CN117174216A - Laminated composite thermal response analysis method, electronic device, and readable storage medium - Google Patents
Laminated composite thermal response analysis method, electronic device, and readable storage medium Download PDFInfo
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Abstract
The application relates to a laminated composite thermal response analysis method, an electronic device and a readable storage medium, wherein the method comprises the following steps: determining heat source parameters and boundary conditions according to the heated heat source of the composite material; calculating the material temperature and decomposition degree of different to-be-detected points in the composite material at different moments according to the original parameters, the heat source parameters, the boundary conditions and a pre-constructed composite material thermal response model of the composite material; wherein the original parameters are data collected when the composite material undergoes a pyrolysis reaction; and analyzing the obtained temperature and decomposition degree of the material to obtain the damage condition of the composite material. The thermal response analysis method provided by the application aims at the three-dimensional anisotropic laminated composite structure, can analyze the temperature and the pyrolysis distribution of each part of the heated radiation composite structure, and solves the problem that the three-dimensional laminated composite structure with multilayer attribute cannot be analyzed in the prior art.
Description
Technical Field
The present application relates to the field of thermal analysis of materials, and in particular to a method for thermal response analysis of a laminated composite material, an electronic device and a readable storage medium.
Background
The laminated composite material structure is a widely used dual-purpose important structure for military and civil, and is often contacted with heat radiation load in the application process, for example, under the impact of a laser weapon, the heat radiation load can cause the problems of temperature rise, pyrolysis damage and the like of the composite material structure in aerospace equipment. Therefore, the construction of the thermal response analysis scheme of the three-dimensional laminated composite material structure under the heat radiation load has important significance for rapidly evaluating the damage degree of the structure, guiding the design of the heat radiation resistance of the structure and the like.
In the prior art, a heat transfer theoretical model is an important means for analyzing the thermal response of a material, but the prior heat transfer theoretical model does not consider the influence of pyrolysis of a composite material and gas generated by the pyrolysis on the temperature of the composite material; in addition, the laminated composite material structure is composed of a plurality of layers of fiber reinforced composite materials, and each layer of material has different directions and complex anisotropic material properties, so that the thermal radiation response is the result of heat conduction, thermal decomposition, gas flow and other factors, but the current analysis and evaluation method of the radiation damage of the composite material structure is a one-dimensional model, and the evaluation of temperature and damage only comprises the thickness direction, so that the method cannot be applied to the three-dimensional laminated composite material structure with the plurality of layers of properties and cannot analyze complex heat load conditions.
Disclosure of Invention
The embodiment of the application provides a thermal response analysis method for a laminated composite material, electronic equipment and a readable storage medium, which at least solve the problem that the prior art cannot analyze the thermal load condition of a three-dimensional laminated composite material structure with multilayer properties.
In a first aspect, embodiments of the present application provide a method for analyzing thermal response of a three-dimensional laminated composite material, comprising:
determining heat source parameters and boundary conditions according to the heated heat source of the composite material;
calculating the material temperature and decomposition degree of different to-be-detected points in the composite material at different moments according to the original parameters, the heat source parameters, the boundary conditions and a pre-constructed composite material thermal response model of the composite material; wherein the original parameters are data collected when the composite material undergoes a pyrolysis reaction;
and analyzing the obtained temperature and decomposition degree of the material to obtain the damage condition of the composite material.
In one embodiment, the construction of the composite thermal response model includes:
calculating the real-time density of the composite material according to the real-time temperature of the composite material;
determining the mass of the decomposition gas produced by pyrolysis of the composite material based on the real-time density;
obtaining the specific heat capacity and the thermal conductivity of the composite material according to the real-time temperature of the composite material;
and constructing the thermal response model of the composite material according to the real-time density, the mass, the specific heat capacity and the thermal conductivity of the decomposed gas.
In one embodiment, the composite thermal response model is:wherein,real-time density of the composite material; c (C) P The specific heat capacity of the composite material at the current moment; t is the real-time temperature of the composite material; t is the pyrolysis time of the composite material heated radiation; k (k) x 、k y 、k z Thermal conductivities of the composite material in x, y and z directions respectively;the mass of the decomposition gas generated when the composite material is pyrolyzed; c (C) pg Specific heat capacity for a decomposition gas generated when the composite material is pyrolyzed; q (Q) dec Is the heat generated when the composite material is pyrolyzed; h and h g The enthalpy change of the composite material and the enthalpy change of the decomposed gas are respectively.
In an embodiment, the calculating the material temperature and the decomposition degree of different points to be measured in the composite material at different moments according to the original parameters, the heat source parameters, the boundary conditions and the pre-constructed thermal response model of the composite material includes:
inputting the original parameters and the heat source parameters into the composite material thermal response model to obtain the change relation of the composite material temperature along with the pyrolysis time;
acquiring coordinates of the point to be detected, acquiring material temperature of the coordinates at the last moment according to the change relation, and calculating the decomposition degree of the composite material at the current moment according to the material temperature;
and calculating the decomposition degree of all the points to be tested of the composite material at the next moment according to the preset step length updating time until the boundary condition is met.
In an embodiment, the calculating the decomposition degree of the composite material at the current moment according to the material temperature includes:
calculating the current time density of the composite material according to the material temperature;
and calculating the initial density, the decomposition density and the current time density of the composite material to obtain the decomposition degree.
In an embodiment, the method further comprises:
obtaining a layering mode of each layer of material of the composite material, and extracting a corresponding model differential format according to the layering mode;
and carrying out format conversion treatment on the composite material thermal response model according to the model differential format, and calculating the material temperature and the decomposition degree through the composite material thermal response model after the format conversion treatment.
In one embodiment, the real-time density of the composite material is calculated by the following formula:
the mass calculation formula of the decomposed gas is as follows:wherein,an initial density of the composite material;the decomposition density of the composite material is completely decomposed after the composite material is damaged by heat radiation; n is the reaction progression of the composite material; a is a pre-finger factor of the composite material; e is the decomposition activation energy of the composite material; r is the dissociation gas constant.
In one embodiment, the specific heat capacity and thermal conductivity of the composite material are obtained from the real-time temperature of the composite material; the calculation process comprises the following steps:
wherein k (T) is the thermal conductivity of the composite material as a function of temperature; k (k) v (T) is the initial thermal conductivity of the composite material as a function of temperature; k (k) c (T) is the thermal conductivity as a function of temperature of the composite material that is completely decomposed after being damaged by thermal radiation; c (T) is the specific heat capacity of the composite material along with the change of temperature; c (C) v (T) is the initial specific heat capacity of the composite material as a function of temperature; c (C) c (T) is the temperature-dependent specific heat capacity of the composite material that is fully decomposed after being damaged by thermal radiation; f is the degree of decomposition of the composite material.
In one embodiment, the composite thermal response model includes boundary conditions; wherein the boundary conditions are as follows:wherein,andthe temperature change rate of the heating surface and the temperature change rate of the back surface of the composite material are respectively;a heat flux density for heat radiation to which the composite material is subjected;refractive index of the composite material；Is a stefin-boltzmann constant; h is a front And h back The convection heat exchange coefficient of the heating surface of the composite material and the convection heat exchange coefficient of the back surface are respectively; t (T) s 、T back 、T ∞ The temperature of the material of the heating surface of the composite material, the temperature of the material of the back surface of the composite material and the ambient temperature are respectively.
In one embodiment, format conversion processing is performed on the composite thermal response model according to the model differential format; wherein,
when the layering angle of the layering mode isOr (b)When the formula of the thermal response model of the composite material is converted into:
when the layering angle of the layering mode isWhen the formula of the thermal response model of the composite material is converted into:
wherein, p and p+1 are marked on the formula to respectively represent the material temperature at the current moment and the next moment; subscripts m, n, q represent x, y, z coordinate points of the spatial position where the differential point is located, respectively.
In one embodiment, the heat source parameters include: the heat source radius, the heat flux density and the heat flux action time of the composite material heated heat source; the raw parameters include dimensional parameters, thermophysical parameters, reaction parameters, and environmental parameters of the composite material.
In a second aspect, embodiments of the present application provide a computer device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing the method of thermal response analysis of a laminated composite material as described in the first aspect when the computer program is executed by the processor.
In a third aspect, embodiments of the present application provide a computer readable storage medium having stored thereon a computer program which when executed by a processor implements a method of thermal response analysis of a laminated composite material as described in the first aspect above.
The thermal response analysis method of the laminated composite material, the electronic equipment and the readable storage medium provided by the embodiment of the application have at least the following technical effects:
determining heat source parameters and boundary conditions by a heated heat source according to the composite material; calculating the material temperature and decomposition degree of different to-be-detected points in the composite material at different moments according to the original parameters, the heat source parameters, the boundary conditions and a pre-constructed composite material thermal response model of the composite material; wherein the original parameters are data collected when the composite material undergoes a pyrolysis reaction; the obtained material temperature and decomposition degree are analyzed to obtain the damage condition of the composite material, and the problem that the three-dimensional laminated composite material structure with the multilayer attribute cannot be analyzed in the prior art is solved. Compared with the traditional heat transfer model, the method considers the influence of material pyrolysis and gas escape of the composite material structure subjected to heat radiation on the temperature of the composite material structure, and can analyze the temperature distribution and pyrolysis depth of the composite material structure in detail. In addition, the thermal response analysis method provided by the application aims at the three-dimensional anisotropic laminated composite structure, and the temperature and the pyrolysis distribution of each part of the composite structure subjected to heated radiation can be analyzed by the method.
The details of one or more embodiments of the application are set forth in the accompanying drawings and the description below to provide a more thorough understanding of the other features, objects, and advantages of the application.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application and do not constitute a limitation on the application. In the drawings:
FIG. 1 is a flow chart of a method of thermal response analysis of a three-dimensional laminate composite according to an embodiment of the present application;
FIG. 2 is a flow chart for solving a composite thermal response model in an embodiment of the application;
FIG. 3 is a temperature cloud of the composite material at 0.5 mm, 1.5 mm, 2.5 mm, respectively, heated radiation in an embodiment of the present application;
FIG. 4 is a graph of degree of decomposition versus time for a sample center at 0.1 mm for a composite in accordance with one embodiment of the present application;
fig. 5 is a block diagram of an electronic device according to an embodiment of the application.
Detailed Description
The present application will be described and illustrated with reference to the accompanying drawings and examples in order to make the objects, technical solutions and advantages of the present application more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the application. All other embodiments, which can be made by a person of ordinary skill in the art based on the embodiments provided by the present application without making any inventive effort, are intended to fall within the scope of the present application.
It is apparent that the drawings in the following description are only some examples or embodiments of the present application, and it is possible for those of ordinary skill in the art to apply the present application to other similar situations according to these drawings without inventive effort. Moreover, it should be appreciated that while such a development effort might be complex and lengthy, it would nevertheless be a routine undertaking of design, fabrication, or manufacture for those of ordinary skill having the benefit of this disclosure, and thus should not be construed as having the benefit of this disclosure.
Reference in the specification to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the application. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. It is to be expressly and implicitly understood by those of ordinary skill in the art that the described embodiments of the application can be combined with other embodiments without conflict.
Unless defined otherwise, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "a," "an," "the," and similar referents in the context of the application are not to be construed as limiting the quantity, but rather as singular or plural. The terms "comprising," "including," "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, article, or apparatus that comprises a list of steps or modules (elements) is not limited to only those steps or elements but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus. The terms "connected," "coupled," and the like in connection with the present application are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. The term "plurality" as used herein means two or more. "and/or" describes an association relationship of an association object, meaning that there may be three relationships, e.g., "a and/or B" may mean: a exists alone, A and B exist together, and B exists alone. The character "/" generally indicates that the context-dependent object is an "or" relationship. The terms "first," "second," "third," and the like, as used herein, are merely distinguishing between similar objects and not representing a particular ordering of objects.
In order to solve the problem that the prior art cannot predict the thermal response of a three-dimensional laminated composite material structure under the heat radiation load, the application provides a thermal response analysis method of the three-dimensional laminated composite material, which is based on the theory of object heat transfer, and establishes a three-dimensional numerical analysis method considering anisotropy, heat conduction, pyrolysis, gas flow and multilayer superposition in consideration of the thermal response analysis method of the three-dimensional laminated composite material structure (hereinafter referred to as composite material) under the heat radiation load, referring to fig. 1, the thermal response analysis method of an embodiment of the application comprises the following steps.
And S1, determining heat source parameters and boundary conditions according to the heated heat source of the composite material. Specifically, in this embodiment, heated heat source parameters are determined according to service conditions of the composite structure, that is, under different application scenarios, heat sources contacted by the composite material are different, and after the heated heat sources are determined, the heat source parameters are obtained, where the heat source parameters include a heat source radius, a heat flux density and a heat flux acting time. In this embodiment, the heat flux density generated by the heat source to the composite structure varies with time, and as the temperature of the composite varies with time, the heat flux density can be considered to vary with temperature. The boundary condition of the present embodiment is thus obtained as shown in formula (1): （1）
wherein,andthe temperature change rate of the heating surface and the temperature change rate of the back surface of the composite material are respectively;a heat flux density for heat radiation to which the composite material is subjected;a refractive index of the composite material;is a stefin-boltzmann constant; h is a front And h back The convection heat transfer coefficient and the back of the heated surface of the composite material respectivelyA convective heat transfer coefficient; t (T) s 、T back 、T ∞ The temperature of the material of the heating surface of the composite material, the temperature of the material of the back surface of the composite material and the ambient temperature are respectively.
The above-described calculation formula of the boundary condition is applicable to a case where the heat source radius is not within the heat source radius, and the change rate is set to a certain value (for example, zero).
Step S2, calculating the material temperature and decomposition degree of different points to be detected in the composite material at different moments according to the original parameters, heat source parameters, boundary conditions and a pre-constructed composite material thermal response model of the composite material; the original parameters are data acquired when the composite material is subjected to pyrolysis reaction, and the original parameters comprise size parameters, thermophysical parameters, reaction parameters and environmental parameters of the composite material. More specifically, dimensional parameters generally include material thickness, material width, material length of the composite material; reaction parameters generally include material decomposition activation energy, reaction progression, pre-finger factor; the thermophysical parameters generally include the convective heat transfer coefficient, the refractive index of the material, the heat of decomposition of the material, the initial density, the decomposed density, the initial specific heat capacity, the decomposed specific heat capacity, the specific heat capacity of the decomposed gas generated by pyrolysis, the initial thermal conductivity of the composite in the (x, y, z) three directions, and the decomposed thermal conductivity.
After the original parameters are obtained, a composite thermal response model can be constructed according to the original parameters. In this embodiment, the real-time density of the composite material needs to be calculated according to the real-time temperature of the composite material, that is, the relationship between the temperature and the density of the composite material is constructed, and the density of the composite material changes along with the change of the temperature; determining the mass of the decomposed gas generated by pyrolysis of the composite material according to the real-time density; the specific heat capacity and the thermal conductivity of the composite material are obtained according to the real-time temperature of the composite material, namely, the relation between the specific heat capacity and the thermal conductivity and the temperature is constructed; and finally, constructing the thermal response model of the composite material according to the real-time density, the mass, the specific heat capacity and the thermal conductivity of the decomposed gas.
In particular, composite thermal response models such as the maleFormula (2): （2）
wherein,real-time density of the composite material; c (C) P The specific heat capacity of the composite material at the current moment; t is the real-time temperature of the composite material; t is the pyrolysis time of the composite material heated radiation; k (k) x 、k y 、k z Thermal conductivities of the composite material in x, y and z directions respectively;the mass of the decomposition gas generated when the composite material is pyrolyzed; c (C) pg Specific heat capacity for a decomposition gas generated when the composite material is pyrolyzed; q (Q) dec Is the heat generated when the composite material is pyrolyzed; h and h g The enthalpy change of the composite material and the enthalpy change of the decomposed gas are respectively.
In the embodiment, the change of the mass of the material along with the change of time is predicted by adopting an Arrhenius equation, and the mass change equation is shown in a formula (3): （3）
the mass calculation formula of the decomposed gas is shown as formula (4): （4）
wherein,an initial density of the composite material;the decomposition density of the composite material is completely decomposed after the composite material is damaged by heat radiation; n is the reaction progression of the composite material; a is a pre-finger factor of the composite material; e is the composite materialThe decomposition activation energy of the material; r is the dissociation gas constant.
In this embodiment, the decomposition degree of the composite material may be calculated according to the real-time density, the initial density, and the decomposition density of the composite material, and specifically, the material decomposition degree formula is shown in formula (5): （5）
the specific heat capacity and the thermal conductivity of the composite material are related to the decomposition degree and the temperature, and the change equation of the specific heat capacity and the thermal conductivity of the material along with the state is shown in a formula (6): （6）
wherein k (T) is the thermal conductivity of the composite material as a function of temperature; k (k) v (T) is the initial thermal conductivity of the composite material as a function of temperature; k (k) c (T) is the thermal conductivity as a function of temperature of the composite material that is completely decomposed after being damaged by thermal radiation; c (T) is the specific heat capacity of the composite material along with the change of temperature; c (C) v (T) is the initial specific heat capacity of the composite material as a function of temperature; c (C) c (T) is the temperature-dependent specific heat capacity of the composite material that is fully decomposed after being damaged by thermal radiation; f is the degree of decomposition of the composite material.
The gas enthalpy change and material enthalpy change calculation process in the composite material thermal response model is shown in the formula (7): （7）
in formula (7), h and h g The material enthalpy change and the gas enthalpy change respectively.
Substituting the formulas (3), (4), (5), (6) and (7) into the thermal response model of the formula composite material can calculate the temperature at the current moment, and substituting the temperature at the current moment into the formulas (3), (4), (5), (6) and (7) can calculate the material parameters (such as decomposition degree, real-time density, specific heat capacity, thermal conductivity, gas enthalpy change or material enthalpy change and the like) of the composite material at the next moment.
Specifically, referring to fig. 2, according to the original parameters, the heat source parameters, the boundary conditions and the pre-constructed thermal response model of the composite material, the method calculates the material temperature and the decomposition degree of different points to be measured in the composite material at different moments, and includes the following steps:
s21, inputting the original parameters and the heat source parameters into the composite material thermal response model to obtain the change relation of the composite material temperature along with the pyrolysis time;
step S22, obtaining coordinates of the point to be tested, obtaining the material temperature of the coordinates at the last moment according to the change relation, and calculating the decomposition degree of the composite material at the current moment according to the material temperature; wherein the current time density of the composite material is calculated according to the material temperature, and the formula (3) is referred to; calculating the initial density, the decomposition density and the current time density of the composite material to obtain the decomposition degree, and referring to a formula (5);
and S23, calculating the decomposition degree of all the points to be tested of the composite material at the next moment according to the preset step length updating time until the boundary condition is met.
Specifically, a coordinate system is established by taking the thickness direction of the composite material as the z direction, the length and width directions of the composite material are respectively taken as the x direction and the y direction, and the point to be measured is a point at different positions in the composite material and is expressed by coordinates (x, y, z). Referring to fig. 2, when solving a composite thermal response model for the first time, initial conditions are acquired to initialize the model, where the initial conditions include:wherein T1 is the initial temperature. After the position information (i.e. coordinates) of each point to be measured is obtained, the temperature of the position at the last moment is calculated, then the material parameters of the position are calculated according to the temperature at the last moment, the material parameters comprise the decomposition degree (pyrolysis degree), the mass of decomposed gas and the enthalpy change of the material, and then the material parameters are calculated according to the decomposition degreeCalculating the material temperature of the current point to be measured (i.e. updating the position temperature) at the current moment by the mass of the decomposed gas and the enthalpy change of the material, and taking the material temperature as the temperature calculated at the next moment of the position; calculating the decomposition degree and the material temperature of each point to be detected in the x direction by using x=x+1; after the calculation in the x direction is finished, calculating the decomposition degree and the material temperature of each point to be measured in the y direction by using y=y+1; after the calculation in the y direction is finished, calculating the decomposition degree and the material temperature of each point to be measured in the z direction by using z=z+1; and after the calculation of all the points to be measured in the z direction is completed, updating the boundary condition, and recalculating the material temperature and the decomposition degree at the next moment of each position in the composite material until t reaches the upper limit by using the pyrolysis time t=t+1.
And S3, analyzing the obtained temperature and decomposition degree of the material to obtain the damage condition of the composite material. Specifically, the calculated data of the temperature and the decomposition degree of all materials are processed, for example, the data of the same thickness (i.e. t and y are the same) at the same moment is used as a data set, and the data of each data set are presented in a cloud image form, so that the temperature cloud images of the composite materials with different thicknesses can be obtained. For another example, the decomposition degree of the same position at different moments (i.e. the coordinates are the same and t is different) is used as a data set, and then the data in each data set is processed to obtain a temperature change curve. And determining the damage condition of the composite material according to the temperature cloud picture and the temperature change curve, and presenting the data to a user in a graphical form.
Compared with the traditional heat transfer model, the method considers the influence of material pyrolysis and gas escape of the composite material structure subjected to heat radiation on the temperature of the composite material structure, and can analyze the temperature distribution and pyrolysis depth of the composite material structure in detail. In addition, the thermal response analysis method provided by the application aims at the three-dimensional anisotropic laminated composite structure, and the temperature and the pyrolysis distribution of each part of the composite structure subjected to heated radiation can be analyzed by the method, so that the thermal response analysis is more accurate and comprehensive.
In another embodiment of the present application, to facilitate solving the model, the present embodiment is based on finite difference programming to solve the thermal response model of the composite structure, i.e. the method further comprises: obtaining a layering mode of each layer of material of the composite material, and extracting a corresponding model differential format according to the layering mode; and carrying out format conversion treatment on the composite material thermal response model according to the model differential format, and calculating the material temperature and the decomposition degree through the composite material thermal response model after the format conversion treatment.
Specifically, in the present embodiment, the layering manner is generally divided into three layering angles:when the layering angle of the layering mode isOr (b)When the formula of the thermal response model of the composite material is converted into: （8）
when the layering angle of the layering mode isWhen the formula of the thermal response model of the composite material is converted into:（9）
wherein, p and p+1 are marked on the formula to respectively represent the material temperature at the current moment and the next moment; subscripts m, n, q represent x, y, z coordinate points of the spatial position where the differential point is located, respectively.
In another embodiment of the present application, practical data is taken as an example to illustrate the practical effect of the thermal response analysis method of the three-dimensional laminated composite material of the present application, and the example uses a laser beam with a heat source radius of 2 mm, a heat flux density of 700 kW/m2, and a heat flux action time of 450 s, which acts on the center of the composite material sample. The composite samples were 60 mm in both width and length. Three-layer material in composite materialThe layering modes of the materials are respectivelyEach layer had a thickness of 1 mm. The ambient temperature is->The original parameters of the composite are shown in table 1.
TABLE 1
Substituting the data of table 1 into the above formula, a temperature cloud image at the sample centers 0.5 mm, 1.5 mm, 2.5 mm (i.e., the thickness of the composite material) was calculated, as shown in fig. 3. Fig. 4 also shows the thermal decomposition degree (decomposition degree) of the sample center at 0.1. 0.1 mm in this example as a function of time.
The example calculation result shows that the method can calculate the change relation between the temperature and the pyrolysis degree of the composite material structure at different positions along with time, and can be used for evaluating the damage of the equipment structure under the scene of heat radiation. The comprehensive description of the method has practical guidance and application values.
The foregoing is a detailed modeling process of the method of the present application, which is developed from a basic principle to embody the main features and advantages of the present application, which are different from those of the heat transfer model of other materials, and the solving result is shown in the accompanying drawings by a specific example. In addition, the application is not limited to the above examples, and can realize analysis of various scenes by modifying heat source parameters, material types, layering sequence and the like. Accordingly, the models directly modified and deformed by those skilled in the art from the present disclosure are considered as the protection scope of the present application. What is not described in detail in the present specification belongs to the known technology of those skilled in the art.
In a second aspect, an embodiment of the present application provides an electronic device, and fig. 5 is a block diagram of the electronic device according to an exemplary embodiment. As shown in fig. 5, the electronic device may include a processor 51 and a memory 52 storing computer program instructions.
In particular, the processor 51 may comprise a Central Processing Unit (CPU), or an application specific integrated circuit (Application Specific Integrated Circuit, abbreviated as ASIC), or may be configured as one or more integrated circuits that implement embodiments of the present application.
Memory 52 may include, among other things, mass storage for data or instructions. By way of example, and not limitation, memory 52 may comprise a Hard Disk Drive (HDD), floppy Disk Drive, solid state Drive (Solid State Drive, SSD), flash memory, optical Disk, magneto-optical Disk, tape, or universal serial bus (Universal Serial Bus, USB) Drive, or a combination of two or more of the foregoing. Memory 52 may include removable or non-removable (or fixed) media, where appropriate. The memory 52 may be internal or external to the data processing apparatus, where appropriate. In a particular embodiment, the memory 52 is a Non-Volatile memory. In particular embodiments, memory 52 includes Read-Only Memory (ROM) and random access Memory (Random Access Memory, RAM). Where appropriate, the ROM may be a mask-programmed ROM, a programmable ROM (Programmable Read-Only Memory, abbreviated PROM), an erasable PROM (Erasable Programmable Read-Only Memory, abbreviated EPROM), an electrically erasable PROM (Electrically Erasable Programmable Read-Only Memory, abbreviated EEPROM), an electrically rewritable ROM (Electrically Alterable Read-Only Memory, abbreviated EAROM), or a FLASH Memory (FLASH), or a combination of two or more of these. The RAM may be Static Random-Access Memory (SRAM) or dynamic Random-Access Memory (Dynamic Random Access Memory DRAM), where the DRAM may be a fast page mode dynamic Random-Access Memory (Fast Page Mode Dynamic Random Access Memory FPMDRAM), extended data output dynamic Random-Access Memory (Extended Date Out Dynamic Random Access Memory EDODRAM), synchronous dynamic Random-Access Memory (Synchronous Dynamic Random-Access Memory SDRAM), or the like, as appropriate.
Memory 52 may be used to store or cache various data files that need to be processed and/or communicated, as well as possible computer program instructions for execution by processor 51.
The processor 51 reads and executes the computer program instructions stored in the memory 52 to implement any of the three-dimensional laminate composite thermal response analysis methods of the above embodiments.
In an embodiment, the electronic device may also include a communication interface 53 and a bus 50. As shown in fig. 5, the processor 51, the memory 52, and the communication interface 53 are connected to each other through the bus 50 and perform communication with each other.
The communication interface 53 is used to enable communication between modules, devices, units, and/or units in embodiments of the application. The communication port 53 may also enable communication with other components such as: and the external equipment, the image/data acquisition equipment, the database, the external storage, the image/data processing workstation and the like are used for data communication.
Bus 50 includes hardware, software, or both that couple components of the electronic device to one another. Bus 50 includes, but is not limited to, at least one of: data Bus (Data Bus), address Bus (Address Bus), control Bus (Control Bus), expansion Bus (Expansion Bus), local Bus (Local Bus). By way of example, and not limitation, bus 50 may include a graphics acceleration interface (Accelerated Graphics Port), abbreviated AGP, or other graphics Bus, an enhanced industry standard architecture (Extended Industry Standard Architecture, abbreviated EISA) Bus, a Front Side Bus (FSB), a HyperTransport (HT) interconnect, an industry standard architecture (Industry Standard Architecture, ISA) Bus, a wireless bandwidth (InfiniBand) interconnect, a Low Pin Count (LPC) Bus, a memory Bus, a micro channel architecture (Micro Channel Architecture, abbreviated MCa) Bus, a peripheral component interconnect (Peripheral Component Interconnect, abbreviated PCI) Bus, a PCI-Express (PCI-X) Bus, a serial advanced technology attachment (Serial Advanced Technology Attachment, abbreviated SATA) Bus, a video electronics standards association local (Video Electronics Standards Association Local Bus, abbreviated VLB) Bus, or other suitable Bus, or a combination of two or more of the foregoing. Bus 50 may include one or more buses, where appropriate. Although embodiments of the application have been described and illustrated with respect to a particular bus, the application contemplates any suitable bus or interconnect.
In a third aspect, embodiments of the present application provide a computer-readable storage medium having stored thereon a program which, when executed by a processor, implements the three-dimensional laminated composite thermal response analysis method provided in the first aspect.
More specifically, among others, readable storage media may be employed including, but not limited to: portable disk, hard disk, random access memory, read only memory, erasable programmable read only memory, optical storage device, magnetic storage device, or any suitable combination of the foregoing.
In a possible embodiment, the application may also be realized in the form of a program product comprising program code for causing a terminal device to carry out the steps of carrying out the method of thermal response analysis of a three-dimensional laminated composite material as provided in the first aspect, when said program product is run on the terminal device.
Wherein the program code for carrying out the application may be written in any combination of one or more programming languages, which program code may execute entirely on the user device, partly on the user device, as a stand-alone software package, partly on the user device and partly on the remote device or entirely on the remote device.
The technical features of the above-described embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above-described embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.
The above examples illustrate only a few embodiments of the application, which are described in detail and are not to be construed as limiting the scope of the application. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application. Accordingly, the scope of protection of the present application is to be determined by the appended claims.
Claims (10)
1. A method of analyzing thermal response of a laminated composite material, comprising:
determining heat source parameters and boundary conditions according to the heated heat source of the composite material;
calculating the material temperature and decomposition degree of different to-be-detected points in the composite material at different moments according to the original parameters, the heat source parameters, the boundary conditions and a pre-constructed composite material thermal response model of the composite material; wherein the original parameters are data collected when the composite material undergoes a pyrolysis reaction;
and analyzing the obtained temperature and decomposition degree of the material to obtain the damage condition of the composite material.
2. The method of claim 1, wherein the constructing of the composite thermal response model comprises:
calculating the real-time density of the composite material according to the real-time temperature of the composite material;
determining the mass of the decomposition gas produced by pyrolysis of the composite material based on the real-time density;
obtaining the specific heat capacity and the thermal conductivity of the composite material according to the real-time temperature of the composite material;
and constructing the thermal response model of the composite material according to the real-time density, the mass, the specific heat capacity and the thermal conductivity of the decomposed gas.
3. The method of claim 2, wherein the composite thermal response model is:
wherein (1)>Real-time density of the composite material; c (C) P The specific heat capacity of the composite material at the current moment; t is the real-time temperature of the composite material; t is the pyrolysis time of the composite material heated radiation; k (k) x 、k y 、k z Thermal conductivities of the composite material in x, y and z directions respectively; />The mass of the decomposition gas generated when the composite material is pyrolyzed; c (C) pg Specific heat capacity for a decomposition gas generated when the composite material is pyrolyzed; q (Q) dec Is the heat generated when the composite material is pyrolyzed; h and h g The enthalpy change of the composite material and the enthalpy change of the decomposed gas are respectively.
4. The method according to claim 1, wherein calculating the material temperature and the decomposition degree of different points to be measured in the composite material at different moments according to the original parameters, the heat source parameters, the boundary conditions and the pre-constructed thermal response model of the composite material comprises:
inputting the original parameters and the heat source parameters into the composite material thermal response model to obtain the change relation of the composite material temperature along with the pyrolysis time;
acquiring coordinates of the point to be measured, and acquiring the material temperature of the coordinates at the last moment according to the change relation;
calculating the current time density of the composite material according to the material temperature;
calculating the initial density, the decomposition density and the current time density of the composite material to obtain the decomposition degree;
and calculating the decomposition degree of all the points to be tested of the composite material at the next moment according to the preset step length updating time until the boundary condition is met.
5. The method of claim 2, wherein the step of determining the position of the substrate comprises,
the calculation formula of the real-time density of the composite material is as follows:
the mass calculation formula of the decomposed gas is as follows: />Wherein (1)>An initial density of the composite material; />The decomposition density of the composite material is completely decomposed after the composite material is damaged by heat radiation; n is the reaction progression of the composite material; a is a pre-finger factor of the composite material; e is the decomposition activation energy of the composite material; r is the dissociation gas constant.
6. The method of claim 2, wherein the specific heat capacity and thermal conductivity of the composite are obtained from real-time temperature of the composite; the calculation process comprises the following steps:
wherein k (T) is the thermal conductivity of the composite material as a function of temperature; k (k) v (T) is the initial thermal conductivity of the composite material as a function of temperature; k (k) c (T) is the thermal conductivity as a function of temperature of the composite material that is completely decomposed after being damaged by thermal radiation; c (T) is the specific heat capacity of the composite material along with the change of temperature; c (C) v (T) is the initial ratio of the composite material with the change of temperatureA heat capacity; c (C) c (T) is the temperature-dependent specific heat capacity of the composite material that is fully decomposed after being damaged by thermal radiation; f is the degree of decomposition of the composite material.
7. The method of claim 1, wherein the composite thermal response model includes boundary conditions; wherein the boundary conditions are as follows:
wherein (1)>And->The temperature change rate of the heating surface and the temperature change rate of the back surface of the composite material are respectively; />A heat flux density for heat radiation to which the composite material is subjected; />A refractive index of the composite material; />Is a stefin-boltzmann constant; h is a front And h back The convection heat exchange coefficient of the heating surface of the composite material and the convection heat exchange coefficient of the back surface are respectively; t (T) s 、T back 、T ∞ The temperature of the material of the heating surface of the composite material, the temperature of the material of the back surface of the composite material and the ambient temperature are respectively.
8. The method according to claim 1, wherein the method further comprises:
obtaining a layering mode of each layer of material of the composite material, and extracting a corresponding model differential format according to the layering mode;
performing format conversion treatment on the composite material thermal response model according to the model differential format, and calculating the material temperature and the decomposition degree through the composite material thermal response model after the format conversion treatment; wherein,
when the layering angle of the layering mode isOr->When the formula of the thermal response model of the composite material is converted into:
when the layering angle of the layering manner is +.>When the formula of the thermal response model of the composite material is converted into:wherein, p and p+1 are marked on the formula to respectively represent the material temperature at the current moment and the next moment; subscripts m, n, q represent x, y, z coordinate points of the spatial position where the differential point is located, respectively.
9. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, the processor implementing the laminated composite thermal response analysis method of any one of claims 1 to 8 when the computer program is executed.
10. A computer readable storage medium having stored thereon a computer program, wherein the program when executed by a processor implements the laminated composite thermal response analysis method of any one of claims 1 to 8.
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