Jet field measurement system and method for aircraft tire explosion

Abstract

The invention discloses a jet flow field measurement system and method for aircraft tire explosion. The system comprises a perforated tire, a fixing frame, a jet flow control module, an inflation module and a jet flow measurement module. The perforated tire is an aircraft tire of which the side surface is provided with a jet hole; the fixing frame is used for fixing the perforated tire on the ground in a standing manner; the inflating module is in data connection with the jet flow control module and the jet flow measurement module, is in airtight connection with an inflating opening of the perforated tire and is used for inflating high-pressure tracer gas into the perforated tire and generating a trigger signal; the jet flow control module is fixed on the outer side surface of the perforated tire and is used for controlling the opening and closing of the jet flow hole according to the trigger signal so as to form a gas jet flow; and the jet flow measurement module is used for measuring the gas jet flow according to the trigger signal to obtain a global peak velocity sequence. The interference of the sensor on the gas jet can be reduced, and the accuracy of peak velocity measurement is improved.

Description

Technical Field

[0001] This invention belongs to the field of aircraft tire burst testing technology, specifically a jet field measurement system and method for aircraft tire bursts. Background Technology

[0002] As my country's independent aircraft research and development capabilities continue to improve, the demand for tire burst testing is also increasing. First, a tire burst generates a massive energy shock, potentially damaging critical equipment and piping within the landing gear bay. Burst tests verify whether this equipment can withstand the energy impact released during a tire burst, thus ensuring flight safety in extreme situations such as tire bursts. Second, burst tests obtain crucial data such as pressure distribution and impact load during a tire burst. This data is of significant guiding importance for designing safer landing gear bay protection structures, optimizing equipment layout, and developing protective measures. Finally, according to international airworthiness standards, aircraft design must consider the impact of tire bursts on aircraft safety. Burst tests verify whether the aircraft meets the requirements of relevant airworthiness regulations, ensuring aircraft safety under extreme conditions.

[0003] In aircraft tire burst tests, one of the most important data points is the relationship between the peak velocity of the gas jet and the ejection distance. This data helps assess the impact of the high-speed airflow generated during a tire burst on surrounding structures and equipment. By measuring the change in peak velocity with distance, the attenuation law of airflow energy can be clarified, providing a basis for designing appropriate protective measures. Furthermore, this data can be used to verify the accuracy of tire burst models, helping researchers better understand the energy release and propagation mechanisms during a tire burst. This provides crucial data for aircraft airworthiness assessment, ensuring that the aircraft's structure and systems can withstand the impact of a tire burst under extreme conditions, thereby guaranteeing flight safety.

[0004] However, existing measurement methods mainly rely on placing a series of sensors along the propagation path of the gas jet to measure its velocity. But the presence of these sensors and their mounting devices can interfere with the gas jet, distorting the measurement data. Furthermore, the closer the sensor is to the puncture in the tire, the stronger the interference with the gas jet, and the more severe the data distortion. Therefore, there is an urgent need for a measurement method that can reduce disturbances to the gas jet. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a jet field measurement system and method for aircraft tire bursting, which can reduce the interference of sensors on gas jets and improve the accuracy of peak velocity measurement.

[0006] To address the aforementioned technical problems, the first aspect of this invention discloses a jet field measurement system for aircraft tire bursting, the system comprising a perforated tire, a mounting frame, a jet control module, an inflation module, and a jet measurement module;

[0007] The perforated tire is an aircraft tire with jet holes on its side; the fixing frame is used to stand the perforated tire upright and fix it to the ground.

[0008] The inflation module is data-connected to the jet control module and the jet measurement module, and is airtightly connected to the inflation port of the perforated tire. It is used to inflate the perforated tire with high-pressure tracer gas and generate a trigger signal.

[0009] The jet control module is fixed to the outer side of the perforated tire and is used to control the opening and closing of the jet hole according to the trigger signal to form a gas jet.

[0010] The jet measurement module is used to measure the gas jet according to the trigger signal to obtain a global peak velocity sequence; the global peak velocity sequence includes several velocity values.

[0011] As an optional implementation, in the first aspect of the present invention, the inflation module includes a particle injection unit, a high-pressure air pump, a mixing chamber, a first pipeline, a second pipeline, a third pipeline, and a control unit;

[0012] The particle injection unit is electrically connected to the control unit and is used to inject tracer particles;

[0013] The high-pressure air pump is electrically connected to the control unit and is used to generate high-pressure gas and measure the internal air pressure value in real time.

[0014] The mixing chamber is an airtight structure with a first air inlet, a second air inlet, and an air outlet, used to mix the tracer particles and the high-pressure gas to obtain high-pressure tracer gas.

[0015] The two ends of the first pipeline are airtightly connected to the air outlet and the air inlet of the perforated tire, respectively; the two ends of the second pipeline are airtightly connected to the particle injection unit and the first air inlet, respectively; the two ends of the third pipeline are airtightly connected to the high-pressure air pump and the second air inlet, respectively.

[0016] The control unit is used to synchronously start the particle injection unit and the high-pressure air pump when the measurement begins, and to shut down the high-pressure air pump and generate the trigger signal when the internal air pressure value is greater than the preset working air pressure value.

[0017] As an optional implementation, in the first aspect of the present invention, the jet control module includes a reinforcement submodule and a jet orifice opening / closing submodule;

[0018] The reinforcing submodule is fixed to the outer side of the perforated tire and located above the jet hole, and is used to enhance the tire strength around the jet hole; the reinforcing submodule has a through hole corresponding to the jet hole;

[0019] The jet orifice opening and closing submodule is fixed to the top of the through hole of the reinforcing submodule and is used to seal the through hole when the high-pressure tracer gas is filled into the perforated tire, and to quickly open the through hole after receiving the trigger signal.

[0020] As an optional implementation, in the first aspect of the present invention, the jet measurement module includes a near-end measurement submodule, a far-end measurement submodule, and a data analysis submodule;

[0021] The proximal measurement submodule is connected to the inflation module and the data analysis submodule, and is used to measure the proximal jet video under the control of the trigger signal.

[0022] The remote measurement submodule is connected to the inflation module and the data analysis submodule, and is used to measure a set of remote center pressure sequences under the control of the trigger signal; the set of remote center pressure sequences includes N remote center pressure sequences; the remote center pressure sequence includes several pressure values; N is an integer greater than 1;

[0023] The data analysis submodule is used to process the near-end jet video and the far-end center pressure sequence set to obtain the global peak velocity sequence.

[0024] As an optional implementation, in the first aspect of the present invention, the near-end measurement submodule includes a sheet light source and a high-speed camera;

[0025] The sheet light source is fixedly disposed in front of the jet hole and is data connected to the inflation module, and is used to generate sheet light after receiving the trigger signal;

[0026] The high-speed camera is fixedly installed at the same height to the side of the jet orifice and is data-connected to the inflation module. It is used to capture the gas jet ejected from the jet orifice after receiving the trigger signal, so as to obtain a near-end jet video.

[0027] As an optional implementation, in the first aspect of the present invention, the sheet light source includes a semiconductor laser, a collimating lens, and a cylindrical lens.

[0028] As an optional implementation, in the first aspect of the present invention, the remote measurement submodule includes a base and N flow velocity measurement units;

[0029] The base is a plate-shaped structure used to fix the flow velocity measurement unit;

[0030] The flow velocity measurement unit includes a support rod and a piezoresistive sensor;

[0031] The bottom end of the support rod is vertically fixed to the upper surface of the base;

[0032] The piezoresistive sensor is fixed to the top of the support rod and is used to measure the corresponding distal center pressure sequence under the control of the trigger signal.

[0033] All of the piezoresistive sensors are located on the jet centerline; the jet centerline is a horizontal ray perpendicular to the jet orifice.

[0034] A second aspect of this invention discloses a method for measuring the jet field during aircraft tire bursting, the method comprising:

[0035] S1. Using the inflation module, high-pressure tracer gas is injected into the perforated tire, and a trigger signal is generated;

[0036] S2. Use the jet control module to unseal the jet orifice and form a gas jet;

[0037] S3. Using the jet measurement module, the gas jet is measured to obtain a set of near-end jet video and far-end center pressure sequence. The near-end jet video and the far-end center pressure sequence are then processed to obtain a global peak velocity sequence.

[0038] As an optional implementation, in the second aspect of the present invention, processing the near-end jet video and the far-end center pressure sequence set to obtain a global peak velocity sequence includes:

[0039] S31. The near-end jet video is split into a jet image sequence; the jet image sequence includes several near-end jet images;

[0040] S32. Process the jet image sequence to obtain a set of proximal center velocity sequences; the set of proximal center velocity sequences includes several proximal center velocity sequences;

[0041] S33. Process the set of proximal center velocity sequences to obtain the proximal peak velocity sequence;

[0042] S34. Process the set of remote center pressure sequences to obtain the remote peak velocity sequence;

[0043] S35. Perform spatial interpolation on the near-end peak velocity sequence and the far-end peak velocity sequence to obtain the global peak velocity sequence.

[0044] As an optional implementation, in a second aspect of the present invention, processing the proximal center velocity sequence set to obtain a proximal peak velocity sequence includes:

[0045] S331. Take each of the near-center velocity sequences as row vectors and concatenate them to obtain a velocity matrix;

[0046] S332. The maximum values ​​of each column of the velocity matrix are combined sequentially to obtain the near-end peak velocity sequence.

[0047] Compared with the prior art, the embodiments of the present invention have the following beneficial effects:

[0048] By using tracer particle method and sensor measurement at the near end and far end of the jet orifice respectively, the near end jet video and far end center pressure sequence are obtained, and further analysis is performed to obtain the global peak velocity sequence. This avoids the decrease in accuracy caused by simply using tracer particle method for far end analysis, reduces the distortion caused by setting up sensors at the near end, and thus improves the accuracy of measurement. Attached Figure Description

[0049] 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.

[0050] Figure 1 This is a top view of a jet field measurement system for aircraft tire bursting disclosed in an embodiment of the present invention.

[0051] Figure 2 This is a side view of the jet measurement module of a jet field measurement system for aircraft tire explosion disclosed in an embodiment of the present invention.

[0052] Figure 3 This is a schematic flowchart of a jet field measurement method for aircraft tire bursting disclosed in an embodiment of the present invention.

[0053] Explanation of reference numerals in the attached drawings: 1. Perforated tire; 2. Fixing frame; 3. Jet control module; 4. Inflation module; 41. Particle injection unit; 42. High-pressure air pump; 43. Mixing chamber; 431. First air inlet; 432. Second air inlet; 433. Air outlet; 44. First pipeline; 45. Second pipeline; 46. Third pipeline; 47. Control unit; 5. Jet measurement module; 51. Proximal measurement submodule; 511. Sheet light source; 5111. Optical platform; 512. High-speed camera; 52. Remote measurement submodule; 521. Flow velocity measurement unit; 5211. Support rod; 5212. Piezoresistive sensor; 522. Base. Detailed Implementation

[0054] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. 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 are within the scope of protection of the present invention.

[0055] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0056] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0057] Example 1

[0058] Please see Figure 1 and Figure 2 . Figure 1 This is a top view of a jet field measurement system for aircraft tire bursting disclosed in an embodiment of the present invention. Figure 2 This is a side view of the jet measurement module of a jet field measurement system for aircraft tire bursting, as disclosed in an embodiment of the present invention. Figure 1 and Figure 2 The described jet field measurement system for aircraft tire burst testing is applied in the field of aircraft tire burst testing, such as jet field measurement in aircraft tire burst testing. This invention is not limited to specific embodiments. Figure 1 and Figure 2 As shown, the system includes a perforated tire 1, a fixing frame 2, a jet control module 3, an inflation module 4, and a jet measurement module 5.

[0059] The aforementioned perforated tire 1 is an aircraft tire with jet holes on its side; the aforementioned fixing frame 2 is used to stand the aforementioned perforated tire 1 upright and fix it on the ground.

[0060] It should be noted that after the perforated tire 1 is fixed by the fixing bracket 2, its axis is in the horizontal direction. This can simulate the actual tire posture when an aircraft tire bursts, making the generated gas jet closer to the actual distribution.

[0061] The inflation module 4 is connected to the jet control module 3 and the jet measurement module 5 via data connection, and is airtightly connected to the inflation port of the perforated tire 1. It is used to inflate the perforated tire 1 with high-pressure tracer gas and generate a trigger signal.

[0062] The jet control module 3 is fixed to the outer side of the perforated tire 1 and is used to control the opening and closing of the jet hole according to the trigger signal to form a gas jet.

[0063] It should be noted that the jet control module 3 mentioned above closes the jet orifice by default, and only quickly uncloses the jet orifice after receiving a trigger signal.

[0064] The jet measurement module 5 is used to measure the gas jet according to the trigger signal to obtain a global peak velocity sequence; the global peak velocity sequence includes several velocity values.

[0065] It should be noted that the above global peak velocity sequence represents the maximum gas velocity at a series of uniformly distributed positions along the jet centerline, arranged from farthest to closest to the jet orifice.

[0066] In an optional embodiment, the inflation module 4 includes a particle injection unit 41, a high-pressure air pump 42, a mixing chamber 43, a first pipeline 44, a second pipeline 45, a third pipeline 46, and a control unit 47.

[0067] The particle injection unit 41 is electrically connected to the control unit 47 and is used to inject tracer particles.

[0068] Preferably, the tracer particles are mica powder with a diameter of 6 μm.

[0069] The high-pressure air pump 42 is electrically connected to the control unit 47 and is used to generate high-pressure gas and measure the internal air pressure value in real time.

[0070] The aforementioned mixing chamber 43 is an airtight structure with a first air inlet 431, a second air inlet 432, and an air outlet 433, used to mix the aforementioned tracer particles and the aforementioned high-pressure gas to obtain high-pressure tracer gas.

[0071] The two ends of the first pipe 44 are respectively airtightly connected to the air outlet 433 and the air inlet of the perforated tire 1; the two ends of the second pipe 45 are respectively airtightly connected to the particle injection unit 41 and the first air inlet 431; the two ends of the third pipe 46 are respectively airtightly connected to the high-pressure air pump 42 and the second air inlet 432.

[0072] The control unit 47 is used to synchronously start the particle injection unit 41 and the high-pressure air pump 42 when the measurement begins, and to shut down the high-pressure air pump 42 and generate the trigger signal when the internal air pressure value is greater than the preset working air pressure value.

[0073] It should be noted that the control unit 47 mentioned above can be implemented by a microcontroller, FPGA or PLC, and the embodiments of the present invention are not limited thereto.

[0074] In another optional embodiment, the jet control module 3 includes a reinforcement submodule and a jet orifice opening / closing submodule.

[0075] The aforementioned reinforcing submodule is fixed to the outer side of the aforementioned perforated tire 1 and located above the aforementioned jet hole, for enhancing the tire strength around the aforementioned jet hole; the aforementioned reinforcing submodule has a through hole corresponding to the aforementioned jet hole.

[0076] The aforementioned jet orifice opening and closing submodule is fixed to the top of the aforementioned through hole of the aforementioned reinforcing submodule, and is used to seal the aforementioned through hole when the aforementioned high-pressure tracer gas is filled into the aforementioned perforated tire 1, and to quickly open the aforementioned through hole after receiving the aforementioned trigger signal.

[0077] Optionally, the above-mentioned jet orifice opening and closing sub-module includes a jet orifice sealing unit and a combustion power unit.

[0078] Optionally, the aforementioned jet nozzle sealing unit is connected to the reinforcing submodule to construct the jet nozzle and jet channel, forming the gas jet required for the experiment.

[0079] Optionally, the aforementioned deflagration power unit is connected to the jet nozzle sealing unit to provide the deflagration power required to generate the gas jet that causes the aircraft tire to burst.

[0080] In yet another optional embodiment, the jet measurement module 5 described above includes a near-end measurement submodule 51, a far-end measurement submodule 52, and a data analysis submodule.

[0081] The aforementioned proximal measurement submodule 51 is connected to the aforementioned inflation module 4 and the aforementioned data analysis submodule, and is used to measure the proximal jet video under the control of the aforementioned trigger signal.

[0082] The aforementioned remote measurement submodule 52 is connected to the aforementioned inflation module 4 and the aforementioned data analysis submodule, and is used to measure and obtain a set of remote center pressure sequences under the control of the aforementioned trigger signal; the aforementioned set of remote center pressure sequences includes N remote center pressure sequences; the aforementioned remote center pressure sequences include several pressure values; N is an integer greater than 1.

[0083] The aforementioned data analysis submodule is used to process the aforementioned near-end jet video and the aforementioned far-end center pressure sequence set to obtain the aforementioned global peak velocity sequence.

[0084] It should be noted that the above-mentioned data analysis submodule can be implemented by an executable program preset on a PC, and this embodiment of the invention does not impose any limitations.

[0085] In yet another alternative embodiment, the aforementioned near-end measurement submodule 51 includes a sheet light source 511 and a high-speed camera 512.

[0086] The aforementioned sheet light source 511 is fixedly disposed in front of the aforementioned jet hole and is data-connected to the aforementioned inflation module 4, and is used to generate sheet light after receiving the aforementioned trigger signal.

[0087] It should be noted that the height of the aforementioned sheet light source 511 is higher than the jet aperture, and the sheet light it produces shines vertically downwards. The aforementioned sheet light is a special beam of light, the shape of which is a very thin plane, used to uniformly illuminate a vertical two-dimensional plane area in front of the jet aperture, and the jet centerline is located within this two-dimensional plane area.

[0088] Preferably, the horizontal distance between the sheet light source 511 and the jet hole is 10cm, and the horizontal width of the two-dimensional planar area illuminated by the sheet light source 511 is 20cm.

[0089] Preferably, the vertical distance between the above-mentioned sheet light source 511 and the jet hole is 80cm.

[0090] The high-speed camera 512 is fixedly installed at the same height to the side of the jet hole and is connected to the inflation module 4 for data transmission. It is used to capture the gas jet ejected from the jet hole after receiving the trigger signal, and obtain a near-end jet video.

[0091] It should be noted that the shooting direction of the aforementioned high-speed camera is perpendicular to the two-dimensional plane region where the sheet light is located. The near-end jet video captured by the camera corresponds to a rectangular region symmetrical about the center line of the jet within the aforementioned two-dimensional plane region outside the jet aperture. Due to the scattering caused by the tracer particles in the high-pressure tracer gas, each frame in the near-end jet video can accurately reflect the position of each tracer particle within that rectangular region at the corresponding moment.

[0092] However, after the gas jet exits the jet orifice, the concentration of tracer particles continuously decreases, resulting in sparse tracer particles in the captured images, making it difficult to accurately reflect changes in the flow field. Therefore, using the near-end measurement submodule 51 to capture images near the jet orifice outlet to obtain near-end jet video can avoid the decrease in subsequent analysis accuracy caused by the reduction in far-end tracer particle concentration.

[0093] In yet another alternative embodiment, the sheet light source 511 described above includes a semiconductor laser, a collimating lens, and a cylindrical lens.

[0094] It should be noted that the aforementioned semiconductor laser is fixed on the optical platform 5111, and its output direction is adjusted. Then, a collimating lens and a cylindrical lens are placed sequentially at the laser output end. The collimating lens is used to collimate the diverging laser beam into a parallel beam. By adjusting the position and angle of the collimating lens, the divergence angle of the laser beam is reduced to a suitable level. Next, the cylindrical lens is placed, and its position and angle are adjusted to focus the collimated laser beam into a sheet of light.

[0095] In yet another alternative embodiment, the aforementioned remote measurement submodule 52 includes a base 522 and N flow rate measurement units 521.

[0096] The base 522 is a plate-shaped structure used to fix the flow velocity measuring unit 521.

[0097] The aforementioned flow velocity measurement unit 521 includes a support rod 5211 and a piezoresistive sensor 5212.

[0098] The bottom end of the aforementioned support rod 5211 is vertically fixed to the upper surface of the aforementioned base 522.

[0099] The piezoresistive sensor 5212 is fixed to the top of the support rod 5211 and is used to measure the corresponding distal center pressure sequence under the control of the trigger signal.

[0100] It should be noted that each piezoresistive sensor 5212 begins measurement after receiving a trigger signal, and measures the corresponding pressure value at fixed time intervals. The pressure values ​​of each piezoresistive sensor 5212 are arranged chronologically to obtain the corresponding remote center pressure sequence.

[0101] All of the aforementioned piezoresistive sensors 5212 are located on the aforementioned jet centerline; the aforementioned jet centerline is a horizontal ray perpendicular to the aforementioned jet orifice.

[0102] Preferably, the piezoresistive sensors 5212 are evenly distributed along the center line of the jet, and their horizontal distance from the jet holes is greater than the horizontal width of the two-dimensional planar area illuminated by the sheet light source 511.

[0103] It should be noted that the piezoresistive sensor described above can be either the CYG508 transmitting pressure sensor or the CYG503 reflecting pressure sensor, and the embodiments of the present invention are not limited thereto.

[0104] It should be noted that the N distal center pressure sequences correspond to N piezoresistive sensors 5212. Each distal center pressure sequence represents a series of pressure values ​​collected by the corresponding piezoresistive sensor 5212 over time. Furthermore, the N piezoresistive sensors 5212 synchronously begin collecting data upon receiving a trigger signal.

[0105] As can be seen, by using the remote measurement submodule 52, it is possible to avoid setting up a sensor near the jet orifice, reduce the interference of the sensor on the gas jet, and accurately obtain the pressure change of the jet field at the far end of the jet orifice.

[0106] As can be seen, by implementing the jet field measurement system for aircraft tire bursting described in the embodiments of the present invention, and by using tracer particle method and sensor measurement at the near end and far end of the jet hole respectively to obtain the near end jet video and the far end center pressure sequence set, and further analyzing to obtain the global peak velocity sequence, the accuracy reduction caused by simply using tracer particle method for far end analysis can be avoided, and the distortion caused by setting up sensors at the near end can be reduced, thereby improving the accuracy of measurement.

[0107] Example 2

[0108] Please see Figure 3 , Figure 3 This is a flowchart illustrating a jet field measurement method for aircraft tire bursting, as disclosed in an embodiment of the present invention. Figure 3 The described jet field measurement method for aircraft tire bursting is applied in the field of aircraft tire bursting tests, such as jet field measurement in aircraft tire bursting tests. This invention is not limited to specific embodiments. Figure 3 As shown, the jet field measurement method for aircraft tire bursting includes:

[0109] S1. Using the inflation module 4, high-pressure tracer gas is injected into the perforated tire 1, and a trigger signal is generated.

[0110] S2. Use the above-mentioned jet control module 3 to unseal the jet hole and form a gas jet.

[0111] S3. Using the near-end measurement submodule 51 and the far-end measurement submodule 52 of the jet measurement module 5, the gas jet is measured to obtain a near-end jet video and a far-end center pressure sequence set. Using the data analysis submodule of the jet measurement module 5, the near-end jet video and the far-end center pressure sequence set are processed to obtain a global peak velocity sequence.

[0112] In an optional embodiment, the above-described processing of the near-end jet video and the far-end center pressure sequence set to obtain a global peak velocity sequence includes:

[0113] S31. The above-mentioned near-end jet video is split into a jet image sequence; the above-mentioned jet image sequence includes several near-end jet images.

[0114] It should be noted that each of the above near-end jet images corresponds to one frame of the near-end jet video.

[0115] S32. The above jet image sequence is processed to obtain a set of proximal center velocity sequences; the above set of proximal center velocity sequences includes several proximal center velocity sequences.

[0116] It should be noted that the above-mentioned near-center velocity sequence represents jet velocity values ​​at several uniformly distributed positions along the jet centerline, and these jet velocity values ​​are arranged in order of increasing distance from the jet orifice. Furthermore, the position corresponding to each jet velocity value is located within a two-dimensional planar region illuminated by the sheet light.

[0117] S33. Process the above set of proximal center velocity sequences to obtain the proximal peak velocity sequence.

[0118] S34. Process the above set of remote center pressure sequences to obtain the remote peak velocity sequence.

[0119] S35. Perform spatial interpolation on the above-mentioned near-end peak velocity sequence and the above-mentioned far-end peak velocity sequence to obtain the global peak velocity sequence.

[0120] It should be noted that the near-end peak velocity sequence and the far-end peak velocity sequence represent the maximum gas velocity at a series of uniformly distributed positions near the jet orifice on the jet centerline, and at the piezoresistive sensor 5212 at the far end of the jet orifice, respectively. By spatially interpolating the two, the maximum gas velocity at a series of uniformly distributed positions on the entire jet centerline can be obtained.

[0121] In another optional embodiment, the above-described processing of the jet image sequence to obtain a set of proximal center velocity sequences can be achieved by calling PIVLab software, and the specific steps include:

[0122] (1) Import images into PIVlab

[0123] Launch PIVlab and load the jet image sequence using the "Load Image" function.

[0124] (2) Image preprocessing

[0125] Using PIVlab, contrast and brightness adjustments, as well as noise removal operations, were performed on each near-end jet image to enhance image quality and highlight particle features.

[0126] (3) Set analysis parameters

[0127] In PIVlab, select the region near the axis as the analysis area.

[0128] Set the window size to 64×64 pixels; this value determines the accuracy and speed of the analysis.

[0129] Set the overlap rate to 50%;

[0130] Set the time interval to the interval between adjacent frames of the near-end jet video.

[0131] (4) Run PIV analysis

[0132] Using PIVlab, the velocity field analysis results are automatically calculated for each pair of adjacent near-end jet images. Therefore, the number of velocity field analysis results is equal to the number of near-end jet images minus 1.

[0133] (5) Post-processing

[0134] PIVlab is used for vector field smoothing and outlier processing. The former reduces the impact of random errors and noise through spatial filtering techniques, while the latter removes abnormal velocity vectors, such as zero velocity vectors or excessively large velocity vectors.

[0135] (6) Export data

[0136] Using the "line selection" tool, select the jet centerline and export the velocity vectors at several locations evenly distributed along the centerline for each velocity field analysis result. Arrange the velocity vectors corresponding to each velocity field analysis result in order from closest to furthest from the jet orifice to obtain the corresponding velocity vector sequence.

[0137] The aforementioned velocity vector includes components in the two vertical directions, u and v.

[0138] Calculate the length of all velocity vectors in each velocity vector sequence to obtain the corresponding near-center velocity sequence.

[0139] In yet another optional embodiment, the above-mentioned processing of the proximal center velocity sequence set to obtain the proximal peak velocity sequence includes:

[0140] S331. Take each of the above near-center velocity sequences as row vectors and concatenate them to obtain a velocity matrix.

[0141] S332. The maximum values ​​of each column of the above velocity matrix are combined sequentially to obtain the above near-end peak velocity sequence.

[0142] In another optional embodiment, the above-mentioned processing of the distal center pressure sequence set to obtain the distal peak velocity sequence includes:

[0143] S341. Set the peak index of each piezoresistive sensor 5212 to the maximum value of the remote center pressure sequence and its sequence number in the remote center pressure sequence.

[0144] S342. Arrange all peak indices in order of distance from the corresponding piezoresistive sensor 5212 to the jet orifice from near to far to obtain the peak index sequence.

[0145] S343. Using the remote velocity estimation model, the above peak index sequence is processed to obtain the remote peak velocity sequence.

[0146] The expression for the above remote velocity estimation model is:

[0147]

[0148] In the diagram, v i ID is the i-th velocity value in the far-end peak velocity sequence. i+1 and ID i These are the (i+1)th and ith peak indices of the peak index sequence, respectively; i is an integer from 1 to M-1, and M is the length of the peak index sequence; Δd ​​is the distance between adjacent piezoresistive sensors 5212; and Δt is the sampling interval of the aforementioned piezoresistive sensors 5212.

[0149] It should be noted that the gas jet generated by the explosion passes through each piezoresistive sensor 5212 in sequence during its propagation. The above method calculates the average velocity by using the time difference of the pressure signals collected by adjacent piezoresistive sensors 5212, and uses this average velocity to estimate the peak velocity at the piezoresistive sensor 5212 that is farther away.

[0150] As can be seen, the jet field measurement method for aircraft tire bursting described in the embodiments of the present invention, by using tracer particle method and sensor measurement at the near end and far end of the jet hole respectively, to obtain near-end jet video and far-end center pressure sequence set, and further analyzing to obtain global peak velocity sequence, can avoid the decrease in accuracy caused by simply using tracer particle method for far-end analysis, reduce the distortion caused by setting up sensors at the near end, and thus improve the accuracy of measurement.

[0151] The device embodiments described above are merely illustrative. The modules described as separate components may or may not be physically separate, and the components shown as modules may or may not be physical modules; that is, they may be located in one place or distributed across multiple network modules. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0152] Through the detailed description of the above embodiments, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, including read-only memory (ROM), random access memory (RAM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), one-time programmable read-only memory (OTPROM), electrically-erasable programmable read-only memory (EEPROM), compact disc read-only memory (CD-ROM) or other optical disc storage, disk storage, magnetic tape storage, or any other computer-readable medium that can be used to carry or store data.

[0153] Finally, it should be noted that the jet field measurement system and method for aircraft tire explosion disclosed in the embodiments of the present invention are merely preferred embodiments of the present invention, and are only used to illustrate the technical solutions of the present invention, not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A jet field measurement system for aircraft tire explosion, characterized in that, Includes perforated tires, mounting brackets, jet control module, inflation module, and jet measurement module; The perforated tire is an aircraft tire with jet holes on its side; the fixing frame is used to stand the perforated tire upright and fix it to the ground. The inflation module is data-connected to the jet control module and the jet measurement module, and is airtightly connected to the inflation port of the perforated tire. It is used to inflate the perforated tire with high-pressure tracer gas and generate a trigger signal. The jet control module is fixed to the outer side of the perforated tire and is used to control the opening and closing of the jet hole according to the trigger signal to form a gas jet. The jet measurement module is used to measure the gas jet according to the trigger signal to obtain a global peak velocity sequence; the global peak velocity sequence includes several velocity values.

2. The jet field measurement system for aircraft tire bursting according to claim 1, characterized in that, The inflation module includes a particle injection unit, a high-pressure air pump, a mixing chamber, a first pipeline, a second pipeline, a third pipeline, and a control unit; The particle injection unit is electrically connected to the control unit and is used to inject tracer particles; The high-pressure air pump is electrically connected to the control unit and is used to generate high-pressure gas and measure the internal air pressure value in real time. The mixing chamber is an airtight structure with a first air inlet, a second air inlet, and an air outlet, used to mix the tracer particles and the high-pressure gas to obtain high-pressure tracer gas. The two ends of the first pipeline are airtightly connected to the air outlet and the air inlet of the perforated tire, respectively; the two ends of the second pipeline are airtightly connected to the particle injection unit and the first air inlet, respectively; the two ends of the third pipeline are airtightly connected to the high-pressure air pump and the second air inlet, respectively. The control unit is used to synchronously start the particle injection unit and the high-pressure air pump when the measurement begins, and to shut down the high-pressure air pump and generate the trigger signal when the internal air pressure value is greater than the preset working air pressure value.

3. The jet field measurement system for aircraft tire bursting according to claim 1, characterized in that, The jet control module includes a reinforcement submodule and a jet orifice opening / closing submodule; The reinforcing submodule is fixed to the outer side of the perforated tire and located above the jet hole, and is used to enhance the tire strength around the jet hole; the reinforcing submodule has a through hole corresponding to the jet hole; The jet orifice opening and closing submodule is fixed to the top of the through hole of the reinforcing submodule and is used to seal the through hole when the high-pressure tracer gas is filled into the perforated tire, and to quickly open the through hole after receiving the trigger signal.

4. The jet field measurement system for aircraft tire bursting according to claim 1, characterized in that, The jet measurement module includes a near-end measurement submodule, a far-end measurement submodule, and a data analysis submodule; The proximal measurement submodule is connected to the inflation module and the data analysis submodule, and is used to measure the proximal jet video under the control of the trigger signal. The remote measurement submodule is connected to the inflation module and the data analysis submodule, and is used to measure a set of remote center pressure sequences under the control of the trigger signal; the set of remote center pressure sequences includes N remote center pressure sequences; the remote center pressure sequence includes several pressure values; N is an integer greater than 1; The data analysis submodule is used to process the near-end jet video and the far-end center pressure sequence set to obtain the global peak velocity sequence.

5. The jet field measurement system for aircraft tire bursting according to claim 4, characterized in that, The near-end measurement submodule includes a sheet light source and a high-speed camera; The sheet light source is fixedly disposed in front of the jet hole and is data connected to the inflation module, and is used to generate sheet light after receiving the trigger signal; The high-speed camera is fixedly installed at the same height to the side of the jet orifice and is data-connected to the inflation module. It is used to capture the gas jet ejected from the jet orifice after receiving the trigger signal, so as to obtain a near-end jet video.

6. The jet field measurement system for aircraft tire bursting according to claim 5, characterized in that, The sheet light source includes a semiconductor laser, a collimating lens, and a cylindrical lens.

7. The jet field measurement system for aircraft tire bursting according to claim 4, characterized in that, The remote measurement submodule includes a base and N flow velocity measurement units; The base is a plate-shaped structure used to fix the flow velocity measurement unit; The flow velocity measurement unit includes a support rod and a piezoresistive sensor; The bottom end of the support rod is vertically fixed to the upper surface of the base; The piezoresistive sensor is fixed to the top of the support rod and is used to measure the corresponding distal center pressure sequence under the control of the trigger signal. All of the piezoresistive sensors are located on the jet centerline; the jet centerline is a horizontal ray perpendicular to the jet orifice.

8. A method for measuring the jet field in the event of aircraft tire explosion, characterized in that, The method, applied to the jet field measurement system for aircraft tire bursting as described in any one of claims 1 to 7, comprises: S1. Using the inflation module, high-pressure tracer gas is injected into the perforated tire, and a trigger signal is generated; S2. Use the jet control module to unseal the jet orifice and form a gas jet; S3. Using the jet measurement module, the gas jet is measured to obtain a set of near-end jet video and far-end center pressure sequence. The near-end jet video and the far-end center pressure sequence are then processed to obtain a global peak velocity sequence.

9. The jet field measurement method for aircraft tire bursting according to claim 8, characterized in that, The process of processing the near-end jet video and the far-end center pressure sequence set to obtain the global peak velocity sequence includes: S31. The near-end jet video is split into a jet image sequence; the jet image sequence includes several near-end jet images; S32. Process the jet image sequence to obtain a set of proximal center velocity sequences; the set of proximal center velocity sequences includes several proximal center velocity sequences; S33. Process the set of proximal center velocity sequences to obtain the proximal peak velocity sequence; S34. Process the set of remote center pressure sequences to obtain the remote peak velocity sequence; S35. Perform spatial interpolation on the near-end peak velocity sequence and the far-end peak velocity sequence to obtain the global peak velocity sequence.

10. The jet field measurement method for aircraft tire bursting according to claim 9, characterized in that, The process of processing the proximal center velocity sequence set to obtain the proximal peak velocity sequence includes: S331. Take each of the near-center velocity sequences as row vectors and concatenate them to obtain a velocity matrix; S332. The maximum values ​​of each column of the velocity matrix are combined sequentially to obtain the near-end peak velocity sequence.

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