Method and device for analyzing wind-sand erosive wear characteristics of aircraft coating

Abstract

The embodiment of the invention provides a wind-sand erosion wear characteristic analysis method and device for an aircraft coating, and the method comprises the steps: carrying out the multiple times of wind-sand erosion simulation on a test piece through a wind-sand erosion simulation device, and enabling the material of the test piece to be the same as the material of an aircraft; determining energy generated when sand grains collide with the surface of the test piece in each simulation process, and determining the number of wear layers of a coating on the surface of the test piece after each simulation is finished; and according to the energy and the number of wear layers corresponding to each simulation in the multiple wind-sand erosion simulations, establishing a relation model between the number of wear layers of the test piece surface coating and the energy generated when sand grains collide with the surface of the test piece, and determining the relation model as a wind-sand erosion wear characteristic analysis result of the aircraft coating.

Description

TECHNICAL FIELD

[0001] Embodiments of the present specification relate to the technical field of wind and sand erosion wear, and in particular to a method for analyzing wind and sand erosion wear characteristics of an aircraft coating. BACKGROUND

[0002] When an aircraft takes off or lands in a strong wind and sand area, it is subjected to long-term erosion and wear by wind and sand flow, causing damage to the aircraft coating. With the accumulation of structural fatigue damage, its performance gradually declines, and even structural failure accidents of aircraft components occur under extreme environmental loads. Therefore, studying the erosion and wear rules of aircraft coatings in strong wind and sand areas plays a positive role in ensuring the safe operation of aircrafts, and has important engineering application value and academic theoretical value. SUMMARY

[0003] Therefore, the embodiments of the present specification provide a method for analyzing wind and sand erosion wear characteristics of an aircraft coating. One or more embodiments of the present specification also relate to a device for analyzing wind and sand erosion wear characteristics of an aircraft coating, a computing device, a computer-readable storage medium, and a computer program to solve the technical defects in the prior art.

[0004] According to a first aspect of the embodiments of the present specification, a method for analyzing wind and sand erosion wear characteristics of an aircraft coating is provided, comprising: performing multiple wind and sand erosion simulations on a test piece by a wind and sand erosion simulation device, wherein the material of the test piece is the same as that of the aircraft; determining the energy generated by sand particles colliding with the surface of the test piece during each simulation, and determining the number of worn layers of the coating on the surface of the test piece after each simulation; establishing a relationship model between the number of worn layers of the coating on the surface of the test piece and the energy generated by sand particles colliding with the surface of the test piece according to the energy and the number of worn layers corresponding to each simulation in the multiple wind and sand erosion simulations, and determining the relationship model as the analysis result of the wind and sand erosion wear characteristics of the aircraft coating.

[0005] Optionally, the determination of the energy generated by sand particles colliding with the surface of the test piece during each simulation comprises: determining the total number of sand particles used in each simulation and the volume density of the sand particles; determining the initial energy generated by a single sand particle colliding with the surface of the test piece according to the mass of the single sand particle and the flight speed of the single sand particle during the simulation; determining the contact area of the test piece with the sand particles during each simulation, and determining the simulation duration of each simulation; determine the energy generated by the sand particle colliding with the surface of the test piece in each simulation process based on the total number of sand particles, the volumetric density of sand particles, the initial energy, the flight speed of the single sand particle, the contact surface area, and the simulation duration.

[0006] Optionally, the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating further comprises: determining the initial position of the single sand particle in the wind and sand erosion simulation device and determining the distance from the initial position to the surface of the test piece; determining the corresponding flight time of the single sand particle from the initial position to the surface of the test piece in the simulation process according to the distance and the pre-acquired relationship between the flight time of the sand particle and the distance from the sand particle to the surface of the test piece; determining the flight speed of the single sand particle in the simulation process according to the mass of the single sand particle, the flight time, and the simulated wind speed of the wind and sand erosion simulation device in the simulation process.

[0007] Optionally, the wind and sand erosion simulation device comprises a laser and a laser prism; Correspondingly, the method further comprises: determining the distance between the laser and the laser prism; determining the attenuation value of the laser according to the distance and the corresponding transmittance of the laser emitted by the laser passing through the sand particle in the simulation process; determining the volumetric density of sand particles in each simulation process based on the attenuation value and the average particle size of the sand particles.

[0008] Optionally, the establishing of the relationship model between the number of wear layers of the coating on the surface of the test piece and the energy generated by the sand particle colliding with the surface of the test piece in each simulation of the multiple wind and sand erosion simulations comprises: fitting the relationship between the energy and the number of wear layers corresponding to each simulation of the multiple wind and sand erosion simulations using a piecewise function to generate the fitting result corresponding to the number of wear layers of the coating on the surface of the test piece and the energy generated by the sand particle colliding with the surface of the test piece.

[0009] Optionally, the fitting of the relationship between the energy and the number of wear layers corresponding to each simulation of the multiple wind and sand erosion simulations using a piecewise function comprises: fitting the number of wear layers less than or equal to a preset threshold and the corresponding energy in the multiple wind and sand erosion simulations using a quadratic polynomial passing through the origin; fitting the number of wear layers greater than the preset threshold and the corresponding energy in the multiple wind and sand erosion simulations using a straight line passing through the origin.

[0010] Optionally, the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating further comprises: According to the geometric parameters of the sand particles in the desert region, the wind speed conditions, and the take-off and landing time and frequency of the aircraft, the impact energy of the sand particles impacting the surface of the aircraft is calculated; The impact energy is input into the relationship model, and the number of wear layers of the aircraft coating is determined according to the output result of the relationship model.

[0011] According to a second aspect of the embodiments of the present specification, a device for analyzing the wind and sand erosion wear characteristics of an aircraft coating is provided, comprising: A simulation module is configured to perform multiple wind and sand erosion simulations on a test piece by a wind and sand erosion simulation device, wherein the material of the test piece is the same as the material of the aircraft; A determination module is configured to determine the energy generated by sand particles colliding with the surface of the test piece during each simulation, and to determine the number of wear layers of the coating on the surface of the test piece after each simulation; An establishment module is configured to establish a relationship model between the number of wear layers of the coating on the surface of the test piece and the energy generated by sand particles colliding with the surface of the test piece according to the energy and the number of wear layers corresponding to each simulation in the multiple wind and sand erosion simulations, and to determine the relationship model as the analysis result of the wind and sand erosion wear characteristics of the aircraft coating.

[0012] According to a third aspect of the embodiments of the present specification, a computing device is provided, comprising: a memory and a processor; The memory is used to store computer executable instructions, and the processor is used to execute the computer executable instructions to implement the steps of any one of the methods for analyzing the wind and sand erosion wear characteristics of the aircraft coating.

[0013] According to a fourth aspect of the embodiments of the present specification, a computer readable storage medium is provided, which stores computer executable instructions, and the instructions are executed by a processor to implement the steps of any one of the methods for analyzing the wind and sand erosion wear characteristics of the aircraft coating.

[0014] According to a fifth aspect of the embodiments of the present specification, a computer program is provided, wherein when the computer program is executed in a computer, the computer is caused to execute the steps of the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating.

[0015] The embodiment of the present specification provides a method for analyzing the wind and sand erosion wear characteristics of an aircraft coating. The method comprises the following steps: performing multiple wind and sand erosion simulations on a test piece by a wind and sand erosion simulation device, wherein the material of the test piece is the same as the material of the aircraft; determining the energy generated by sand particles colliding with the surface of the test piece during each simulation, and determining the wear layers of the coating on the surface of the test piece after each simulation; establishing a relationship model between the wear layers of the coating on the surface of the test piece and the energy generated by sand particles colliding with the surface of the test piece according to the energy and the wear layers corresponding to each simulation in the multiple wind and sand erosion simulations, and determining the relationship model as the analysis result of the wind and sand erosion wear characteristics of the aircraft coating. Through this processing method, the erosion and wear of the aircraft coating under strong wind and sand can be accurately simulated, and the erosion and wear law under multiple variable conditions such as angle and wind speed can be further promoted. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 FIG. 1 is a flowchart of a method for analyzing the wind and sand erosion wear characteristics of an aircraft coating according to an embodiment of the present specification; Figure 2 FIG. 2 is a schematic diagram of a wind and sand erosion simulation device according to an embodiment of the present specification; Figure 3 FIG. 3 is a schematic diagram of the change of the mass of a test piece with the number of simulations according to an embodiment of the present specification; FIG. 4(a) is a schematic diagram of the change of the transmittance of laser passing through a sand and dust particle system with time according to an embodiment of the present specification; FIG. 4(b) is a schematic diagram of the change of the sand and dust concentration with the number of simulations according to an embodiment of the present specification; Figure 5 FIG. 5 is a schematic diagram of the change of the number of damaged layers of a test piece coating with the energy of sand particles colliding with the surface of the test piece according to an embodiment of the present specification; Figure 6 FIG. 6 is a structural schematic diagram of a device for analyzing the wind and sand erosion wear characteristics of an aircraft coating according to an embodiment of the present specification; Figure 7 FIG. 7 is a structural block diagram of a computing device according to an embodiment of the present specification. DETAILED DESCRIPTION

[0017] In the following description, many specific details are set forth in order to provide a thorough understanding of the present specification. However, the present specification can be practiced in many different ways from those described herein, and it is understood that the present specification is not limited to the embodiments described herein and that the scope of the application is defined by the appended claims.

[0018] The terminology used in this disclosure of one or more embodiments is for the purpose of describing particular embodiments only and is not intended to be limiting of one or more embodiments of the disclosure. As used in this disclosure and the appended claims, the singular forms "a," "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will also be understood that the term "and / or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

[0019] It is to be understood that the terms first, second, etc. can be employed in this disclosure of one or more embodiments to describe various information. Such information should not be limited by these terms. These terms are only used to distinguish one category of information from another category of information. For example, without departing from the scope of one or more embodiments of the disclosure, first can be termed second, and, similarly, second can be termed first. Depending on the context, the word "if' as used herein can be interpreted to mean "when" or "in response to determining."

[0020] In the present specification, a method for analyzing wind and sand erosion wear characteristics of an aircraft coating is provided, and the present specification also relates to a device for analyzing wind and sand erosion wear characteristics of an aircraft coating, a computing device, a computer-readable storage medium, and a computer program, which are described in detail one by one in the following embodiments.

[0021] Figure 1 A flowchart of a method for analyzing wind and sand erosion wear characteristics of an aircraft coating according to an embodiment of the present specification is shown, which specifically includes the following steps.

[0022] Step 102: performing multiple wind and sand erosion simulations on the test piece by the wind and sand erosion simulation device, wherein the material of the test piece is the same as the material of the aircraft.

[0023] Specifically, the embodiments of the present specification analyze the phenomenon of sand particles colliding and rubbing against the aircraft fuselage during takeoff and landing of the aircraft in a desert area. The specific analysis process studies the wind and sand erosion of the aircraft fuselage skin test piece during takeoff and landing on a typical sand source surface under a wind speed of 103-109 m / s, and gives the changes of the skin coating surface with the number of erosion times and the changes of the mass loss of the skin coating with the number of erosion times. The phenomenon of layered damage of the aircraft skin coating caused by wind and sand erosion is found, and a relationship model of the number of damaged layers of the aircraft skin during takeoff and landing of the aircraft in a sand environment is given, which is a function of the takeoff and landing time, the number of takeoff and landing, the wind speed, and the sand particle size.

[0024] A schematic diagram of a wind and sand erosion simulation device provided by the embodiments of the present specification is shown in Figure 2The figure shows. Wherein, (1) is frequency converter, (2) is fan, (3) is wind tunnel gradual reduction section, (4) is add hourglass funnel, (5) is camera, (6) is laser, (7) is laser prism, (8) is laser power meter, (9) is computer, (10) is test piece. In addition, the sand and wind erosion device also includes laser receiver and pitot tube.

[0025] In order to generate wind speed of 100 m / s or more, a small wind tunnel capable of generating high wind speed is designed by using fan, and the maximum wind speed can reach about 110 m / s; the wind speed is measured by pitot tube anemometer, the range is 0~160 m / s, and the accuracy is 0.01 m / s.

[0026] Considering the plane taking off and landing in the sand desert area, due to the strong airflow generated by the engine of the plane, a large amount of sand particles on the ground will be disturbed, and the blown sand particles will collide and rub with the plane body. In order to quantify how many sand particles contact the plane body, a laser receiver with a wavelength of 550 nm is selected to inverse the sand particle number concentration or local visibility. In addition, the surface damage of the test piece under the wind and sand erosion is recorded by using high resolution camera, the mass reduction caused by the coating falling off of the test piece surface is weighed and recorded by electronic balance (accuracy 0.01g), and the whole simulation process is recorded by using high speed camera.

[0027] Since the factors affecting the test piece skin coating are the length of the plane taking off and landing, that is, the length of the test piece being blown by sand and wind, the number of plane taking off and landing, the particle size and quantity of sand particles, and the angle between the wind direction and the test piece, and according to the fact that the typical helicopter taking off and landing time does not exceed 20s, the simulation time is fixed between 18-20s in the embodiment of the specification, which is recorded by the laser and the video recorder. The laser receiver records the signal. The fan switch is used to simulate the number of plane taking off and landing, and other conditions such as sand particle size distribution, average value of sand particle concentration, wind speed, wind direction and angle with test piece are not changed under the same working condition. The angle between the wind direction and the test piece surface is realized by adjusting the nut of the fixed test piece.

[0028] In order to ensure the safety and smooth progress of the simulation, sufficient preparation and protection measures should be taken before the simulation, such as cleaning the site (the fan power is large, in order to prevent electric leakage, the ground cannot have water, metal and other conductors), the operator wears insulating gloves and goggles (to prevent electric leakage and splashing sand particles from hurting people), covers other equipment (to prevent sand particles from splashing and falling into the equipment), etc. Then make sure to cut off the power supply, observe whether the fan, frequency converter and other equipment can be safely started, and check whether the rest of the equipment is running normally. The specific simulation steps are as follows: 1) weigh the test piece, clean the test piece surface with clean superfine fiber cloth, then slowly put it on the electronic balance and weigh it three times to get the average value, record the initial mass of the test piece, and measure the relative humidity and temperature of the site; 2) Install the test piece, install the test piece on the test piece fixing device, ensure that the blown-erosion position is appropriate, and is not loose and does not fall off; 3) Adjust the laser equipment, turn on the laser power meter and adjust to zero; turn on the laser, so that the laser beam is parallel to the surface of the test piece and is perpendicular to the center of the laser prism; turn on the computer, and after the reading of the laser power meter is stable, measure the initial power, and the measurement time must be greater than 18s (about one erosion time), and record 10 laser power data per second; 4) Weigh the sand particles, block the lower section of the sand adding funnel, and add the sand particles to the sand adding funnel; 5) Erosion simulation, turn on the total power air switch and the frequency converter air switch in turn. Turn on the high-speed camera to record the simulation process video, and run the laser power meter software to record the receiving end power data; start the fan, and when the frequency converter output frequency is 50Hz, that is, the motor reaches the rated speed, and the wind speed at the outlet section is maximum, quickly open the lower section of the sand adding funnel to release the sand particles therein. After all the sand particles in the sand adding funnel are discharged, turn off the frequency converter, turn off the camera, and stop recording the laser receiving end data; then turn off the frequency converter air switch and the total power air switch in turn; 6) Take down the test piece from the test piece fixing device, and take down the wrapping material; use a clean superfine fiber cloth to wipe the dust on the surface of the test piece; 7) Weigh the mass of the test piece after sand blowing with an electronic balance, weigh three times and take the average value, record the mass of the test piece after the simulation experiment, and take a photo with a high-resolution camera to observe the change in the surface morphology of the test sample after being blown.

[0029] The above are the specific steps of one simulation process. The intermittent simulation experiment is first carried out in the embodiment of the present specification, each group of simulation experiment has an erosion time of about 18s, and a plurality of simulation processes are repeated in this way to observe the erosion and wear of the coating.

[0030] Several aspects need to be paid attention to in the simulation process. First, the fluctuation of the laser emitter power, so a suitable laser emitter power needs to be selected, too large emitter power will cause large fluctuation error, and too small emitter power cannot clearly characterize the change process of the sand dust concentration with time; at the same time, the laser beam needs to be parallel to the surface of the test piece, and the laser emitter and receiver need to be fixed to prevent the laser equipment from being blown away from the original position. Second, the measurement of the mass of the test piece, the measurement of the mass of the test piece requires high accuracy, and the measurement value will not be accurate due to environmental disturbance, including wind speed, temperature and humidity, simulation device table vibration, etc. Therefore, when measuring the mass of the test piece, the experimental environment needs to be ensured to reach the "still" state. Third, the sand particles are not cleaned at the parts such as the fan impeller, and the fan needs to be started before the simulation to run to a stable state so that the wind speed reaches the maximum.

[0031] The weight of the test piece is weighed before and after each simulation, so the change of the weight of the test piece with the number of simulations and the weight of the test piece surface worn each time can be calculated. The schematic diagram of the change of the weight of the test piece with the number of simulations provided by the embodiment of the present specification is shown in FIG. 1. Figure 3 Figure 3 The upper half of FIG. 1 is the change of the weight of the test piece with the number of simulations, and the lower half is the decrease of the weight of the test piece after each simulation.

[0032] Step 104: determining the energy generated by the sand particles colliding with the surface of the test piece during each simulation, and determining the number of layers of the coating worn on the surface of the test piece after each simulation.

[0033] In an optional embodiment, the determination of the energy generated by the sand particles colliding with the surface of the test piece during each simulation comprises: determining the total number of sand particles used in each simulation and the volumetric density of the sand particles; determining the initial energy generated by a single sand particle colliding with the surface of the test piece according to the mass of the single sand particle and the flight speed of the single sand particle during the simulation; determining the contact area of the test piece with the sand particles during each simulation, and determining the simulation time of each simulation; determining the energy generated by the sand particles colliding with the surface of the test piece during each simulation based on the total number of sand particles, the volumetric density of the sand particles, the initial energy, the flight speed of the single sand particle, the contact area, and the simulation time.

[0034] In an optional embodiment, the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating further comprises: determining the initial position of a single sand particle in the wind and sand erosion simulation device, and determining the distance from the initial position to the surface of the test piece; determining the flight time of the single sand particle from the initial position to the surface of the test piece during the simulation according to the distance and the previously obtained relationship between the flight time of the sand particle and the distance from the sand particle to the surface of the test piece; determining the flight speed of the single sand particle during the simulation according to the mass of the single sand particle, the flight time, and the simulation wind speed of the wind and sand erosion simulation device during the simulation.

[0035] In an optional embodiment, the wind and sand erosion simulation device comprises a laser and a laser prism. Correspondingly, the method further comprises: determining the distance between the laser and the laser prism; determining the attenuation value of the laser according to the distance and the corresponding transmittance of the laser emitted by the laser passing through the sand particles during the simulation.​ Based on the attenuation value and the average particle size of the sand, the volumetric density of the sand particles in each simulation process is determined.

[0036] Specifically, based on the wear morphology of the specimen surface during the simulation, it can be inferred that the greater the number and force of impacts on the specimen surface, the greater the degree of damage to the specimen surface. Therefore, the embodiments in this specification calculate the energy of sand particles colliding with the specimen surface in each simulation, correlate it with the number of wear layers appearing on the specimen surface, establish a relationship model between different coating wear layers and the energy of sand particles colliding with the specimen surface, and provide a model of wear and damage of aircraft coatings during takeoff and landing in a sandy environment.

[0037] Because sand grains are accelerated by the wind, and the force of the wind... The calculation formula is: Formula (1) in, air density, The cross-sectional area of ​​the sand grain. The drag coefficient, This represents the velocity of the dust particles relative to the airflow.

[0038] Formula (2) in, For wind speed, This represents the velocity of the sand grains.

[0039] Assuming the Reynolds number of the airflow is small, then: Formula (3) Formula (4) in, air viscosity ( =1.5x10-5m2 / s); D is the diameter of the sand grain.

[0040] Based on this, we have: Formula (5) Neglecting the vertical velocity of the sand grains, the final velocity of the sand grains upon impact with the specimen surface is... It can be determined by the mass of sand grains The flight time t of the sand grains and the wind speed were obtained as follows: Formula (6) The relationship between the flight time of sand grains and the distance from the sand grains to the surface of the specimen is as follows: Formula (7) When x = 0.3 m, t ≈ 0.08 s. Substituting t into formula (6), we can find that the sand particle velocity is approximately 9.3387 m / s when it reaches the surface of the specimen.

[0041] Based on the kinetic energy of a single sand grain colliding with the surface of the specimen This allows us to estimate the kinetic energy of sand grains in n simulated collisions. as follows: Formula (8) Formula (9) Where S is the contact area between the specimen and the sand grains, and T is the duration of each simulation. The mass of a single grain of sand, This refers to the density of sand particles.

[0042] In addition, as mentioned above, there are a large number of sand particles in contact with the specimen. In this embodiment of the specification, the attenuation value of the laser is measured by the transmittance T(t) of a 550nm laser (emission power 6 mW) through the sand particle system. The specific expression is as follows: Formula (10) Where L is the distance between the sand and dust, which is the distance between the laser and the laser prism. In this embodiment, L = 0.15m.

[0043] Furthermore, the volumetric density of dust (Dimensions, units / m) 3 The relationship between the average grain size R (dimension m) and the average grain size of sand is as follows: Formula (11) Figure 4(a) shows a schematic diagram of the change in the transmittance of the laser through the dust particle system over time during the simulation, and Figure 4(b) shows a schematic diagram of the change in dust concentration over the number of simulations.

[0044] The relevant experimental parameters used in the simulation process in the embodiments of this specification are shown in Table 1.

[0045] Table 1 Experimental parameters

[0046] Step 106: Based on the energy and wear layer number corresponding to each simulation in the multiple sand erosion simulations, establish a relationship model between the wear layer number of the coating on the specimen surface and the energy generated by sand particles colliding with the specimen surface, and determine the relationship model as the analysis result of the sand erosion wear characteristics of the aircraft coating.

[0047] In one optional implementation, the step of establishing a relationship model between the number of wear layers of the coating on the specimen surface and the energy generated by sand particles colliding with the specimen surface, based on the energy and the number of wear layers corresponding to each simulation in the multiple sand erosion simulations, includes: A piecewise function is used to fit the relationship between the energy and the number of wear layers in each simulation of multiple wind and sand erosion simulations, generating fitting results corresponding to the number of wear layers of the coating on the specimen surface and the energy generated by sand particles colliding with the specimen surface.

[0048] In one optional implementation, the step of fitting the relationship between the energy and the number of wear layers corresponding to each simulation in the multiple wind and sand erosion simulations using a piecewise function includes: A quadratic polynomial passing through the origin is used to fit the number of wear layers less than or equal to a preset threshold and their corresponding energy in the multiple wind and sand erosion simulations. A straight line passing through the origin is used to fit the number of wear layers exceeding a preset threshold and their corresponding energy in the multiple wind and sand erosion simulations.

[0049] Specifically, after determining the relevant experimental parameters used in the simulation experiment, the cumulative energy of sand particles on the surface of the impacted specimen can be estimated with the number of simulations. This energy can then be correlated with the observed number of coating failure layers. A schematic diagram illustrating the change in the number of coating failure layers as a function of the impacted sand particle energy on the specimen surface, provided in this specification, is shown below. Figure 5 As shown, in the previous simulations, the surface coating morphology of the specimen changed significantly, and the surface coating was quickly destroyed, requiring relatively low sand impact energy. The coating deeper than the surface was more difficult to destroy, requiring higher sand impact energy, exhibiting a segmented trend. Therefore, this specification's embodiments, considering the relationship between the number of destroyed layers and erosion energy, employ a segmented approach to fit the number of destroyed coating layers to the impact energy.

[0050] like Figure 5 As shown, in the first six simulations, i.e. the erosion damage range of the surface layer and the first yellow layer, a quadratic polynomial passing through the origin was used for fitting. The fitting curve, formula, and correlation coefficient are shown in red in the figure. Subsequently, when the first yellow layer was damaged and the second gray layer began to be eroded and worn, a straight line passing through the origin was used for fitting. The fitting curve, formula, and correlation coefficient are shown in blue in the figure. Based on the fitting results, the relationship model of the number of damaged layers of the coating under the action of wind and sand can be obtained.

[0051] The wind and sand erosion wear characteristic analysis model of the aircraft coating in the embodiments of this specification is as follows: Formula (12) In an optional embodiment, the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating further includes: According to the geometric parameters of sand particles in the desert region, the wind speed condition, and the take-off and landing time and frequency of the aircraft, the impact energy of the sand particles impacting the surface of the aircraft is calculated; The impact energy is input into the relationship model, and the number of worn layers of the coating of the aircraft is determined according to the output result of the relationship model.

[0052] Specifically, according to the geometric parameters of sand particles in the desert region, the wind speed condition, and the take-off and landing time and frequency of the aircraft, the energy of the sand particles impacting the surface of the aircraft can be estimated by using formula (8), and then the formula (12) can be used to estimate the number of times the coating of the surface of the aircraft can be damaged.

[0053] The method for analyzing the wind and sand erosion wear characteristics of the coating of the aircraft provided by one embodiment of the present specification comprises the following steps:

[0054] Corresponding to the method embodiment described above, the present specification also provides an apparatus for analyzing the wind and sand erosion wear characteristics of the coating of the aircraft, Figure 6 A structural schematic diagram of an apparatus for analyzing the wind and sand erosion wear characteristics of the coating of the aircraft provided by one embodiment of the present specification is shown. Figure 6 As shown in the figure, the apparatus comprises: The simulation module 602 is configured to perform multiple wind and sand erosion simulations on a test piece by using a wind and sand erosion simulation device, wherein the material of the test piece is the same as that of the aircraft; The determination module 604 is configured to determine the energy generated by the sand particles impacting the surface of the test piece in each simulation process, and determine the number of worn layers of the coating of the surface of the test piece after each simulation ends; The establishing module 606 is configured to establish a relationship model between the number of wear layers of the surface coating of the test piece and the energy generated by the sand particles colliding with the surface of the test piece according to the energy and the number of wear layers in each simulation of the multiple sand and wind erosion simulations, and determine the relationship model as the wind and sand erosion wear characteristic analysis result of the aircraft coating.

[0055] Optionally, the determining module 604 is further configured to: determine the total number of sand particles and the volume density of the sand particles used in each simulation process; determine the initial energy generated by a single sand particle colliding with the surface of the test piece according to the mass of the single sand particle and the flight speed of the single sand particle in the simulation process; determine the contact surface area of the test piece and the sand particles in each simulation process, and determine the simulation time length of each simulation; determine the energy generated by the sand particles colliding with the surface of the test piece in each simulation process based on the total number of sand particles, the volume density of the sand particles, the initial energy, the flight speed of the single sand particle, the contact surface area, and the simulation time length.

[0056] Optionally, the determining module 604 is further configured to: determine the initial position of a single sand particle in the wind and sand erosion simulation device and the distance from the initial position to the surface of the test piece; determine the flight time of the single sand particle from the initial position to the surface of the test piece in the simulation process according to the distance and the relationship between the flight time of the sand particle and the distance from the sand particle to the surface of the test piece obtained in advance; determine the flight speed of the single sand particle in the simulation process according to the mass of the single sand particle, the flight time, and the simulation wind speed of the wind and sand erosion simulation device in the simulation process.

[0057] Optionally, the wind and sand erosion simulation device comprises a laser and a laser prism. Correspondingly, the device further comprises a processing module configured to: determine the distance between the laser and the laser prism; determine the attenuation value of the laser according to the distance and the transmittance of the laser emitted by the laser passing through the sand particles in the simulation process; determine the volume density of the sand particles in each simulation process based on the attenuation value and the average particle size of the sand particles.

[0058] Optionally, the establishing module 606 is further configured to: The relationship between the energy and the number of wear layers corresponding to each simulation in the multiple sand and wind erosion simulation is fitted by using a piecewise function to generate the fitting result of the number of wear layers of the surface coating of the test piece and the energy generated by the sand particle impacting the surface of the test piece.

[0059] Optionally, the establishing module 606 is further configured to: The number of wear layers less than or equal to a preset threshold and the corresponding energy in the multiple sand and wind erosion simulation are fitted by using a quadratic polynomial passing through the origin. The number of wear layers greater than a preset threshold and the corresponding energy in the multiple sand and wind erosion simulation are fitted by using a straight line passing through the origin.

[0060] Optionally, the processing module is further configured to: According to the geometric parameters of the sand particles in the desert area, the wind speed condition, and the take-off and landing time and frequency of the aircraft, the impact energy of the sand particles impacting the surface of the aircraft is calculated; The impact energy is input into the relationship model, and the number of wear layers of the coating of the aircraft is determined according to the output result of the relationship model.

[0061] The above is a schematic scheme of the aircraft coating sand and wind erosion wear characteristic analysis device of the embodiment. It should be noted that the technical scheme of the aircraft coating sand and wind erosion wear characteristic analysis device belongs to the same concept as the technical scheme of the aircraft coating sand and wind erosion wear characteristic analysis method described above. The technical scheme of the aircraft coating sand and wind erosion wear characteristic analysis device is not described in detail, and the details can be referred to the description of the technical scheme of the aircraft coating sand and wind erosion wear characteristic analysis method.

[0062] Figure 7 A structural block diagram of a computing device 700 according to one embodiment of the present specification is shown. The components of the computing device 700 include but are not limited to a memory 710 and a processor 720. The processor 720 is connected to the memory 710 through a bus 730, and a database 750 is used to save data.

[0063] The computing device 700 also includes an access device 740 that enables the computing device 700 to communicate via one or more networks 760. Examples of such networks include a public switched telephone network (PSTN), a local area network (LAN), a wide area network (WAN), a personal area network (PAN), or combinations of such networks, such as the Internet. The access device 740 can include one or more of any type of network interface (for example, a network interface card (NIC)), such as an IEEE 802.11 wireless local area network (WLAN) wireless interface, a global system for mobile communications (GSM) interface, a code division multiple access (CDMA) interface, a Bluetooth interface, a near field communication (NFC) interface, a universal serial bus (USB) interface, a Wi-Fi® interface, a Wi-MAX interface, an Ethernet interface, or the like.

[0064] In one embodiment of the present specification, the above-mentioned components of the computing device 700 and other components not shown in the above-mentioned components of the computing device 700 can be connected to each other, for example, through a bus. It should be understood that Figure 7 Figure 7 The computing device structure diagram shown is merely for the purpose of example, and is not a limitation on the scope of the present specification. Other components can be added or replaced as needed by those skilled in the art.

[0065] The computing device 700 can be any type of stationary or mobile computing device, including a mobile computer or mobile computing device (for example, a tablet computer, a personal digital assistant, a laptop computer, a notebook computer, a netbook, and the like), a mobile phone (for example, a smartphone), a wearable computing device (for example, a smart watch, smart glasses, and the like), or other types of mobile devices, or a stationary computing device such as a desktop computer or a PC. The computing device 700 can also be a mobile or stationary server.

[0066] The processor 720 is configured to execute computer-executable instructions, which, when executed by the processor, implement the steps of the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating.

[0067] The above is a schematic scheme of a computing device according to the present embodiment. It should be noted that the technical scheme of the computing device belongs to the same concept as the technical scheme of the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating, and the details of the technical scheme of the computing device that are not described in detail can be referred to the description of the technical scheme of the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating.

[0068] The present embodiment of the present specification also provides a computer-readable storage medium storing computer-executable instructions, which, when executed by a processor, implement the steps of the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating.

[0069] ​The above is a schematic scheme of the computer readable storage medium of the embodiment. It should be noted that the technical scheme of the storage medium and the technical scheme of the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating belong to the same concept, and the details of the technical scheme of the storage medium that are not described in detail can be seen from the description of the technical scheme of the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating.

[0070] An embodiment of the present specification also provides a computer program, wherein the computer program causes the computer to execute the steps of the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating when the computer program is executed in the computer.

[0071] The above is a schematic scheme of the computer program of the embodiment. It should be noted that the technical scheme of the computer program and the technical scheme of the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating belong to the same concept, and the details of the technical scheme of the computer program that are not described in detail can be seen from the description of the technical scheme of the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating.

[0072] The above describes specific embodiments of the present specification. Other embodiments are within the scope of the appended claims. In some cases, the acts or steps recited in the claims can be performed in a different order than the order in which they are recited and still achieve desirable results. In addition, the processes depicted in the figures do not necessarily require the particular order shown, or sequential order to achieve the desired results. In certain implementations, multitasking and parallel processing can be advantageous.

[0073] The computer readable medium can include any entity or device capable of carrying the computer program code, recording medium, U disk, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signal, telecommunication signal, and software distribution medium, etc. It should be noted that the contents included in the computer readable medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction, for example, in some jurisdictions, according to legislation and patent practice, the computer readable medium does not include electrical carrier signals and telecommunication signals.

[0074] It should be noted that, for the aforementioned method embodiments, the sequences of the described actions are not necessarily required to implement the present application, and certain actions can be performed in other sequences, or even at the same time, in accordance with the present application. Furthermore, certain actions can not be required to implement the present application. Additionally, the described embodiments are not necessarily the only possible implementation of the present application.

[0075] In the above embodiments, the description of each embodiment focuses on different aspects, and the parts not described in detail in a certain embodiment can be referred to the relevant description of other embodiments.

[0076] The preferred embodiments of the present application disclosed above are only used to clarify the present application. The alternative embodiments do not describe all the details and limit the present application to the specific embodiments described. Obviously, according to the content of the present application, many modifications and changes can be made. The present application selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present application, so that those skilled in the art can well understand and use the present application. The present application is limited by the claims and their full scope and equivalents.

Claims

1. A method for analyzing the wind and sand erosion wear characteristics of aircraft coatings, comprising: The specimen was subjected to multiple sand erosion simulations using a sand erosion simulation device, wherein the material of the specimen was the same as that of the aircraft. Determine the energy generated by sand particles colliding with the surface of the specimen during each simulation, and determine the number of wear layers of the coating on the surface of the specimen after each simulation; Based on the energy and wear layer number corresponding to each simulation in the multiple sand erosion simulations, a relationship model is established between the wear layer number of the coating on the specimen surface and the energy generated by sand particles colliding with the specimen surface, and the relationship model is determined as the analysis result of the sand erosion wear characteristics of the aircraft coating.

2. The method for analyzing the wind and sand erosion wear characteristics of aircraft coatings according to claim 1, wherein determining the energy generated by sand particles colliding with the surface of the specimen during each simulation includes: Determine the total number of sand grains used in each simulation process and the sand grain volume density; The initial energy generated by the collision of a single sand grain with the surface of the specimen is determined based on the mass of a single sand grain and the flight speed of the single sand grain during the simulation. Determine the contact area between the specimen and the sand grains during each simulation, and determine the simulation duration for each simulation. Based on the total number of sand grains, the volumetric density of the sand grains, the initial energy, the flight speed of a single sand grain, the contact area, and the simulation duration, the energy generated by the sand grains colliding with the surface of the specimen during each simulation is determined.

3. The method for analyzing the wind and sand erosion wear characteristics of aircraft coatings according to claim 2 further includes: Determine the initial position of a single sand grain in the wind and sand erosion simulation device, and determine the distance from the initial position to the surface of the specimen; Based on the distance and the relationship between the pre-obtained sand grain flight time and the distance from the sand grain to the specimen surface, the flight time of a single sand grain from the starting position to the specimen surface during the simulation is determined. The flight speed of the individual sand grain during the simulation is determined based on the mass of the individual sand grain, the flight time, and the simulated wind speed of the wind and sand erosion simulation device during the simulation.

4. The method for analyzing the wind and sand erosion wear characteristics of aircraft coatings according to claim 2, wherein the wind and sand erosion simulation device includes a laser and a laser prism; Accordingly, the method further includes: Determine the distance between the laser and the laser prism; The laser attenuation value is determined based on the distance and the transmittance of the laser emitted by the laser through the sand grains during the simulation. Based on the attenuation value and the average particle size of the sand, the volumetric density of the sand particles in each simulation process is determined.

5. The method for analyzing the wind and sand erosion wear characteristics of aircraft coatings according to claim 1, wherein establishing a relationship model between the number of wear layers of the coating on the specimen surface and the energy generated by sand particles colliding with the specimen surface based on the energy and the number of wear layers corresponding to each simulation in the multiple wind and sand erosion simulations, includes: A piecewise function is used to fit the relationship between the energy and the number of wear layers in each simulation of multiple wind and sand erosion simulations, generating fitting results corresponding to the number of wear layers of the coating on the specimen surface and the energy generated by sand particles colliding with the specimen surface.

6. The method for analyzing the wind and sand erosion wear characteristics of aircraft coatings according to claim 5, wherein the step of fitting the relationship between the energy and the number of wear layers corresponding to each simulation in the multiple wind and sand erosion simulations using a piecewise function includes: A quadratic polynomial passing through the origin is used to fit the number of wear layers less than or equal to a preset threshold and their corresponding energy in the multiple wind and sand erosion simulations. A straight line passing through the origin is used to fit the number of wear layers exceeding a preset threshold and their corresponding energy in the multiple wind and sand erosion simulations.

7. The method for analyzing the wind and sand erosion wear characteristics of aircraft coatings according to claim 1, further comprising: Based on the geometric parameters of sand grains in desert areas, wind speed conditions, and the duration and number of takeoffs and landings of aircraft, the impact energy corresponding to sand grains impacting the surface of an aircraft is calculated. The impact energy is input into the relational model, and the number of wear layers of the aircraft coating is determined based on the output of the relational model.

8. An analysis device for the wind and sand erosion wear characteristics of aircraft coatings, comprising: The simulation module is configured to perform multiple sand erosion simulations on the specimen using a sand erosion simulation device, wherein the material of the specimen is the same as that of the aircraft. The determination module is configured to determine the energy generated by sand particles colliding with the surface of the specimen during each simulation, and to determine the number of wear layers of the coating on the surface of the specimen after each simulation. The module is configured to establish a relationship model between the number of wear layers of the coating on the specimen surface and the energy generated by sand particles colliding with the specimen surface, based on the energy and the number of wear layers corresponding to each simulation in the multiple sand erosion simulations, and to determine the relationship model as the analysis result of the sand erosion wear characteristics of the aircraft coating.

9. A computing device, comprising: Memory and processor; The memory is used to store computer-executable instructions, and the processor is used to execute the computer-executable instructions. When the computer-executable instructions are executed by the processor, they implement the steps of the method for analyzing the wind and sand erosion wear characteristics of the aircraft coating as described in any one of claims 1 to 7.

10. A computer-readable storage medium storing computer-executable instructions that, when executed by a processor, implement the steps of the method for analyzing the wind and sand erosion wear characteristics of an aircraft coating as described in any one of claims 1 to 7.

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