CN114527123B - Method, equipment and medium for identifying damage position of solid propellant - Google Patents
Method, equipment and medium for identifying damage position of solid propellant Download PDFInfo
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
- G01N21/84—Systems specially adapted for particular applications
- G01N21/88—Investigating the presence of flaws or contamination
- G01N21/8851—Scan or image signal processing specially adapted therefor, e.g. for scan signal adjustment, for detecting different kinds of defects, for compensating for structures, markings, edges
- G01N2021/8887—Scan or image signal processing specially adapted therefor, e.g. for scan signal adjustment, for detecting different kinds of defects, for compensating for structures, markings, edges based on image processing techniques
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Abstract
The embodiment of the application discloses a method, equipment and medium for identifying damage positions of a solid propellant. Compressing the solid propellant sample; wherein, the surface of the solid propellant sample is prepared with uniform speckles; the method comprises the steps of performing initial speckle image acquisition on a solid propellant sample through an image acquisition device, and performing deformation speckle image acquisition on the solid propellant in compression processing; determining a first image subarea in the acquired initial speckle image, and determining a first center point coordinate according to the first image subarea; determining a second image subarea which accords with the preset similarity value condition corresponding to the first image subarea in the acquired deformed speckle image, and determining a second center point coordinate according to the second image subarea; and identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate. By the method, the identification efficiency of the damaged position of the solid propellant is improved.
Description
Technical Field
The application relates to the technical field of aerospace power, in particular to a method, equipment and medium for identifying damage positions of a solid propellant.
Background
Composite solid propellant materials are very high inclusion ratio particle reinforced composite materials, typically formed by bonding two or more metal fuel particles, oxidizer particles with a resin binder, and typically have a packing ratio approaching or exceeding 90%. Under the extremely severe transportation, storage and launching load conditions experienced by solid rocket engines, solid propellant materials are extremely susceptible to microscopic damage, thereby inducing macroscopic fracture. Therefore, in the product development period, the mechanical property of the system needs to be ground, comprehensive mechanical property parameters are obtained at the material level, the damage limit and main damage form of the propellant material under various working conditions are obtained, and further the integrity of the system is evaluated on a large grain structure, so that the reliable operation of the solid engine under various extremely harsh task profiles is ensured.
At present, a microscopic observation means is generally used for identifying damage to the solid propellant, a microscopic mechanical experiment is relatively complex, and the microscopic mechanical experiment is difficult to be associated with the loading process of macroscopic solid propellant, so that the identification process of the damage position of the solid propellant is complicated, and the damage position of the solid propellant is difficult to be identified efficiently.
Disclosure of Invention
The embodiment of the application provides a method, equipment and medium for identifying the damage position of a solid propellant, which are used for solving the following technical problems: the mesomechanics experiment is difficult to efficiently identify the damage of the solid propellant.
The embodiment of the application adopts the following technical scheme:
The embodiment of the application provides a method for identifying a damage position of a solid propellant. The method comprises the steps of compressing a solid propellant sample through a solid propellant sample loading device; wherein, the surface of the solid propellant sample is prepared with uniform speckles; the method comprises the steps of performing initial speckle image acquisition on a solid propellant sample through an image acquisition device, and performing deformation speckle image acquisition on the solid propellant sample in compression processing; determining a first image subarea in the acquired initial speckle image, and determining a first center point coordinate according to the first image subarea; the first image subarea is any subarea image in the initial speckle image; determining a second image subarea which accords with the preset similarity value condition corresponding to the first image subarea in the acquired deformed speckle image, and determining a second center point coordinate according to the second image subarea; and identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate.
According to the embodiment of the application, the initial speckle image acquisition is carried out on the solid propellant sample, and the first image subarea is determined according to the acquired initial speckle image, so that the second image subarea which is most similar to the first image subarea is determined in the deformed speckle image according to the first image subarea. And thus, the deformed speckle images acquired at different times are matched to determine the displacement changes of the pixel points in the same area corresponding to the different times. And determining the damage position of the solid propellant according to the displacement change of the pixel points. According to the embodiment of the application, the damage position can be obtained through image change, and the complex process of determining the damage position through a mesomechanics experiment is abandoned, so that the efficiency of identifying the loss position is improved.
In one implementation manner of the present application, in the acquired deformed speckle image, a second image subarea which meets a preset similarity value condition corresponding to the first image subarea is determined, and the method specifically includes: determining an image size of the first image subregion; determining a plurality of reference subregions of the same image size as the first image subregion in the anamorphic speckle image; obtaining similar values between the first image subarea and a plurality of reference subareas respectively through a preset least square distance correlation function so as to determine a second image subarea in the plurality of reference subareas according to the similar values and a preset similar value condition; wherein the second image subregion is a subregion image in the anamorphic speckle image.
According to the embodiment of the application, the image size of the reference subarea is determined through the size of the first image subarea. And determining a second image subarea in a plurality of reference subareas according to a preset least square distance correlation function, so that the accuracy of image subarea matching is ensured through the image size and a preset function, and the accuracy of identifying the damage position of the solid propellant is further ensured.
In one implementation manner of the present application, obtaining similarity values between the first image subregion and the plurality of reference subregions respectively by presetting a least squares distance correlation function specifically includes: determining a gray value of each pixel point of the first image subarea, and respectively determining a first difference value between the gray values of each pixel point of the first image subarea and the average gray value corresponding to the first image subarea; determining a gray value of each pixel point of the reference subarea, and respectively determining a second difference value between the gray value and the average gray value corresponding to the reference subarea; and obtaining similar values between the first image subarea and a plurality of reference subareas respectively based on the first difference value, the second difference value and a preset least square distance correlation function.
In one implementation of the present application, after determining the second center point coordinate corresponding to the second image subregion, the method further includes: determining the displacement strain state of the solid propellant corresponding to the second image subarea through the rigid body change state of the solid propellant corresponding to the second center point coordinate and a preset shape function; the rigid body change state at least comprises one of rigid body displacement, rigid body rotation, shearing and expansion deformation.
In one implementation manner of the present application, the displacement strain state of the solid propellant corresponding to the second image subarea is determined by the rigid body change state of the solid propellant corresponding to the second center point coordinate and the preset shape function, and specifically includes: under the condition that the solid propellant corresponding to the second center point coordinate only generates rigid displacement, determining a displacement strain state corresponding to the second image subarea through a zero-order shape function; or under the condition that the solid propellant corresponding to the second center point coordinate rotates, shears and stretches out and draws back to deform, determining a displacement strain state corresponding to the solid propellant in the second image subarea through a first-order function; or under the condition that the solid propellant corresponding to the second center point coordinate is coupled, determining a displacement strain state corresponding to the solid propellant in the second image subarea through a second order function.
According to the embodiment of the application, the displacement strain state corresponding to the second image subarea is determined through shape functions of different orders according to different rigid body change states corresponding to the second center point coordinates. When the deformation of the object surface is relatively complex, the deformation of the sub-zones is not a linear deformation. As the size and displacement gradient of the image sub-region increase, the possibility that the displacement field in the image sub-region remains linear decreases, so that non-uniform deformation of the sub-region needs to be considered, and the complex deformation is described more accurately by increasing the second-order displacement gradient, so that the displacement and strain of the object surface under the complex deformation condition can be measured more accurately.
In one implementation of the present application, identifying a damaged position of a solid propellant sample according to a first center point coordinate and a second center point coordinate specifically includes: determining a displacement component of the second center point according to the first center point coordinate and the second center point coordinate; according to the time sequence, the displacement components of a plurality of second center points corresponding to the deformation speckle images at different moments are obtained, and the damage positions of the solid propellant sample are identified according to the displacement components of the second center points.
In one implementation of the present application, identifying a damaged position of the solid propellant sample according to displacement components of the plurality of second center points specifically includes: according to the displacement components of the second center points, determining pixel point displacement distribution corresponding to the speckle image; if the pixel position displacement distribution is discontinuously changed, the solid propellant sample is damaged, so that the damage position information of the solid propellant sample is determined according to the position information of the pixel position displacement distribution.
In one implementation of the present application, determining damage location information of a solid propellant sample according to location information of pixel location distribution specifically includes: according to the position information of pixel position displacement distribution, a displacement cloud picture corresponding to a speckle deformation process is established; and determining the position information of the speckle tearing position according to the displacement cloud picture, and taking the position information of the speckle tearing position as the damage position information of the solid propellant sample.
The embodiment of the application provides a device for identifying the damage position of a solid propellant, which comprises the following components: at least one processor; and a memory communicatively coupled to the at least one processor; wherein the memory stores instructions executable by the at least one processor, the instructions being executable by the at least one processor to enable the at least one processor to: compressing a solid propellant sample by a solid propellant sample loading device; wherein, the surface of the solid propellant sample is prepared with uniform speckles; the method comprises the steps of performing initial speckle image acquisition on a solid propellant sample through an image acquisition device, and performing deformation speckle image acquisition on the solid propellant sample in compression processing; determining a first image subarea in the acquired initial speckle image, and determining a first center point coordinate according to the first image subarea; the first image subarea is any subarea image in the initial speckle image; determining a second image subarea which accords with the preset similarity value condition corresponding to the first image subarea in the acquired deformed speckle image, and determining a second center point coordinate according to the second image subarea; and identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate.
The non-volatile computer storage medium provided by the embodiment of the application stores computer executable instructions, and the computer executable instructions are set as follows: compressing a solid propellant sample by a solid propellant sample loading device; wherein, the surface of the solid propellant sample is prepared with uniform speckles; the method comprises the steps of performing initial speckle image acquisition on a solid propellant sample through an image acquisition device, and performing deformation speckle image acquisition on the solid propellant sample in compression processing; determining a first image subarea in the acquired initial speckle image, and determining a first center point coordinate according to the first image subarea; the first image subarea is any subarea image in the initial speckle image; determining a second image subarea which accords with the preset similarity value condition corresponding to the first image subarea in the acquired deformed speckle image, and determining a second center point coordinate according to the second image subarea; and identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate.
The above at least one technical scheme adopted by the embodiment of the application can achieve the following beneficial effects: according to the embodiment of the application, the initial speckle image acquisition is carried out on the solid propellant sample, the first image subarea is determined according to the acquired initial speckle image, and the second image subarea which is most similar to the first image subarea in the deformed speckle image can be determined according to the first image subarea. And thus, the deformed speckle images acquired at different times are matched to determine the displacement changes of the pixel points in the same area corresponding to the different times. And determining the damage position of the solid propellant according to the displacement change of the pixel points. According to the embodiment of the application, the damage position can be obtained through image change, and the complex process of determining the damage position through a mesomechanics experiment is abandoned, so that the efficiency of identifying the loss position is improved.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art. In the drawings:
FIG. 1 is a flow chart of a method for identifying damage positions of a solid propellant, which is provided by an embodiment of the application;
FIG. 2 is a schematic diagram of a non-contact optical measurement platform according to an embodiment of the present application;
FIG. 3 is a schematic diagram of an in-situ observation compression experimental device for a solid propellant test piece provided by an embodiment of the application;
FIG. 4 is a displacement cloud image corresponding to an image of a solid propellant sample according to an embodiment of the present application;
fig. 5 is a schematic structural diagram of a device for identifying a damaged position of a solid propellant according to an embodiment of the present application.
Detailed Description
The embodiment of the application provides a method, equipment and medium for identifying damage positions of a solid propellant.
In order to make the technical solution of the present application better understood by those skilled in the art, the technical solution of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are only some embodiments of the present application, not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, shall fall within the scope of the present application.
At present, most solid propellant researches use a microscopic observation means to combine experimental data of a macroscopic mechanical experiment to identify a damage mode of the solid propellant, the microscopic mechanical experiment is relatively complex, and the microscopic mechanical experiment means cannot be directly connected with a macroscopic loading process, so that the damage mode of the solid propellant is difficult to identify and characterize, and therefore the damage position of the solid propellant is difficult to identify efficiently.
In order to solve the problems, the embodiment of the application provides a method, equipment and medium for identifying the damage position of a solid propellant. The method comprises the steps of carrying out initial speckle image acquisition on a solid propellant sample, and determining a first image subarea according to the acquired initial speckle image, so that a second image subarea which is most similar to the first image subarea in a deformed speckle image is determined through the first image subarea. And thus, the deformed speckle images acquired at different times are matched to determine the displacement changes of the pixel points in the same area corresponding to the different times. And determining the damage position of the solid propellant according to the displacement change of the pixel points. According to the embodiment of the application, the damage position can be obtained through image change, and the complex process of determining the damage position through a mesomechanics experiment is abandoned, so that the efficiency of identifying the loss position is improved.
The following describes the technical scheme provided by the embodiment of the application in detail through the attached drawings.
Fig. 1 is a schematic diagram of a non-contact optical measurement platform according to an embodiment of the present application. As shown in fig. 1, the non-contact optical measurement platform includes a control computer, a sample, a high-precision camera, and a light supplement lamp.
In one embodiment of the application, the random, uniform speckle pattern is produced on the surface of the sample from Gao Wenya gloss resistant paint. The control computer is connected with the high-precision video camera, and camera control software is installed in the computer and used for controlling various parameters of the camera during shooting to meet various requirements of experiments and storing experimental images obtained through shooting. The camera control software is matched with the high-precision camera, can adjust parameters such as camera exposure time, shooting interval and the like, and is used for synchronous shooting and shooting trigger control of a plurality of cameras. The high-precision camera is provided with a plurality of lenses with different focal lengths, and can be suitable for shooting in various experimental environments. The light supplementing lamp is a direct-current power supply lamp without a stroboscopic effect and is used for shooting light supplementing under the condition of weak illumination, so that the acquired experimental images are clear in contrast.
In one embodiment of the application, a solid propellant test piece loading device comprises: the universal material testing machine, the experiment control computer and the temperature control box.
Specifically, the universal material testing machine is used for loading the solid propellant test piece. And the experiment control computer is connected with the universal material testing machine and used for controlling the loading mode, parameters and the like of the testing machine. The temperature control box is used for preserving the heat of the solid propellant test piece and providing the required experimental temperature.
Fig. 2 is a flowchart of a method for identifying a damaged position of a solid propellant, according to an embodiment of the present application, where, as shown in fig. 2, the method for identifying a damaged position of a solid propellant includes the following steps:
s101, the solid propellant test piece loading device compresses a solid propellant test piece.
In one embodiment of the application, a random and uniform speckle pattern is prepared on the surface of a solid propellant sample by adopting high-temperature resistant paint spraying, so that the subsequent digital image correlation technology is convenient to track the deformation field of the sample. In order to ensure the preparation quality of the speckles, spraying is sprayed above the sample, and the random uniform speckles are formed when paint spray falls on the surface of the sample. And secondly, uniformly smearing liquid Vaseline or solid graphite powder between the sample piece and the clamp of the tester, thereby reducing the friction force between the solid propellant sample piece and the clamp.
Further, the universal material testing machine is pre-adjusted to enable the machine to reach a stable working state, the zero point of the recorder is adjusted, the force measuring system is calibrated, the loading speed is selected, and the recording paper speed is selected. And secondly, adjusting a temperature control system of the temperature control box, and carrying out experiments after the test piece is kept at a constant temperature for at least 1 hour. Placing a solid propellant test piece to enable the test piece to coincide with the central axis of the clamp of the testing machine so as to prevent the test piece from being distorted and deformed caused by off-axis loading.
Further, the optical measurement platform system is adjusted so that the camera lens is in high agreement with the solid propellant sample, and the lens screen is parallel to the loading plane. The light supplementing system is adjusted so that the speckles can be clearly collected. Parameters such as shooting focal length, sampling interval and the like are adjusted to be matched with the experimental loading rate. Starting a solid propellant test piece loading device, compressing a current solid propellant test piece through a universal material testing machine in the solid propellant test piece loading device, and enabling the solid propellant test piece to deform through compression.
S102, the image acquisition device acquires an initial speckle image of the solid propellant sample and acquires a deformed speckle image of the solid propellant in compression.
In one embodiment of the application, an initial speckle image acquisition is performed on a solid propellant sample by a camera. That is, the solid propellant sample is photographed before it is subjected to the compression process, resulting in an initial speckle image. In the compression processing process of the solid propellant sample, the solid propellant sample is subjected to image acquisition through camera intervals so as to obtain deformation speckle images of the solid propellant sample changing along with time.
S103, the processor determines a first image subarea in the acquired initial speckle image, and determines a first center point coordinate according to the first image subarea.
In one embodiment of the application, a first image subregion is determined by a processor in the acquired initial speckle image, wherein the first image subregion is any one of the initial speckle images. And determining a first center point coordinate corresponding to the first image subarea through the coordinate point set of the first image subarea.
Specifically, the displacement of each point on the surface of the measured object is obtained by matching corresponding image subareas in the digital speckle diagrams before and after deformation. Before the image matching process, in order to search for the most similar template for matching, a correlation function needs to be predefined, and the correlation functions commonly used at present are a cross correlation (Cross correlation, CC) function and a least squares distance (Sum-Squared difference, SSD) function. The Zero-mean normalized least squares distance (Zero-mean normalized sum of squared difference, ZNSSD) correlation function and the parameterized least squares distance (PARAMETRIC SUM OF SQUARED DIFFERENCE, PSSD) correlation function are currently two most preferred correlation functions, considering the interference resistance and accuracy of the various correlation functions.
Further, a square of (2m+1) x (2m+1) pixel size is taken as the first image subregion in the initial speckle image, and the center point (x 0,y0) of the first image subregion is determined. And matching the first image subarea with the deformed speckle image by taking the first image subarea as a template.
S104, the processor determines a second image subarea which meets the preset similarity value condition corresponding to the first image subarea in the acquired deformed speckle image, and determines a second center point coordinate according to the second image subarea.
In one embodiment of the application, a second image subregion is determined by the processor in the acquired anamorphic speckle image, wherein the second image subregion is any one of the subregion images in the initial speckle image. And determining a second center point coordinate corresponding to the first image subarea through the coordinate point set of the second image subarea.
In one embodiment of the application, the image size of the first image subregion is determined. In the anamorphic speckle image, a plurality of reference subregions of the same image size as the first image subregion are determined. Obtaining similar values between the first image subarea and the plurality of reference subareas respectively through a preset least square distance correlation function, so as to determine a second image subarea in the plurality of reference subareas according to the similar values and a preset similar value condition.
Specifically, a plurality of reference subregions (2m+1) x (2m+1) are determined in the anamorphic speckle image according to the size (2m+1) x (2m+1) of the first image subregion. And calculating the similarity value between the first image subarea and a plurality of reference subareas respectively through a preset least square distance correlation function, and taking the reference subarea with the largest similarity value as a second image subarea.
In one embodiment of the application, a first difference between the gray value of each pixel point of the first image subregion and the average gray value corresponding to the first image subregion, respectively, is determined. And determining a gray value of each pixel point of the reference subarea, and a second difference value between the gray value and the average gray value corresponding to the reference subarea respectively. And obtaining similar values between the first image subarea and a plurality of reference subareas respectively based on the first difference value, the second difference value and a preset least square distance correlation function.
Specifically, by presetting a least squares distance correlation function
And calculating similar values between the first image subarea and the plurality of reference subareas respectively. And searching in the deformed image by taking a preset least square distance correlation function as a judgment basis to find an image subarea with the maximum similarity value with the image subarea before deformation. Wherein f (x, y) is the gray value of the (x, y) pixel point of the first image subregion, and g (x, y) is the gray value of the (x, y) pixel point of the reference subregion.For the average gray value corresponding to the first image subregion,/>Is the average gray value corresponding to the reference subregion.
And S105, the processor identifies the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate.
In one embodiment of the present application, the displacement strain state of the solid propellant corresponding to the second image sub-region is determined by the rigid body change state of the solid propellant corresponding to the second center point coordinate and the preset shape function. The rigid body change state at least comprises one of rigid body displacement, rigid body rotation, shearing and expansion deformation.
In one embodiment of the present application, in the case that only rigid displacement of the solid propellant occurs corresponding to the second center point coordinates, the displacement strain state corresponding to the second image subregion is determined by a zero order shape function. Or under the condition that the solid propellant corresponding to the second center point coordinate rotates, shears and stretches, the displacement strain state corresponding to the solid propellant in the second image subarea is determined through a one-step function. Or under the condition that the solid propellant corresponding to the second center point coordinate is coupled, determining a displacement strain state corresponding to the solid propellant in the second image subarea through a second order function.
Specifically, by a function of
A displacement variation relation between the first image subregion and the second image subregion is obtained. Wherein x and y are pixels corresponding to the first image subregion, x 'and y' are pixels corresponding to the second image subregion,And the parameter vector is a pending parameter vector and is used for reflecting the change state of the second central coordinate point.
If the solid propellant corresponding to the target subarea only generates rigid displacement, the shape function is zero order:
Wherein u and v are displacement components in the x and y directions corresponding to the second center point, respectively.
If the solid propellant corresponding to the target subarea also generates rigid rotation, shearing, expansion deformation and the like, the shape function is first order:
Wherein u xΔx+uyΔy is deformation values of rigid body rotation, shearing, expansion and contraction in the x direction corresponding to the second center point; v xΔx+vyΔy is the deformation value of the rigid body rotation, shearing, expansion and contraction in the y direction corresponding to the second center point.
When the deformation of the object surface is relatively complex, the deformation of the sub-zones is not a linear deformation. As the size and displacement gradient of the image sub-region increase, the possibility that the displacement field in the image sub-region remains linear decreases, so that the non-uniform deformation of the sub-region needs to be considered, and the second-order displacement gradient needs to be increased to describe the complex deformation more accurately, so that the displacement and strain of the object surface under the complex deformation condition can be measured more accurately. The expression of the second order form function is as follows:
Wherein u xxΔx2+uxyΔxΔy+uyyΔy2 is the expression of the displacement and strain of the second center point in the x direction by the second order displacement gradient; v xxΔx2+vxyΔxΔy+vyyΔy2 is an expression of displacement and strain of the second center point in the y-direction by a second order displacement gradient.
In one embodiment of the application, the displacement component of the second center point is determined from the first center point coordinates and the second center point coordinates. According to the time sequence, the displacement components of a plurality of second center points corresponding to the deformation speckle images at different moments are obtained, and the damage positions of the solid propellant sample are identified according to the displacement components of the second center points.
Specifically, the obtained deformed speckle images are respectively matched with the initial speckle images, so that a plurality of second image subareas corresponding to the first image subareas can be obtained. And according to the first images determined at the same time, determining a plurality of second image subareas corresponding to the time, so as to obtain a speckle displacement field corresponding to the time, and according to the time sequence of shooting deformed speckle images by a camera, arranging the obtained second image subareas, so as to obtain full-field displacement distribution corresponding to the speckle change process.
In one embodiment of the present application, a pixel displacement distribution corresponding to the speckle image is determined according to the displacement components of the plurality of second center points. If the pixel position displacement distribution is discontinuously changed, the solid propellant sample is damaged, so that the damage position information of the solid propellant sample is determined according to the position information of the pixel position displacement distribution.
Specifically, according to the position information of pixel position displacement distribution, a displacement cloud image corresponding to a speckle deformation process is established. And determining the position information of the speckle tearing position according to the displacement cloud picture, and taking the position information of the speckle tearing position as the damage position information of the solid propellant sample.
Further, when the solid propellant sample is not damaged, the displacement field of the sample should be continuously changed due to the continuity of full-field displacement. When damage and destruction occur, the speckles on the surface of the solid propellant sample are torn, and the displacement field is subjected to discontinuous displacement change. And identifying and recording discontinuous positions of the displacement field to obtain positions where damage occurs. And after the analysis of the whole experiment loading process is finished, obtaining the evolution rule of the damage failure mode of the solid propellant sample.
In one embodiment of the present application, a method for identifying damage to a solid propellant will be further described by taking a cylindrical compressed sample as an example. And random and uniform speckle patterns are prepared on the surface of the cylindrical compressed sample by adopting high-temperature-resistant paint spraying, so that the deformation field of the sample can be tracked by the subsequent digital image correlation technology. In order to ensure the preparation quality of the speckles, spraying is carried out to the upper part of the sample, and the paint spray falls on the surface of the cylindrical compressed sample to form random uniform speckles. And secondly, uniformly smearing liquid Vaseline or solid graphite powder between the cylindrical compression test piece and the flat plate clamp, so that the friction force between the test piece and the clamp is effectively reduced.
Further, the universal material testing machine is pre-adjusted to be in a compression experimental mode and achieve a stable working state, the zero point of the recorder is adjusted, the force measuring system is calibrated, the loading speed is selected, and the recording paper speed is selected. And (3) adjusting a temperature control system of the temperature control box, and carrying out experiments after the test piece is kept at a constant temperature for at least 1 hour. Placing the test piece, enabling the center axes of the test piece and the compression flat clamp to coincide, and preventing the test piece from being distorted and deformed due to compression loading off-axis.
Further, the optical measurement platform system is adjusted so that the camera lens is consistent with the height of the test piece, and the lens screen is parallel to the loading plane. The light supplementing system is adjusted so that the speckles can be clearly collected. Parameters such as shooting focal length, sampling interval and the like are adjusted to be matched with the experimental loading rate.
Further, a shooting and sampling system is started, a universal material testing machine is started to conduct testing, and data are collected through a camera device. Record and save experimental image data, testing machine data and the like. And carrying out post-treatment on the series of experimental images obtained by sampling to obtain a displacement cloud picture and the like in the deformation process. And analyzing the test data, and calculating displacement distribution of the whole field of the solid propellant test piece, wherein when no damage occurs, the displacement field of the test piece is continuously changed due to the continuity of the whole field displacement. When damage occurs, the speckles on the surface of the test piece are torn, the displacement field is subjected to discontinuous displacement change, and the discontinuous position of the recorded displacement field is identified as the damaged position. And after the analysis of the whole experiment loading process is finished, obtaining the evolution rule of the damage failure mode of the test piece.
Fig. 3 is a schematic diagram of an in-situ observation compression experimental device for a solid propellant test piece according to an embodiment of the present application. As shown in fig. 3, the solid propellant sample was subjected to compression treatment by a universal material tester in the direction indicated by the arrow in fig. 3. And adjusting the camera to the same height as the sample, shooting the sample, and obtaining a displacement cloud picture of the corresponding speckle deformation process through the shot speckle image.
Fig. 4 is a displacement cloud image corresponding to an image of a solid propellant sample according to an embodiment of the present application. As shown in fig. 4, the areas at points a and B in the figure are areas where the speckle pattern has a tearing state. This area is the location where the solid propellant sample is damaged.
Fig. 5 is a schematic structural diagram of a device for identifying damage to a solid propellant according to an embodiment of the present application. As shown in fig. 5, the solid propellant damage recognition apparatus includes:
At least one processor; and
A memory communicatively coupled to the at least one processor; wherein,
The memory stores instructions executable by the at least one processor to enable the at least one processor to:
compressing a solid propellant sample by a solid propellant sample loading device; wherein, the surface of the solid propellant sample is provided with uniform speckles;
The method comprises the steps of carrying out initial speckle image acquisition on the solid propellant sample through an image acquisition device, and carrying out deformation speckle image acquisition on the solid propellant in compression processing;
Determining a first image subarea in the acquired initial speckle image, and determining a first center point coordinate according to the first image subarea; wherein the first image subregion is any one of the initial speckle images;
determining a second image subarea which accords with a preset similarity value condition corresponding to the first image subarea in the acquired deformed speckle image, and determining a second center point coordinate according to the second image subarea;
and identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate.
Embodiments of the present application also include a non-volatile computer storage medium storing computer-executable instructions configured to:
compressing a solid propellant sample by a solid propellant sample loading device; wherein, the surface of the solid propellant sample is provided with uniform speckles;
The method comprises the steps of carrying out initial speckle image acquisition on the solid propellant sample through an image acquisition device, and carrying out deformation speckle image acquisition on the solid propellant in compression processing;
Determining a first image subarea in the acquired initial speckle image, and determining a first center point coordinate according to the first image subarea; wherein the first image subregion is any one of the initial speckle images;
determining a second image subarea which accords with a preset similarity value condition corresponding to the first image subarea in the acquired deformed speckle image, and determining a second center point coordinate according to the second image subarea;
and identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate.
The embodiments of the present application are described in a progressive manner, and the same and similar parts of the embodiments are all referred to each other, and each embodiment is mainly described in the differences from the other embodiments. In particular, for apparatus, devices, non-volatile computer storage medium embodiments, the description is relatively simple, as it is substantially similar to method embodiments, with reference to the section of the method embodiments being relevant.
The foregoing describes certain embodiments of the present application. Other embodiments are within the scope of the following claims. In some cases, the actions or steps recited in the claims can be performed in a different order than in the embodiments and still achieve desirable results. In addition, the processes depicted in the accompanying figures do not necessarily require the particular order shown, or sequential order, to achieve desirable results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.
The foregoing is merely exemplary of the present application and is not intended to limit the present application. Various modifications and changes may be made to the embodiments of the application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the embodiments of the present application should be included in the scope of the claims of the present application.
Claims (8)
1. A method of identifying a location of a solid propellant lesion, the method comprising:
compressing a solid propellant sample by a solid propellant sample loading device; wherein, the surface of the solid propellant sample is provided with uniform speckles;
The method comprises the steps of performing initial speckle image acquisition on the solid propellant sample through an image acquisition device, and performing deformation speckle image acquisition on the solid propellant sample in compression processing;
Determining a first image subarea in the acquired initial speckle image, and determining a first center point coordinate according to the first image subarea; wherein the first image subregion is any one of the initial speckle images;
determining a second image subarea which accords with a preset similarity value condition corresponding to the first image subarea in the acquired deformed speckle image, and determining a second center point coordinate according to the second image subarea;
Identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate;
Identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate, specifically including:
Determining a displacement component corresponding to a second center point according to the first center point coordinate and the second center point coordinate;
According to the time sequence, obtaining displacement components of a plurality of second center points corresponding to the deformation speckle images at different moments respectively, and identifying the damage position of the solid propellant sample according to the displacement components of the second center points;
The identifying the damaged position of the solid propellant sample according to the displacement components of the plurality of second center points specifically comprises:
According to the displacement components of the second center points, determining pixel point displacement distribution corresponding to the speckle images;
If the pixel point displacement distribution is discontinuously changed, the solid propellant sample is damaged, so that damage position information of the solid propellant sample is determined according to the position information of the pixel point displacement distribution.
2. The method for identifying a damaged position of a solid propellant according to claim 1, wherein the determining, in the acquired deformed speckle image, a second image subregion that meets a preset similarity value condition corresponding to the first image subregion specifically comprises:
determining an image size of the first image subregion;
Determining a plurality of reference subregions of the same image size as the first image subregion in the anamorphic speckle image;
Obtaining similar values between the first image subarea and the plurality of reference subareas respectively through a preset least square distance correlation function, so as to determine the second image subarea in the plurality of reference subareas according to the similar values and the preset similar value conditions; wherein the second image subregion is a subregion image in the anamorphic speckle image.
3. The method for identifying the damaged position of the solid propellant according to claim 2, wherein the obtaining the similarity value between the first image subarea and the plurality of reference subareas through a preset least square distance correlation function specifically comprises:
Determining a gray value of each pixel point of the first image subarea, and respectively determining a first difference value between the gray value and the average gray value corresponding to the first image subarea; and
Determining a gray value of each pixel point of the reference subarea, and respectively determining a second difference value between the gray value and the average gray value corresponding to the reference subarea;
And obtaining similar values between the first image subarea and the plurality of reference subareas respectively based on the first difference value, the second difference value and the preset least square distance correlation function.
4. The method of claim 1, wherein after determining the second center point coordinates corresponding to the second image sub-region, the method further comprises:
Determining the displacement strain state of the solid propellant corresponding to the second image subarea through the rigid body change state of the solid propellant corresponding to the second center point coordinate and a preset shape function;
the rigid body change state at least comprises one of rigid body displacement, rigid body rotation, shearing and telescopic deformation.
5. The method for identifying a damaged position of a solid propellant according to claim 4, wherein determining the displacement strain state of the solid propellant corresponding to the second image sub-region by using the rigid body change state of the solid propellant corresponding to the second center point coordinate and the preset shape function specifically comprises:
Under the condition that the solid propellant corresponding to the second center point coordinate only generates rigid displacement, determining a displacement strain state corresponding to the second image subarea through a zero-order shape function; or alternatively
Under the condition that the solid propellant corresponding to the second center point coordinate rotates, shears and stretches out and draws back to deform, determining a displacement strain state corresponding to the solid propellant in the second image subarea through a first-order function; or alternatively
And under the condition that the solid propellant corresponding to the second center point coordinate is coupled, determining a displacement strain state corresponding to the solid propellant in the second image subarea through a second order function.
6. The method for identifying the damaged position of the solid propellant according to claim 1, wherein the determining damaged position information of the solid propellant sample according to the position information of the pixel point displacement distribution specifically comprises:
according to the position information of the pixel point displacement distribution, a displacement cloud picture corresponding to the speckle deformation process is established;
And determining the position information of the speckle tearing position according to the displacement cloud picture, and taking the position information of the speckle tearing position as the damage position information of the solid propellant sample.
7. A solid propellant damage location identification apparatus comprising:
At least one processor; and
A memory communicatively coupled to the at least one processor; wherein,
The memory stores instructions executable by the at least one processor to enable the at least one processor to:
compressing a solid propellant sample by a solid propellant sample loading device; wherein, the surface of the solid propellant sample is provided with uniform speckles;
The method comprises the steps of performing initial speckle image acquisition on the solid propellant sample through an image acquisition device, and performing deformation speckle image acquisition on the solid propellant sample in compression processing;
Determining a first image subarea in the acquired initial speckle image, and determining a first center point coordinate according to the first image subarea; wherein the first image subregion is any one of the initial speckle images;
determining a second image subarea which accords with a preset similarity value condition corresponding to the first image subarea in the acquired deformed speckle image, and determining a second center point coordinate according to the second image subarea;
Identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate;
Identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate, specifically including:
Determining a displacement component corresponding to a second center point according to the first center point coordinate and the second center point coordinate;
According to the time sequence, obtaining displacement components of a plurality of second center points corresponding to the deformation speckle images at different moments respectively, and identifying the damage position of the solid propellant sample according to the displacement components of the second center points;
The identifying the damaged position of the solid propellant sample according to the displacement components of the plurality of second center points specifically comprises:
According to the displacement components of the second center points, determining pixel point displacement distribution corresponding to the speckle images;
If the pixel point displacement distribution is discontinuously changed, the solid propellant sample is damaged, so that damage position information of the solid propellant sample is determined according to the position information of the pixel point displacement distribution.
8. A non-volatile computer storage medium storing computer-executable instructions, the computer
The executable instructions are configured to:
compressing a solid propellant sample by a solid propellant sample loading device; wherein, the surface of the solid propellant sample is provided with uniform speckles;
The method comprises the steps of performing initial speckle image acquisition on the solid propellant sample through an image acquisition device, and performing deformation speckle image acquisition on the solid propellant sample in compression processing;
Determining a first image subarea in the acquired initial speckle image, and determining a first center point coordinate according to the first image subarea; wherein the first image subregion is any one of the initial speckle images;
determining a second image subarea which accords with a preset similarity value condition corresponding to the first image subarea in the acquired deformed speckle image, and determining a second center point coordinate according to the second image subarea;
Identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate;
Identifying the damage position of the solid propellant sample according to the first center point coordinate and the second center point coordinate, specifically including:
Determining a displacement component corresponding to a second center point according to the first center point coordinate and the second center point coordinate;
According to the time sequence, obtaining displacement components of a plurality of second center points corresponding to the deformation speckle images at different moments respectively, and identifying the damage position of the solid propellant sample according to the displacement components of the second center points;
The identifying the damaged position of the solid propellant sample according to the displacement components of the plurality of second center points specifically comprises:
According to the displacement components of the second center points, determining pixel point displacement distribution corresponding to the speckle images;
If the pixel point displacement distribution is discontinuously changed, the solid propellant sample is damaged, so that damage position information of the solid propellant sample is determined according to the position information of the pixel point displacement distribution.
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