of the aircraft fuel tank can be determined based on the comparison result. Specifically, if the critical leakage rate is greater than the preset leakage rate threshold, it indicates that the critical leakage rate exceeds the acceptable range, and the test result of the corresponding aircraft fuel tank is determined to be a failure of the leakage test; if the critical leakage rate is less than or equal to the preset leakage rate threshold, it indicates that the critical leakage rate is within the acceptable range, and the test result of the corresponding aircraft fuel tank is determined to be a pass of the leakage test.

[0069] This method, through this setting, determines the test results of the aircraft fuel tank based on the critical leakage rate of the aircraft fuel tank, which has higher test accuracy compared to the overall leakage rate of the aircraft fuel tank.

[0070] Example 3

[0071] Figure 5 This is a schematic diagram of a device for determining the leakage rate of a local leak point in an aircraft fuel tank according to Embodiment 3 of the present invention. This device can execute the method for determining the leakage rate of a local leak point in an aircraft fuel tank provided in any embodiment of the present invention, and possesses the corresponding functional modules and beneficial effects of the method. Figure 5 As shown, the device includes:

[0072] The reference pressure determination module 310 is used to respond to a leak test request of a reference aircraft fuel tank, acquire reference test parameters of the reference aircraft fuel tank, and determine the pressure value of the reference aircraft fuel tank at the maximum pressure bearing point as the reference pressure based on the reference test parameters; wherein, the test parameters include test time, detection solvent density, gravitational acceleration, and maximum liquid level height;

[0073] The candidate time determination module 320 is used to determine the time when the detection solvent first drips through multiple standard leaks with different leakage rates under the reference pressure as the candidate time.

[0074] The reference leakage rate determination module 330 is used to determine one of the candidate times from a plurality of time ranges as a reference time, and to determine the leakage rate of the standard leak corresponding to the reference time as the reference critical leakage rate of the reference aircraft fuel tank; wherein, the first time range is determined based on the test time of the reference aircraft fuel tank, and the critical leakage rate is used to characterize the leakage rate of the most serious local leak point on the aircraft fuel tank.

[0075] Optionally, the device further includes a pressure-time curve determination module, used for:

[0076] After determining the leakage rate of the standard leak corresponding to the reference time as the reference critical leakage rate of the reference aircraft fuel tank, the maximum pressure value that the reference aircraft fuel tank can withstand is obtained as the ultimate pressure; wherein, the ultimate pressure is greater than the reference pressure;

[0077] A pressure range is determined based on the reference pressure and the ultimate pressure. Multiple pressure values ​​are selected within the pressure range, and the reference pressure, the ultimate pressure, and the selected multiple pressure values ​​are used as candidate pressures.

[0078] The time when the detection solvent first drips through the standard leak corresponding to the reference critical leakage rate at each candidate pressure is determined as the target time.

[0079] The least squares method is used to fit the candidate pressure at each target time to obtain the pressure-time curve corresponding to the reference critical leakage rate.

[0080] Optionally, the device further includes: a target leakage rate determination module, used for:

[0081] After fitting the candidate pressure at each target time using the least squares method to obtain the pressure-time curve corresponding to the reference critical leakage rate, the target test parameters of the target aircraft fuel tank are obtained in response to the leakage test request of the target aircraft fuel tank.

[0082] The target pressure is determined based on the target test parameters at the maximum pressure point of the target aircraft fuel tank.

[0083] The data query results are obtained by querying the pressure-time curve corresponding to the reference critical leakage rate based on the target pressure and the test time in the target test parameters.

[0084] If the data query result is successful, then the reference critical leakage rate is determined as the target critical leakage rate of the target aircraft fuel tank.

[0085] Optionally, the target leakage rate determination module is further configured to:

[0086] If the data query result is a query failure, then the time when the detection solvent first drips through multiple standard leaks with different leakage rates under the target pressure is determined.

[0087] The target critical leakage rate of the target aircraft fuel tank is determined based on the leakage rate of the standard leak corresponding to the time within the second time range; wherein the second time range is determined based on the test time of the target aircraft fuel tank.

[0088] Optionally, the apparatus further includes: a leakage test result determination module, used for:

[0089] If the critical leakage rate is greater than the preset leakage rate threshold, the test result of the corresponding aircraft fuel tank is determined to be a failure of the leakage test;

[0090] If the critical leakage rate is less than or equal to the preset leakage rate threshold, then the test result of the corresponding aircraft fuel tank is determined to be a pass in the leakage test.

[0091] Optionally, the lower limit of the time range is set to the aircraft fuel tank test time, and the upper limit is set to 1.05 times the aircraft fuel tank test time.

[0092] Optionally, the reference pressure determination module 310 is used for:

[0093] The reference pressure is determined by multiplying the detected solvent density, gravitational acceleration, and maximum liquid level height of the reference aircraft fuel tank.

[0094] The device for determining the leakage rate of a local leak point in an aircraft fuel tank provided in this embodiment of the invention can execute the method for determining the leakage rate of a local leak point in an aircraft fuel tank provided in any embodiment of the invention, and has the corresponding functional modules and beneficial effects of executing the method.

[0095] Example 4

[0096] Figure 6 A schematic diagram of an electronic device 10, which can be used to implement embodiments of the present invention, is shown. The electronic device is intended to represent various forms of digital computers, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device can also represent various forms of mobile devices, such as personal digital processors, cellular phones, smartphones, wearable devices (e.g., helmets, glasses, watches, etc.), and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely illustrative and are not intended to limit the implementation of the invention described and / or claimed herein.

[0097] like Figure 6 As shown, the electronic device 10 includes at least one processor 11 and a memory, such as a read-only memory (ROM) 12 or a random access memory (RAM) 13, communicatively connected to the at least one processor 11. The memory stores computer programs executable by the at least one processor. The processor 11 can perform various appropriate actions and processes based on the computer program stored in the ROM 12 or loaded from storage unit 18 into the RAM 13. The RAM 13 can also store various programs and data required for the operation of the electronic device 10. The processor 11, ROM 12, and RAM 13 are interconnected via a bus 14. An input / output (I / O) interface 15 is also connected to the bus 14.

[0098] Multiple components in electronic device 10 are connected to I / O interface 15, including: input unit 16, such as keyboard, mouse, etc.; output unit 17, such as various types of displays, speakers, etc.; storage unit 18, such as disk, optical disk, etc.; and communication unit 19, such as network card, modem, wireless transceiver, etc. Communication unit 19 allows electronic device 10 to exchange information / data with other devices through computer networks such as the Internet and / or various telecommunications networks.

[0099] Processor 11 can be a variety of general-purpose and / or special-purpose processing components with processing and computing capabilities. Some examples of processor 11 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various special-purpose artificial intelligence (AI) computing chips, various processors running machine learning model algorithms, a digital signal processor (DSP), and any suitable processor, controller, microcontroller, etc. Processor 11 performs the various methods and processes described above, such as the method for determining the leakage rate of local leaks in aircraft fuel tanks.

[0100] In some embodiments, the method for determining the leakage rate of localized leaks in an aircraft fuel tank can be implemented as a computer program tangibly contained in a computer-readable storage medium, such as storage unit 18. In some embodiments, part or all of the computer program can be loaded and / or installed on electronic device 10 via ROM 12 and / or communication unit 19. When the computer program is loaded into RAM 13 and executed by processor 11, one or more steps of the method for determining the leakage rate of localized leaks in an aircraft fuel tank described above can be performed. Alternatively, in other embodiments, processor 11 can be configured to perform the method for determining the leakage rate of localized leaks in an aircraft fuel tank by any other suitable means (e.g., by means of firmware).

[0101] Various embodiments of the systems and techniques described above herein can be implemented in digital electronic circuit systems, integrated circuit systems, field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), application-specific standard products (ASSPs), systems-on-a-chip (SoCs), payload-programmable logic devices (CPLDs), computer hardware, firmware, software, and / or combinations thereof. These various embodiments may include implementations in one or more computer programs that can be executed and / or interpreted on a programmable system including at least one programmable processor, which may be a dedicated or general-purpose programmable processor, capable of receiving data and instructions from a storage system, at least one input device, and at least one output device, and transmitting data and instructions to the storage system, the at least one input device, and the at least one output device.

[0102] Computer programs used to implement the methods of the present invention may be written in any combination of one or more programming languages. These computer programs may be provided to a processor of a general-purpose computer, a special-purpose computer, or other programmable data processing device, such that when executed by the processor, the computer programs cause the functions / operations specified in the flowcharts and / or block diagrams to be performed. The computer programs may be executed entirely on a machine, partially on a machine, or as a standalone software package, partially on a machine and partially on a remote machine, or entirely on a remote machine or server.

[0103] In the context of this invention, a computer-readable storage medium can be a tangible medium that may contain or store a computer program for use by or in conjunction with an instruction execution system, apparatus, or device. A computer-readable storage medium may include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, apparatus, or devices, or any suitable combination thereof. Alternatively, a computer-readable storage medium may be a machine-readable signal medium. More specific examples of machine-readable storage media include electrical connections based on one or more wires, portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fibers, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof.

[0104] To provide interaction with a user, the systems and techniques described herein can be implemented on an electronic device having: a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to the user; and a keyboard and pointing device (e.g., a mouse or trackball) through which the user provides input to the electronic device. Other types of devices can also be used to provide interaction with the user; for example, feedback provided to the user can be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user can be received in any form (including sound input, voice input, or tactile input).

[0105] The systems and technologies described herein can be implemented in computing systems that include backend components (e.g., as data servers), or middleware components (e.g., application servers), or frontend components (e.g., user computers with graphical user interfaces or web browsers through which users can interact with implementations of the systems and technologies described herein), or any combination of such backend, middleware, or frontend components. The components of the system can be interconnected via digital data communication of any form or medium (e.g., communication networks). Examples of communication networks include local area networks (LANs), wide area networks (WANs), blockchain networks, and the Internet.

[0106] A computing system can include clients and servers. Clients and servers are generally located far apart and typically interact through communication networks. The client-server relationship is created by computer programs running on the respective computers and having a client-server relationship with each other. The server can be a cloud server, also known as a cloud computing server or cloud host, which is a hosting product within the cloud computing service system to address the shortcomings of traditional physical hosts and VPS services, such as high management difficulty and weak business scalability.

[0107] It should be understood that the various forms of processes shown above can be used, with steps reordered, added, or deleted. For example, the steps described in this invention can be executed in parallel, sequentially, or in different orders, as long as the desired result of the technical solution of this invention can be achieved, and this is not limited herein.

[0108] The specific embodiments described above do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A method for determining the leakage rate of localized leak points in an aircraft fuel tank, characterized in that, The method includes: In response to a leak test request for a reference aircraft fuel tank, reference test parameters for the reference aircraft fuel tank are obtained, and the pressure value of the reference aircraft fuel tank at the maximum pressure point is determined as the reference pressure based on the reference test parameters; wherein, the test parameters include test time, detection solvent density, gravitational acceleration, and maximum liquid level height; The time when the detection solvent first drips through multiple standard leaks with different leakage rates at the reference pressure is determined as the candidate time. Based on a first time range, one of the candidate times is determined as a reference time, and the leakage rate of the standard leak corresponding to the reference time is determined as the reference critical leakage rate of the reference aircraft fuel tank; wherein, the first time range is determined based on the test time of the reference aircraft fuel tank, and the critical leakage rate is used to characterize the leakage rate of the most serious local leak point on the aircraft fuel tank.

2. The method according to claim 1, characterized in that, After determining the leakage rate of the standard leak corresponding to the reference time as the reference critical leakage rate of the reference aircraft fuel tank, the method further includes: The maximum pressure that the reference aircraft fuel tank can withstand is obtained as the ultimate pressure; wherein, the ultimate pressure is greater than the reference pressure; A pressure range is determined based on the reference pressure and the ultimate pressure. Multiple pressure values ​​are selected within the pressure range, and the reference pressure, the ultimate pressure, and the selected multiple pressure values ​​are used as candidate pressures. The time when the detection solvent first drips through the standard leak corresponding to the reference critical leakage rate at each candidate pressure is determined as the target time. The least squares method is used to fit the candidate pressure at each target time to obtain the pressure-time curve corresponding to the reference critical leakage rate.

3. The method according to claim 2, characterized in that, After fitting the candidate pressure at each target time using the least squares method to obtain the pressure-time curve corresponding to the reference critical leakage rate, the method further includes: In response to a leak test request for the target aircraft's fuel tank, the target test parameters for the target aircraft's fuel tank are obtained; The target pressure is determined based on the target test parameters at the maximum pressure point of the target aircraft fuel tank. The data query results are obtained by querying the pressure-time curve corresponding to the reference critical leakage rate based on the target pressure and the test time in the target test parameters. If the data query result is successful, then the reference critical leakage rate is determined as the target critical leakage rate of the target aircraft fuel tank.

4. The method according to claim 3, characterized in that, The method further includes: If the data query result is a query failure, then the time when the detection solvent first drips through multiple standard leaks with different leakage rates under the target pressure is determined. The target critical leakage rate of the target aircraft fuel tank is determined based on the leakage rate of the standard leak corresponding to the time within the second time range; wherein the second time range is determined based on the test time of the target aircraft fuel tank.

5. The method according to any one of claims 1-4, characterized in that, The method further includes: If the critical leakage rate is greater than the preset leakage rate threshold, the test result of the corresponding aircraft fuel tank is determined to be a failure of the leakage test; If the critical leakage rate is less than or equal to the preset leakage rate threshold, then the test result of the corresponding aircraft fuel tank is determined to be a pass in the leakage test.

6. The method according to any one of claims 1-4, characterized in that, The lower limit of the time range is set as the aircraft fuel tank test time, and the upper limit is set as 1.05 times the aircraft fuel tank test time.

7. The method according to any one of claims 1-4, characterized in that, Determining the pressure value of the reference aircraft fuel tank at the maximum pressure point based on the reference test parameters as the reference pressure includes: The reference pressure is determined by multiplying the detected solvent density, gravitational acceleration, and maximum liquid level height of the reference aircraft fuel tank.

8. A device for determining the leakage rate of local leak points in an aircraft fuel tank, characterized in that, The device includes: The reference pressure determination module is used to respond to a leak test request of a reference aircraft fuel tank, acquire reference test parameters of the reference aircraft fuel tank, and determine the pressure value of the reference aircraft fuel tank at the maximum pressure bearing point as the reference pressure based on the reference test parameters; wherein, the test parameters include test time, detection solvent density, gravitational acceleration, and maximum liquid level height; The candidate time determination module is used to determine the time when the detection solvent first drips through multiple standard leaks with different leakage rates under the reference pressure as the candidate time. The reference leakage rate determination module is used to determine one of the candidate times from a plurality of time ranges as a reference time based on a first time range, and to determine the leakage rate of the standard leak corresponding to the reference time as the reference critical leakage rate of the reference aircraft fuel tank; wherein, the first time range is determined based on the test time of the reference aircraft fuel tank, and the critical leakage rate is used to characterize the leakage rate of the most serious local leak point on the aircraft fuel tank.

9. An electronic device, characterized in that, The electronic device includes: At least one processor; and, A memory communicatively connected to the at least one processor; wherein, The memory stores a computer program that can be executed by the at least one processor, the computer program being executed by the at least one processor to enable the at least one processor to perform the method for determining the leakage rate of local leaks in an aircraft fuel tank as described in any one of claims 1-7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer instructions that cause a processor to execute the method for determining the leakage rate of local leaks in an aircraft fuel tank as described in any one of claims 1-7.

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