CN115577566A - Processing method, device, equipment and medium for continuous ablation of multilayer heat-proof structure - Google Patents

Processing method, device, equipment and medium for continuous ablation of multilayer heat-proof structure Download PDF

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CN115577566A
CN115577566A CN202211421457.0A CN202211421457A CN115577566A CN 115577566 A CN115577566 A CN 115577566A CN 202211421457 A CN202211421457 A CN 202211421457A CN 115577566 A CN115577566 A CN 115577566A
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CN115577566B (en
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国义军
李睿智
周述光
朱言旦
刘骁
曾磊
邱波
石友安
张昊元
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Computational Aerodynamics Institute of China Aerodynamics Research and Development Center
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Abstract

The application discloses a processing method, a device, equipment and a medium for continuous ablation of a multilayer heat-proof structure, which relate to the field of aerospace craft heat-proof systems and comprise the steps of respectively establishing equations of internal temperature fields of an ablation unit layer, a heat insulation layer and a bearing structure layer which are not ablated in an ablation layer; the ablation unit layer is at least two layers; determining boundary conditions, wherein the boundary conditions comprise boundary conditions of an ablation layer and a heat-insulating layer, boundary conditions of the heat-insulating layer and a bearing structure layer, and boundary conditions of an ablation surface of the ablation layer; boundary conditions for the ablative surface of the ablative layer include wall temperature; carrying out differential dispersion on equations and boundary conditions of all internal temperature fields to obtain a differential equation; and determining the temperature and the wall temperature of the internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated according to a differential equation. According to the method, when the ablation layer is continuously ablated, the internal temperature fields of the heat-insulating layer and the bearing structure layer are taken into account, so that the temperatures of different material layers are obtained, and the ablation appearance and the temperature field calculation accuracy are improved.

Description

Processing method, device, equipment and medium for continuous ablation of multilayer heat-proof structure
Technical Field
The application relates to the field of aerospace craft heat protection systems, in particular to a processing method and device for continuous ablation of a multilayer heat protection structure, electronic equipment and a computer readable storage medium.
Background
The heat protection system of the aerospace craft is generally designed into a multilayer structure form, wherein the outermost layer is an ablation layer, the middle layer is a heat insulation layer, and the inner layer is a bearing structure layer. For the purposes of reducing the weight of the thermal protection system, enhancing the radiation out of the surface for heat dissipation or insulation, the outermost ablative layer may be made of a variety of different types of ablative materials, for example, a thermal protective coating on the outermost layer followed by an insulating layer, a high density ablative material layer, a medium density ablative layer, etc. on the inside. When the aircraft flies in the atmospheric layer, the outer layer materials are sequentially burnt, and the situation of continuous ablation of various materials occurs. At present, an ablation calculation method can only process one layer of ablation material and cannot process continuous ablation of more than two layers of ablation materials in an ablation process, and the influence of a heat insulation layer and a bearing structure layer on an ablation layer is not considered, so that the calculated temperature deviation of each layer of a heat protection system is large.
Therefore, how to solve the above technical problems should be a great concern to those skilled in the art.
Disclosure of Invention
The application aims to provide a processing method, a processing device, electronic equipment and a computer readable storage medium for continuous ablation of a multilayer heat-proof structure so as to accurately obtain the temperature distribution of the multilayer heat-proof structure.
In order to solve the above technical problem, the present application provides a processing method for continuous ablation of a multilayer heat protection structure, including:
respectively establishing equations of internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated in the ablation layer; the ablation unit layer is at least two layers;
determining boundary conditions, wherein the boundary conditions comprise boundary conditions of the ablation layer and the heat-insulating layer, boundary conditions of the heat-insulating layer and the bearing structure layer, and boundary conditions of an ablation surface of the ablation layer; boundary conditions of the ablation surface of the ablation layer include wall temperature;
carrying out differential discretization on equations of all internal temperature fields and the boundary conditions to obtain a differential equation;
and determining the temperatures of the ablation unit layers, the thermal insulation layer and the internal temperature field of the bearing structure layer which are not ablated and the wall temperature according to the difference equation.
Optionally, the method further includes:
respectively establishing the relation between the thermophysical parameters of each ablation unit layer, the heat insulation layer and the bearing structure layer in the ablation layer and the corresponding layer structure thickness;
determining the ablation unit layer at the current outermost layer according to the current ablation amount;
determining a corresponding ablation model for determining the ablation amount at the next moment according to the type of the current outermost layer of the ablation unit layer;
determining the thermophysical property parameters of the ablation unit layer at the current outermost layer according to the relationship;
and determining the ablation amount at the next moment according to the thermophysical property parameters, the temperature of the ablation unit layer which is not ablated, the heat insulation layer, the temperature of the internal temperature field of the bearing structure layer, the wall temperature, the pyrolysis gas mass flow rate and the ablation model.
Optionally, the equation for respectively establishing the internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated in the ablation layer includes:
the equation for establishing the internal temperature field of the non-ablated ablation unit layers in the ablation layer is:
Figure 109053DEST_PATH_IMAGE001
wherein, among others,
Figure 834564DEST_PATH_IMAGE002
for the mass flow rate of the pyrolysis gas,
Figure 80869DEST_PATH_IMAGE003
in order to increase the rate of the pyrolysis reaction,
Figure 92687DEST_PATH_IMAGE004
in order to be the heat of pyrolysis,
Figure 791653DEST_PATH_IMAGE005
the density of the layer of ablated cells for the s-th layer,
Figure 179909DEST_PATH_IMAGE006
is the specific heat capacity, k, of the layer of the s-th ablation unit s Is the thermal conductivity of the s-th layer of ablation unit layer, T is the temperature of the internal temperature field of the non-ablated ablation unit layer, T is the ablation time,
Figure 139775DEST_PATH_IMAGE007
the specific heat at a constant pressure is used,
Figure 197860DEST_PATH_IMAGE008
as a result of the density of the gas,
Figure 774335DEST_PATH_IMAGE009
is the gradient of the temperature T in the heat transfer direction y;
the equation for establishing the internal temperature field of the thermal insulation layer is as follows:
Figure 838719DEST_PATH_IMAGE010
wherein, the first and the second end of the pipe are connected with each other,
Figure 794036DEST_PATH_IMAGE011
the density of the thermal insulation layer is the same as,
Figure 413236DEST_PATH_IMAGE012
is the specific heat capacity of the heat-insulating layer,
Figure 86794DEST_PATH_IMAGE013
is the thermal conductivity of the thermal insulation layer,
Figure 551274DEST_PATH_IMAGE014
is the temperature of the internal temperature field of the insulation layer,
Figure 626677DEST_PATH_IMAGE015
is a temperature
Figure 416779DEST_PATH_IMAGE014
A gradient in the heat transfer direction y;
the equation for establishing the internal temperature field of the bearing structure layer is as follows:
Figure 312054DEST_PATH_IMAGE016
wherein, the first and the second end of the pipe are connected with each other,
Figure 580224DEST_PATH_IMAGE017
is the density of the bearing structure layer,
Figure 634767DEST_PATH_IMAGE018
is the specific heat capacity of the bearing structure layer,
Figure 205557DEST_PATH_IMAGE019
is the heat conductivity coefficient of the bearing structure layer,
Figure 978341DEST_PATH_IMAGE020
is the temperature of the internal temperature field of the bearing structure layer,
Figure 925569DEST_PATH_IMAGE021
is a temperature
Figure 834619DEST_PATH_IMAGE022
Gradient in the heat transfer direction y-direction.
Optionally, the boundary conditions of the ablation surface of the ablation layer are as follows:
Figure 841889DEST_PATH_IMAGE023
wherein the content of the first and second substances,
Figure 836390DEST_PATH_IMAGE024
in order to take account of the net heat flow introduced into the interior of the multilayer heat protection structure from the surface of the ablation layer after the ablation effect,
Figure 590238DEST_PATH_IMAGE025
in order to be the radiation coefficient,
Figure 619374DEST_PATH_IMAGE026
is the Stefan-Boltzmann parameter,
Figure 531966DEST_PATH_IMAGE027
wall temperature, k, of the ablation layer s The thermal conductivity of the s-th layer of the ablated cell layer.
Optionally, determining the temperatures of the internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated according to the difference equation comprises:
and determining the temperatures of the internal temperature fields of the non-ablated ablation unit layers, the thermal insulation layers and the bearing structure layers and the wall temperature according to the differential equation by using any one method of a three-diagonal pursuit method, an LU decomposition method and a direct matrix inversion matrix method.
Optionally, before performing differential discretization on all equations of the internal temperature field and the boundary condition, the method further includes:
transforming the equations of all internal temperature fields and boundary conditions of the ablation surface of said ablation layer in a fixed coordinate system to equations and boundary conditions in a moving coordinate system that recedes with the ablation surface;
accordingly, the differential discretization of the equations for all internal temperature fields and said boundary conditions comprises:
and carrying out differential discretization on equations of all the converted internal temperature fields and the boundary conditions.
The application also provides a processing apparatus when multilayer heat protection structure continues ablation, includes:
the first establishing module is used for respectively establishing equations of internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated in the ablation layer; the ablation unit layer is at least two layers;
the first determining module is used for determining boundary conditions, wherein the boundary conditions comprise boundary conditions of the ablation layer and the thermal insulation layer, boundary conditions of the thermal insulation layer and the bearing structure layer and boundary conditions of an ablation surface of the ablation layer; boundary conditions of the ablation surface of the ablation layer include wall temperature;
the difference dispersion module is used for carrying out difference dispersion on all the equations of the internal temperature fields and the boundary conditions to obtain a difference equation;
and the second determining module is used for determining the temperatures of the ablation unit layers, the thermal insulation layers and the internal temperature fields of the bearing structure layers which are not ablated and the wall temperature according to the differential equation.
Optionally, the method further includes:
the conversion module is used for converting the equations of all internal temperature fields in a fixed coordinate system and the boundary conditions of the ablation surface of the ablation layer into the equations and the boundary conditions in a moving coordinate system which shrinks along with the ablation surface;
correspondingly, the differential dispersion module is used for carrying out differential dispersion on the equations of all the converted internal temperature fields and the boundary conditions to obtain a differential equation.
The present application further provides an electronic device, comprising:
a memory for storing a computer program;
and the processor is used for realizing the steps of the processing method for the continuous ablation of the multilayer heat-proof structure when the computer program is executed.
The present application further provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, and the computer program, when executed by a processor, implements the steps of the processing method for continuous ablation of the multilayer heat protection structure.
The application provides a processing method for continuous ablation of a multilayer heat-proof structure, which comprises the following steps: respectively establishing equations of internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated in the ablation layer; the ablation unit layer is at least two layers; determining boundary conditions, wherein the boundary conditions comprise boundary conditions of the ablation layer and the heat-insulating layer, boundary conditions of the heat-insulating layer and the bearing structure layer, and boundary conditions of an ablation surface of the ablation layer; boundary conditions of the ablation surface of the ablation layer include wall temperature; carrying out differential discretization on equations of all internal temperature fields and the boundary conditions to obtain a differential equation; and determining the temperatures of the ablation unit layers, the thermal insulation layer and the internal temperature field of the bearing structure layer which are not ablated and the wall temperature according to the difference equation.
It can be seen that, in the present application, the ablation layer includes at least two ablation unit layers, equations of corresponding internal temperature fields are respectively established for the ablation unit layers, the thermal insulation layer and the bearing structure layer which are not ablated, boundary conditions among the ablation layer, the thermal insulation layer and the bearing structure layer and boundary conditions of the ablation surface of the ablation layer are determined, then the respective internal temperature field equations and boundary conditions of the ablation layer, the thermal insulation layer and the bearing structure layer are subjected to differential discretization, and then the internal temperatures and wall temperatures of the ablation unit layers, the thermal insulation layer and the bearing structure layer which are not ablated are determined according to the differential discretization equation, so that the temperature distribution of each layer of the multilayer heat-proof structure can be obtained. The temperature accuracy is improved by taking the internal temperature fields of the thermal insulation layer and the bearing structure layer which cannot be ablated into consideration in the continuous ablation process of the ablation unit layers.
In addition, the application also provides a device, an electronic device and a computer readable storage medium with the advantages.
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For a clearer explanation of the embodiments or technical solutions of the prior art of the present application, the drawings needed for the description of the embodiments or prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic diagram of an ablation internal thermal response model of a single-layer ablated material in the prior art;
FIG. 2 is a flowchart of a processing method for sequential ablation of a multilayer thermal structure according to an embodiment of the present disclosure;
FIGS. 3 (a) to 3 (d) are schematic views of the sequential ablation of the multilayer thermal protection structure in the present application;
FIG. 4 is a graph comparing the temperature field inside the ablation layer obtained in the present application with the results calculated by the CHAP program of the United states, experimental results;
FIG. 5 is a flowchart of another alternative method for sequential ablation of a multilayer thermal structure in accordance with an embodiment of the present disclosure;
FIG. 6 is a comparison graph of the results of successive ablation calculations for one and two ablation unit layers in an ablation layer of an aircraft;
FIG. 7 is a flowchart of an implementation of a sequential ablation calculation model for a multi-layer thermal protection structure of an aircraft according to the present application;
fig. 8 is a block diagram of a processing apparatus for sequential ablation of a multilayer heat shielding structure according to an embodiment of the present disclosure.
Detailed Description
In order that those skilled in the art will better understand the disclosure, the following detailed description is given with reference to the accompanying drawings. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The schematic diagram of the ablation internal thermal response model of the single-layer ablation material is shown in FIG. 1, wherein the total thickness of the thermal protection system is
Figure 13763DEST_PATH_IMAGE028
The thickness of the ablation layer is
Figure 302793DEST_PATH_IMAGE029
The remaining thickness of the removed ablation layer is x,
Figure 186435DEST_PATH_IMAGE030
in order to be the flow of the incoming heat,
Figure 269929DEST_PATH_IMAGE031
in order to pyrolyze the heat flow carried away,
Figure 239022DEST_PATH_IMAGE032
in order to obtain the density of the carbonized layer,
Figure 331743DEST_PATH_IMAGE033
in order to obtain the density of the pyrolysis zone,
Figure 69892DEST_PATH_IMAGE034
is the density of the original material layer. O is the origin of the fixed coordinate system, the coordinate axis y is the ablation direction in the fixed coordinate system,
Figure 589866DEST_PATH_IMAGE035
is the origin of a moving coordinate system which is retracted along with the ablation surface
Figure 46255DEST_PATH_IMAGE036
Is the ablation direction in the moving coordinate system.
As described in the background section, the conventional ablation calculation method can only process one layer of ablation material in the ablation process, but cannot process continuous ablation of more than two layers of ablation materials, and does not consider the influence of the thermal insulation layer and the bearing structure layer on the ablation layer, so that the calculated temperature deviation of each layer of the thermal protection system is large.
In view of the above, the present application provides a processing method for continuous ablation of a multi-layer heat shielding structure, please refer to fig. 2, which includes:
step S101: respectively establishing equations of internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated in the ablation layer; the ablation unit layer is at least two layers.
The ablation layer comprises at least two ablation unit layers, the specific number of the ablation unit layers is determined according to the situation, and the application is not particularly limited. The ablation layer is ablated in sequence inwardly from the outermost surface. The multilayer heat-proof structure is provided with an ablation layer, a heat-insulating layer and a bearing structure layer which are arranged outwards and inwards in sequence.
The equation for respectively establishing the internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated in the ablation layer comprises the following steps:
step S1011: the equation for establishing the internal temperature field of the non-ablated ablation unit layers in the ablation layer is:
Figure 677088DEST_PATH_IMAGE037
（1）
wherein the content of the first and second substances,
Figure 535322DEST_PATH_IMAGE002
for the mass flow rate of the pyrolysis gas,
Figure 85252DEST_PATH_IMAGE003
in order to increase the rate of the pyrolysis reaction,
Figure 638725DEST_PATH_IMAGE004
in order to be the heat of pyrolysis,
Figure 197882DEST_PATH_IMAGE005
the density of the layer of the s-th ablation unit,
Figure 783060DEST_PATH_IMAGE006
is the specific heat capacity, k, of the layer of the s-th ablation unit s Is the thermal conductivity of the s-th ablation unit layer, T is the temperature of the internal temperature field of the non-ablated ablation unit layer, T is the ablation time,
Figure 769470DEST_PATH_IMAGE007
the specific heat at a constant pressure is used,
Figure 810238DEST_PATH_IMAGE008
as the density of the gas, it is,
Figure 907507DEST_PATH_IMAGE009
is the gradient of the temperature T in the direction y of the heat transfer direction,
Figure 350121DEST_PATH_IMAGE038
，
Figure 507433DEST_PATH_IMAGE039
for the total thickness of the ablation,
Figure 301077DEST_PATH_IMAGE040
is the total thickness of the ablation layer.
The schematic diagrams of the sequential ablation of the multilayer thermal protection structure are shown in fig. 3 (a) to 3 (d). Assuming that the ablation layer comprises n ablation unit layers, which are respectively marked as ablation unit layer a, ablation unit layer b, ablation unit layer c, \ 8230, ablation unit layer m and ablation unit layer n, the thickness of each ablation unit layer is respectively marked as corresponding
Figure 202037DEST_PATH_IMAGE041
The thickness of the ablation layer
Figure 764736DEST_PATH_IMAGE042
. The thickness of the heat insulation layer is
Figure 92949DEST_PATH_IMAGE043
The thickness of the bearing structure layer is
Figure 373889DEST_PATH_IMAGE044
. With burningThe etching is carried out by sequentially ablating the ablation layer from the outermost layer to the inner side, the total ablation thickness being
Figure 688327DEST_PATH_IMAGE045
。
Figure 230167DEST_PATH_IMAGE046
And
Figure 604647DEST_PATH_IMAGE047
are both piecewise functions of the y-coordinate (heat transfer direction coordinate), depending on the type of material of the ablation layer, i.e.:
Figure 231938DEST_PATH_IMAGE048
。
step S1012: the equation for establishing the internal temperature field of the thermal insulation layer is as follows:
Figure 606857DEST_PATH_IMAGE049
（2）
wherein the content of the first and second substances,
Figure 268782DEST_PATH_IMAGE050
the density of the thermal insulation layer is the same as,
Figure 79743DEST_PATH_IMAGE012
is the specific heat capacity of the heat-insulating layer,
Figure 804117DEST_PATH_IMAGE013
is the thermal conductivity of the thermal insulation layer,
Figure 116149DEST_PATH_IMAGE014
is the temperature of the internal temperature field of the insulation layer,
Figure 773527DEST_PATH_IMAGE051
is temperature
Figure 489810DEST_PATH_IMAGE014
Gradient in the heat transfer direction y-direction.
Step S1013: the equation for establishing the internal temperature field of the bearing structure layer is as follows:
Figure 826114DEST_PATH_IMAGE052
（3）
wherein the content of the first and second substances,
Figure 817203DEST_PATH_IMAGE017
is the density of the bearing structure layer,
Figure 63508DEST_PATH_IMAGE018
is the specific heat capacity of the bearing structure layer,
Figure 75326DEST_PATH_IMAGE053
is the heat conductivity coefficient of the bearing structure layer,
Figure 39871DEST_PATH_IMAGE020
is the temperature of the internal temperature field of the bearing structure layer,
Figure 162548DEST_PATH_IMAGE054
is temperature
Figure 526009DEST_PATH_IMAGE022
Gradient in the heat transfer direction y-direction.
Equations (1), (2), (3) are all equations in a fixed coordinate system, and equation (1) describes the internal temperature field with the one-dimensional heat conduction fundamental equation for solid materials with pyrolysis.
Step S102: determining boundary conditions, wherein the boundary conditions comprise the boundary conditions of the ablation layer and the heat-insulating layer, the boundary conditions of the heat-insulating layer and the bearing structure layer, and the boundary conditions of the ablation surface of the ablation layer; the boundary condition of the ablation surface of the ablation layer includes a wall temperature.
It should be noted that it is also necessary to determine the initial conditions of the environment in which the multilayer thermal protection structure is located, the initial conditions including, but not limited to, the initial temperature, the initial heat flow.
The boundary conditions of the ablation layer and the heat insulation layer are as follows: heat flow and temperature are equal at the interface; the boundary conditions of the heat-insulating layer and the bearing structure layer are as follows: heat flow and temperature are equal at the interface. The inner surface of the ablation layer adopts a heat insulation condition.
The boundary conditions of the ablation surface of the ablation layer are as follows:
Figure 708728DEST_PATH_IMAGE055
（4）
wherein the content of the first and second substances,
Figure 894990DEST_PATH_IMAGE024
in order to take account of the net heat flow introduced into the interior of the multilayer heat protection structure from the surface of the ablation layer after the ablation effect,
Figure 86937DEST_PATH_IMAGE025
in order to be the radiation coefficient,
Figure 307834DEST_PATH_IMAGE026
is the Stefan-Boltzmann parameter,
Figure 661455DEST_PATH_IMAGE027
is the wall temperature of the ablation layer, i.e. the temperature of the outermost surface of the ablation layer, k s The thermal conductivity of the s-th layer of the ablated cell layer.
It is to be noted that the formula (4) is an equation in a fixed coordinate system.
Step S103: and carrying out differential discretization on the equations of all the internal temperature fields and the boundary conditions to obtain a differential equation.
For the specific process of differential dispersion, reference may be made to related technologies, and details are not described herein again. The difference equation obtained in the step is a difference equation in a standard form, and the form is as follows:
Figure 600592DEST_PATH_IMAGE056
（5）
wherein the content of the first and second substances,t is temperature, a, B, C, D are coefficients, corresponding to the variables in the above formula, with the lower corner mark representing a time, the upper corner mark representing a location, e.g.,
Figure 206017DEST_PATH_IMAGE057
indicating the temperature at time i, point n +1 grid position.
Step S104: and determining the temperatures of the ablation unit layers, the thermal insulation layer and the internal temperature field of the bearing structure layer which are not ablated and the wall temperature according to the difference equation.
It should be noted that, in the present application, the manner of processing the differential equation to obtain the temperature of the internal temperature field of the ablation unit layer, the temperature of the internal temperature field of the thermal insulation layer, the temperature of the internal temperature field of the load-bearing structural layer, and the wall temperature is not limited.
Optionally, determining the temperatures of the internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated according to the difference equation comprises:
and determining the temperatures of the internal temperature fields of the non-ablated ablation unit layers, the thermal insulation layers and the bearing structure layers and the wall temperature according to the differential equation by using any one method of a three-diagonal pursuit method, an LU decomposition method and a direct matrix inversion matrix method.
The specific process of solving the differential equation by using the tri-diagonal catch-up method, the LU decomposition method and the direct matrix inversion matrix method can refer to the related art, and details are not repeated here.
The ablation layer at least comprises two ablation unit layers, equations of corresponding internal temperature fields are respectively established for the ablation unit layers, the thermal insulation layer and the bearing structure layer which are not ablated, boundary conditions among the ablation layer, the thermal insulation layer and the bearing structure layer and boundary conditions of the ablation surface of the ablation layer are determined, then the respective internal temperature field equations and boundary conditions of the ablation layer, the thermal insulation layer and the bearing structure layer are subjected to differential discretization, and then the internal temperatures and wall temperatures of the ablation unit layers, the thermal insulation layer and the bearing structure layer which are not ablated are determined according to the differential discretization equations, so that the temperature distribution of each layer of the multilayer heat-proof structure can be obtained. According to the application, the internal temperature fields of the thermal insulation layer and the bearing structure layer which cannot be ablated are taken into consideration in the continuous ablation process of the ablation unit layers, so that the temperature accuracy is improved.
A comparison graph of the temperature field inside the ablation layer obtained by the processing method of the present application with the results calculated by the CHAP program in the united states and the experimental results is shown in fig. 4, in which the abscissa is time and the ordinate is temperature, and the overall trend of the temperature calculated by the processing method of the present application is the same as that of the other two results.
On the basis of the above embodiments, in an embodiment of the present application, referring to fig. 5, the processing method for the sequential ablation of the multilayer thermal protection structure further includes:
step S201: and respectively establishing the relation between the thermophysical property parameters of each ablation unit layer, the heat insulation layer and the bearing structure layer in the ablation layer and the corresponding layer structure thickness.
The form of the relationship between each layer structure and the corresponding thickness is not limited in the present application, and for example, the relationship may be a piecewise function relationship, and the thickness of the ablation unit layer a is
Figure 671633DEST_PATH_IMAGE058
Corresponding to the thermophysical parameters of the ablation unit layer a; for the ablation cell layer b, thickness
Figure 805943DEST_PATH_IMAGE059
Corresponding to the thermal physical property parameter of the ablation unit layer b; 8230; for ablated cell layer n, thickness
Figure 357010DEST_PATH_IMAGE060
Corresponding to the thermophysical parameters of the ablation unit layer n; thickness for the thermal insulation layer
Figure 500546DEST_PATH_IMAGE061
Corresponding to the thermophysical parameters of the heat insulation layer; thickness of bearing structure layer
Figure 555090DEST_PATH_IMAGE062
Corresponding to the thermophysical parameters of the bearing structure layer.Wherein, the thermophysical parameters include but are not limited to thermal conductivity and specific heat capacity.
Step S202: and determining the ablation unit layer at the current outermost layer according to the current ablation amount.
According to the current ablation amount (i.e. the total ablation thickness)
Figure 125880DEST_PATH_IMAGE045
The thickness relationship with each ablation cell layer determines the outermost ablation cell layer. For example, when
Figure 898664DEST_PATH_IMAGE063
When the unit layer is the ablation unit layer a, the ablation unit layer on the outermost layer is the ablation unit layer a; when in use
Figure 114400DEST_PATH_IMAGE064
And then, the outermost ablation unit layer is the ablation unit layer b, and the like, so that the current ablation unit layer at the outermost layer can be determined. When in use
Figure 23450DEST_PATH_IMAGE065
The ablation layer is totally ablated.
Step S203: and determining a corresponding ablation model for determining the ablation amount at the next moment according to the type of the current outermost ablation unit layer.
After the current outermost layer of the ablation unit layer is determined, the material of the current outermost layer of the ablation unit layer can be obtained, so that the type of the current outermost layer of the ablation unit layer can be determined. Types of ablative element layers include, but are not limited to, silicon-based types, carbon-based types, ceramic-based types.
After determining the type of the current outermost layer of ablation cells, a corresponding ablation model may be determined. For example, when the type of the ablation unit layer at the outermost layer is a silicon-based type, the silicon-based ablation model is selected as the ablation model; when the type of the current outermost ablation unit layer is a carbon-based type, selecting a carbon-based ablation model from the ablation model; when the type of the current outermost ablation unit layer is a ceramic-based type, the ablation model is a ceramic-based ablation model.
It should be noted that the equations for the various types of ablation models are prior art and are not listed here.
Step S204: and determining the thermophysical property parameters of the ablation unit layer at the current outermost layer according to the relationship.
For example, when the ablation unit layer at the outermost layer is the ablation unit layer a, the thermophysical property parameter of the ablation unit layer a can be determined from the relation between the thermophysical property parameter and the corresponding layer structure thickness; when the ablation unit layer at the outermost layer is the ablation unit layer c, the thermophysical property parameter of the ablation unit layer c can be determined from the relation between the thermophysical property parameter and the corresponding layer structure thickness.
Step S205: and determining the ablation amount at the next moment according to the thermophysical property parameters, the non-ablated ablation unit layer, the thermal insulation layer, the temperature of the internal temperature field of the bearing structure layer, the wall temperature, the pyrolysis gas mass flow rate and the ablation model.
And (3) substituting the thermal physical property parameters of the ablation unit layer on the outermost layer, the temperature of the internal temperature field of the ablation unit layer which is not ablated, the temperature of the internal temperature field of the thermal insulation layer, the temperature of the internal temperature field of the bearing structure layer, the wall temperature and the pyrolysis gas mass flow rate into the ablation model determined in the step (S203) to obtain the ablation amount of the next moment.
In the embodiment, the relation between the thermophysical property parameters and the corresponding layer structure thickness is respectively established for each ablation unit layer, the thermal insulation layer and the bearing structure layer in the ablation layer, the material performance of each layer is accurately described, the material temperature of the ablation layer can be influenced by the material temperature of the bearing structure layer and the thermal insulation layer, whether ablation occurs or not is determined, and the like.
Further, after all ablation quantities are obtained, the points of the ablation quantities are connected in a coordinate graph to obtain the ablation profile.
When the ablation layer of the aircraft comprises two ablation cell layers, the results of the ablation volume for two ablation cell layers sequentially ablated and one ablation cell layer are shown in fig. 6, where the abscissa is time and the ordinate is ablation volume.
On the basis of any of the foregoing embodiments, in an embodiment of the present application, before performing differential discretization on the equations of all internal temperature fields and the boundary condition, the method further includes:
converting the equations of all internal temperature fields in a fixed coordinate system and the boundary conditions of the ablation surface of the ablation layer into equations and boundary conditions in a moving coordinate system that recedes with the ablation surface;
accordingly, the differential discretization of the equations for all internal temperature fields and said boundary conditions comprises:
and carrying out differential discretization on equations of all the converted internal temperature fields and the boundary conditions.
The fixed coordinate system has its origin at the outermost surface of the ablation layer when it is not ablated and the moving coordinate system has its origin at the outermost surface of the ablation layer during ablation.
For the specific process of converting the equation in different coordinate systems, reference may be made to related technologies, which are not described in detail herein.
In the embodiment, the equation in the fixed coordinate system is converted into the moving coordinate system, and then the converted equation is used for solving, so that the calculation difficulty can be simplified.
The following describes a specific case of the processing method for the successive ablation of the multilayer heat protection structure in the present application.
Step S301: and respectively establishing the relation between the thermophysical parameters of each ablation unit layer, the heat-insulating layer and the bearing structure layer in the ablation layer and the corresponding layer structure thickness.
Step S302: according to the current ablation amount
Figure 30720DEST_PATH_IMAGE045
Determining the current outermost layer of ablation units.
Step S303: and determining a corresponding ablation model for determining the ablation amount at the next moment according to the type of the current outermost ablation unit layer.
Step S304: and determining the thermal physical property parameters of the ablation unit layer at the outermost layer according to the relationship between the thermal physical property parameters and the corresponding layer structure thickness.
Step S305: for the ablation unit layer not ablated in the ablation layer (
Figure 697325DEST_PATH_IMAGE066
) The internal temperature field is described by a one-dimensional heat conduction fundamental equation of solid materials with pyrolysis under a fixed coordinate system:
Figure 448243DEST_PATH_IMAGE067
（1）
wherein the content of the first and second substances,
Figure 211800DEST_PATH_IMAGE002
for the mass flow rate of the pyrolysis gas,
Figure 249026DEST_PATH_IMAGE003
in order to increase the rate of the pyrolysis reaction,
Figure 871769DEST_PATH_IMAGE004
is the heat of pyrolysis and is,
Figure 691957DEST_PATH_IMAGE005
the density of the layer of ablated cells for the s-th layer,
Figure 450966DEST_PATH_IMAGE006
is the specific heat capacity, k, of the layer of the s-th ablation unit s Is the thermal conductivity of the s-th ablation unit layer, T is the temperature of the internal temperature field of the non-ablated ablation unit layer, T is the ablation time,
Figure 924672DEST_PATH_IMAGE007
is the specific heat at constant pressure, and the heat,
Figure 769131DEST_PATH_IMAGE008
as the density of the gas, it is,
Figure 986486DEST_PATH_IMAGE009
is the gradient of the temperature T in the direction y of the heat transfer direction,
Figure 597072DEST_PATH_IMAGE068
，
Figure 507259DEST_PATH_IMAGE069
for the total thickness of the ablation to be,
Figure 839014DEST_PATH_IMAGE070
is the total thickness of the ablation layer.
Step S306: respectively establishing internal temperature fields for the thermal insulation layer and the bearing structure layer which are not ablated as follows:
Figure 594481DEST_PATH_IMAGE071
（2）
wherein, the first and the second end of the pipe are connected with each other,
Figure 328081DEST_PATH_IMAGE011
is the density of the thermal-insulation layer,
Figure 878011DEST_PATH_IMAGE012
is the specific heat capacity of the heat-insulating layer,
Figure 697063DEST_PATH_IMAGE013
is the thermal conductivity of the thermal insulation layer,
Figure 256220DEST_PATH_IMAGE014
is the temperature of the internal temperature field of the insulation layer,
Figure 657377DEST_PATH_IMAGE015
is temperature
Figure 64960DEST_PATH_IMAGE014
A gradient in the heat transfer direction y-direction;
Figure 636887DEST_PATH_IMAGE072
（3）
wherein, the first and the second end of the pipe are connected with each other,
Figure 734156DEST_PATH_IMAGE017
is the density of the bearing structure layer,
Figure 707928DEST_PATH_IMAGE018
is the specific heat capacity of the bearing structure layer,
Figure 740606DEST_PATH_IMAGE019
is the heat conductivity coefficient of the bearing structure layer,
Figure 393305DEST_PATH_IMAGE020
is the temperature of the internal temperature field of the bearing structure layer,
Figure 435210DEST_PATH_IMAGE021
is temperature
Figure 122543DEST_PATH_IMAGE022
Gradient in the heat transfer direction y-direction.
Figure 529385DEST_PATH_IMAGE073
Step S307: initial conditions and boundary conditions at the surface of the material and boundary conditions between functional layers are determined. The boundary conditions at the material surface are:
Figure 403800DEST_PATH_IMAGE074
（4）
wherein the content of the first and second substances,
Figure 718238DEST_PATH_IMAGE024
to account for the net heat flow from the surface of the material into the interior of the heat shield after the ablation effect,
Figure 260078DEST_PATH_IMAGE025
in order to be the radiation coefficient,
Figure 631629DEST_PATH_IMAGE026
is the Stefan-Boltzmann parameter,
Figure 258919DEST_PATH_IMAGE027
wall temperature, k, of the ablation layer s The thermal conductivity of the ablation unit layer of the s-th layer;
ablation layer to thermal barrier layer interface
Figure 377048DEST_PATH_IMAGE075
The boundary condition of heat flow and temperature is satisfied, and the interface of the heat-insulating layer and the bearing structure layer
Figure 773394DEST_PATH_IMAGE076
And boundary conditions of equal heat flow and temperature are met, and the inner surface of the heat-proof layer adopts heat insulation conditions.
Step S308: and respectively adopting coordinate transformation to convert an equation containing variables on the coordinate y in the heat transfer direction in a fixed coordinate system into a moving coordinate system which retracts along with the ablation surface.
Step S309: and performing difference dispersion on all the converted equations and boundary conditions to obtain a difference equation in a standard form as follows:
Figure 318776DEST_PATH_IMAGE077
（5）
wherein T is temperature, A, B, C, D are coefficients, corresponding to variables in the formula, the lower corner mark represents a certain time, and the upper corner mark represents a certain position.
Step S310: and solving a differential equation by adopting a three-diagonal pursuit method to obtain a temperature distribution result and a wall temperature of each layer structure of the multilayer heat-proof structure.
Step S311: and determining the ablation amount at the next moment according to the thermophysical property parameters, the temperature of the ablation unit layer which is not ablated, the temperature of the thermal insulation layer, the temperature of the internal temperature field of the bearing structure layer, the wall temperature, the pyrolysis gas mass flow rate and the ablation model.
Step S312: determining an ablation profile based on the amount of ablation.
The processing method is based on the solid material heat conduction and thermochemical ablation and pyrolysis dynamics basic equations, aiming at multiple layers of different heat-proof materials, selecting corresponding ablation models and thermophysical parameters according to ablation backing quantity and layered coordinates, processing moving boundaries through coordinate transformation, and obtaining ablation quantity and temperature distribution results of the multiple layers of heat-proof structures through difference dispersion and iterative solution, so that a basis is provided for designing a heat-proof system.
An implementation flow chart of a continuous ablation calculation model suitable for an aircraft multilayer heat protection structure is shown in FIG. 7.
The following describes a processing apparatus for continuous ablation of a multilayer thermal protection structure provided in an embodiment of the present application, and the processing apparatus for continuous ablation of a multilayer thermal protection structure described below and the processing method for continuous ablation of a multilayer thermal protection structure described above may be referred to correspondingly.
Fig. 8 is a block diagram of a processing apparatus for sequential ablation of a multilayer heat protection structure according to an embodiment of the present application, where, referring to fig. 8, the processing apparatus may include:
the first establishing module 100 is used for respectively establishing equations of internal temperature fields of an ablation unit layer, a heat insulation layer and a bearing structure layer which are not ablated in an ablation layer; the ablation unit layer is at least two layers;
a first determining module 200, configured to determine boundary conditions, where the boundary conditions include boundary conditions of the ablation layer and the thermal insulation layer, boundary conditions of the thermal insulation layer and the stressed structure layer, and boundary conditions of an ablation surface of the ablation layer; boundary conditions of the ablation surface of the ablation layer include wall temperature;
a difference discretization module 300, configured to perform difference discretization on equations of all internal temperature fields and the boundary condition to obtain a difference equation;
and the second determining module 400 is used for determining the temperatures of the ablation unit layers, the thermal insulation layers and the internal temperature fields of the bearing structure layers which are not ablated and the wall temperature according to the differential equation.
The processing apparatus for continuous ablation of a multilayer heat protection structure in this embodiment is used to implement the aforementioned processing method for continuous ablation of a multilayer heat protection structure, and therefore specific embodiments of the processing apparatus for continuous ablation of a multilayer heat protection structure can be found in the foregoing embodiments of the processing method for continuous ablation of a multilayer heat protection structure, for example, the first establishing module 100, the first determining module 200, the differential discrete module 300, and the second determining module 400 are respectively used to implement steps S101, S102, S103, and S104 in the processing method for continuous ablation of a multilayer heat protection structure, and therefore, the specific embodiments thereof may refer to descriptions of corresponding embodiments of each part, and are not described herein again.
Optionally, the method further includes:
the second establishing module is used for respectively establishing the relation between the thermophysical parameters of each ablation unit layer, the heat insulation layer and the bearing structure layer in the ablation layer and the corresponding layer structure thickness;
the third determining module is used for determining the ablation unit layer at the current outermost layer according to the current ablation amount;
a fourth determining module, configured to determine, according to the type of the ablation unit layer at the outermost layer, a corresponding ablation model for determining an ablation amount at the next time;
a fifth determining module, configured to determine a thermophysical property parameter of the ablation unit layer at the current outermost layer according to the relationship;
and the sixth determining module is used for determining the ablation amount at the next moment according to the thermophysical property parameters, the temperature of the ablation unit layer which is not ablated, the thermal insulation layer, the temperature of the internal temperature field of the bearing structure layer, the wall temperature, the pyrolysis gas mass flow rate and the ablation model.
Optionally, the first establishing module 100 includes:
a first establishing unit for establishing an equation of an internal temperature field of an ablation unit layer that is not ablated in the ablation layer as follows:
Figure 433363DEST_PATH_IMAGE078
（1）
wherein the content of the first and second substances,
Figure 355182DEST_PATH_IMAGE002
for the mass flow rate of the pyrolysis gas,
Figure 340456DEST_PATH_IMAGE003
in order to increase the rate of the pyrolysis reaction,
Figure 56739DEST_PATH_IMAGE004
is the heat of pyrolysis and is,
Figure 658622DEST_PATH_IMAGE005
the density of the layer of the s-th ablation unit,
Figure 118553DEST_PATH_IMAGE006
specific heat capacity, k, of the layer of the s-th ablation unit s Is the thermal conductivity of the s-th layer of ablation unit layer, T is the temperature of the internal temperature field of the non-ablated ablation unit layer, T is the ablation time,
Figure 489491DEST_PATH_IMAGE007
the specific heat at a constant pressure is used,
Figure 376676DEST_PATH_IMAGE008
as a result of the density of the gas,
Figure 465855DEST_PATH_IMAGE009
is the gradient of the temperature T in the direction y of the heat transfer;
a second establishing unit, configured to establish an equation of an internal temperature field of the thermal insulation layer as follows:
Figure 463898DEST_PATH_IMAGE079
（2）
wherein, the first and the second end of the pipe are connected with each other,
Figure 423763DEST_PATH_IMAGE011
the density of the thermal insulation layer is the same as,
Figure 872062DEST_PATH_IMAGE012
is the specific heat capacity of the heat-insulating layer,
Figure 61254DEST_PATH_IMAGE013
is the thermal conductivity of the thermal insulation layer,
Figure 987622DEST_PATH_IMAGE014
is the temperature of the internal temperature field of the insulation layer,
Figure 208518DEST_PATH_IMAGE015
is temperature
Figure 562139DEST_PATH_IMAGE014
A gradient in the heat transfer direction y-direction;
the third establishing unit is used for establishing an equation of an internal temperature field of the bearing structure layer as follows:
Figure 970118DEST_PATH_IMAGE080
（3）
wherein the content of the first and second substances,
Figure 965756DEST_PATH_IMAGE017
is the density of the bearing structure layer,
Figure 41159DEST_PATH_IMAGE018
is the specific heat capacity of the bearing structure layer,
Figure 565682DEST_PATH_IMAGE081
is the heat conductivity coefficient of the bearing structure layer,
Figure 460956DEST_PATH_IMAGE020
is the temperature of the internal temperature field of the bearing structure layer,
Figure 729127DEST_PATH_IMAGE082
is temperature
Figure 659037DEST_PATH_IMAGE022
Gradient in the heat transfer direction y-direction.
Optionally, the first determining module determines that the boundary condition of the ablation surface of the ablation layer is:
Figure 292143DEST_PATH_IMAGE083
（4）
wherein, the first and the second end of the pipe are connected with each other,
Figure 64927DEST_PATH_IMAGE024
in order to take account of the net heat flow introduced into the interior of the multilayer heat protection structure from the surface of the ablation layer after the ablation effect,
Figure 480996DEST_PATH_IMAGE025
in order to be the radiation coefficient,
Figure 655626DEST_PATH_IMAGE026
is the Stefan-Boltzmann parameter,
Figure 394387DEST_PATH_IMAGE027
wall temperature, k, of the ablation layer s The thermal conductivity of the s-th layer of the ablated cell layer.
Optionally, the second determining module is specifically configured to determine, according to the difference equation, the temperatures of the internal temperature fields of the ablation unit layer, the thermal insulation layer, and the carrier structure layer that are not ablated, and the wall temperature by using any one of a three-diagonal pursuit method, an LU decomposition method, and a direct matrix inversion matrix method.
Optionally, the method further includes:
the conversion module is used for converting the equations of all internal temperature fields in a fixed coordinate system and the boundary conditions of the ablation surface of the ablation layer into the equations and the boundary conditions in a moving coordinate system which shrinks along with the ablation surface;
correspondingly, the differential dispersion module is used for carrying out differential dispersion on the equations of all the converted internal temperature fields and the boundary conditions to obtain a differential equation.
In the following, the electronic device provided by the embodiment of the present application is introduced, and the electronic device described below and the processing method for continuous ablation of the multilayer heat protection structure described above may be referred to correspondingly.
An electronic device, comprising:
a memory for storing a computer program;
and the processor is used for realizing the steps of the processing method for the continuous ablation of the multilayer heat-proof structure in any embodiment when the computer program is executed.
The following describes a computer-readable storage medium provided by an embodiment of the present application, and the computer-readable storage medium described below and the processing method for sequential ablation of the multilayer heat protection structure described above may be referred to correspondingly.
A computer-readable storage medium, on which a computer program is stored, which, when executed by a processor, implements the steps of the processing method for sequential ablation of a multilayer thermal protection structure according to any one of the above embodiments.
The embodiments are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same or similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
Those of skill would further appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware, computer software, or combinations of both, and that the various illustrative components and steps have been described above generally in terms of their functionality in order to clearly illustrate this interchangeability of hardware and software. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the technical solution. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present application.
The steps of a method or algorithm described in connection with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. A software module may reside in Random Access Memory (RAM), memory, read Only Memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art.
The method, apparatus, electronic device and computer readable storage medium for processing the multilayer thermal protection structure during sequential ablation provided by the present application are described in detail above. The principles and embodiments of the present application are explained herein using specific examples, which are provided only to help understand the method and the core idea of the present application. It should be noted that, for those skilled in the art, it is possible to make several improvements and modifications to the present application without departing from the principle of the present application, and such improvements and modifications also fall within the scope of the claims of the present application.

Claims (10)

1. A processing method for continuous ablation of a multilayer heat-proof structure is characterized by comprising the following steps:
respectively establishing equations of internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated in the ablation layer; the ablation unit layer is at least two layers;
determining boundary conditions, wherein the boundary conditions comprise boundary conditions of the ablation layer and the heat-insulating layer, boundary conditions of the heat-insulating layer and the bearing structure layer, and boundary conditions of an ablation surface of the ablation layer; boundary conditions of the ablation surface of the ablation layer include wall temperature;
carrying out differential discretization on equations of all internal temperature fields and the boundary conditions to obtain a differential equation;
and determining the temperatures of the ablation unit layers, the thermal insulation layer and the internal temperature field of the bearing structure layer which are not ablated and the wall temperature according to the difference equation.
2. The method of claim 1, further comprising:
respectively establishing the relation between the thermophysical property parameters of each ablation unit layer, the heat insulation layer and the bearing structure layer in the ablation layer and the corresponding layer structure thickness;
determining the ablation unit layer at the current outermost layer according to the current ablation amount;
determining a corresponding ablation model for determining the ablation amount at the next moment according to the type of the ablation unit layer at the outermost layer;
determining the thermophysical property parameters of the ablation unit layer at the current outermost layer according to the relationship;
and determining the ablation amount at the next moment according to the thermophysical property parameters, the temperature of the ablation unit layer which is not ablated, the heat insulation layer, the temperature of the internal temperature field of the bearing structure layer, the wall temperature, the pyrolysis gas mass flow rate and the ablation model.
3. The method for processing the continuous ablation of the multilayer heat-proof structure as claimed in claim 1, wherein the equation for respectively establishing the internal temperature fields of the ablation unit layer, the heat-insulating layer and the force-bearing structure layer which are not ablated in the ablation layer comprises the following steps:
the equation for establishing the internal temperature field of the non-ablated ablation unit layers in the ablation layer is:
Figure 979708DEST_PATH_IMAGE001
wherein the content of the first and second substances,
Figure 797491DEST_PATH_IMAGE002
for the mass flow rate of the pyrolysis gas,
Figure 203196DEST_PATH_IMAGE003
in order to increase the rate of the pyrolysis reaction,
Figure 956388DEST_PATH_IMAGE004
is the heat of pyrolysis and is,
Figure 696811DEST_PATH_IMAGE005
the density of the layer of the s-th ablation unit,
Figure 928072DEST_PATH_IMAGE006
is the specific heat capacity, k, of the layer of the s-th ablation unit s Is the thermal conductivity of the s-th ablation unit layer, T is the temperature of the internal temperature field of the non-ablated ablation unit layer, T is the ablation time,
Figure 188283DEST_PATH_IMAGE007
the specific heat at a constant pressure is used,
Figure 237011DEST_PATH_IMAGE008
as the density of the gas, it is,
Figure 340096DEST_PATH_IMAGE009
is the gradient of the temperature T in the direction y of the heat transfer;
the equation for establishing the internal temperature field of the thermal insulation layer is as follows:
Figure 250414DEST_PATH_IMAGE010
wherein the content of the first and second substances,
Figure 755345DEST_PATH_IMAGE011
the density of the thermal insulation layer is the same as,
Figure 974974DEST_PATH_IMAGE012
is the specific heat capacity of the heat-insulating layer,
Figure 830934DEST_PATH_IMAGE013
is the thermal conductivity of the thermal insulation layer,
Figure 294013DEST_PATH_IMAGE014
is the temperature of the internal temperature field of the insulation layer,
Figure 919029DEST_PATH_IMAGE015
is temperature
Figure 43980DEST_PATH_IMAGE014
A gradient in the heat transfer direction y-direction;
the equation for establishing the internal temperature field of the bearing structure layer is as follows:
Figure 997024DEST_PATH_IMAGE016
wherein the content of the first and second substances,
Figure 639358DEST_PATH_IMAGE017
is the density of the bearing structure layer,
Figure 977935DEST_PATH_IMAGE018
is the specific heat capacity of the bearing structure layer,
Figure 414733DEST_PATH_IMAGE019
is the heat conductivity coefficient of the bearing structure layer,
Figure 855072DEST_PATH_IMAGE020
is the temperature of the internal temperature field of the bearing structure layer,
Figure 769939DEST_PATH_IMAGE021
is temperature
Figure 228602DEST_PATH_IMAGE022
Gradient in the heat transfer direction y-direction.
4. The method for treating the sequential ablation of the multilayer heat-proof structure according to claim 1, wherein the boundary conditions of the ablation surface of the ablation layer are as follows:
Figure 711667DEST_PATH_IMAGE023
wherein the content of the first and second substances,
Figure 763937DEST_PATH_IMAGE024
in order to take account of the net heat flow introduced into the interior of the multilayer heat protection structure from the surface of the ablation layer after the ablation effect,
Figure 607128DEST_PATH_IMAGE025
in order to be the radiation coefficient,
Figure 61243DEST_PATH_IMAGE026
is the Stefan-Boltzmann parameter,
Figure 446700DEST_PATH_IMAGE027
wall temperature, k, of the ablation layer s The thermal conductivity of the s-th layer of the ablation unit layer.
5. The method for processing the multilayer heat-proof structure during continuous ablation according to claim 1, wherein the step of determining the temperatures of the ablation unit layers, the heat-insulating layers and the internal temperature fields of the force-bearing structure layers which are not ablated and the wall temperature according to the differential equation comprises the following steps:
and determining the temperatures of the internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated and the wall temperature according to the difference equation by using any one of a three-diagonal catch-up method, an LU decomposition method and a direct matrix inversion matrix method.
6. The method for processing the sequential ablation of the multilayer heat-proof structure according to any one of claims 1 to 5, wherein before the differential discretization of the equations of all internal temperature fields and the boundary conditions, the method further comprises:
converting the equations of all internal temperature fields in a fixed coordinate system and the boundary conditions of the ablation surface of the ablation layer into equations and boundary conditions in a moving coordinate system that recedes with the ablation surface;
accordingly, the differential discretization of the equations for all internal temperature fields and said boundary conditions comprises:
and carrying out differential discretization on equations of all the converted internal temperature fields and the boundary conditions.
7. A processing device for continuous ablation of a multilayer heat-proof structure, comprising:
the first establishing module is used for respectively establishing equations of internal temperature fields of the ablation unit layer, the thermal insulation layer and the bearing structure layer which are not ablated in the ablation layer; the ablation unit layer is at least two layers;
the first determining module is used for determining boundary conditions, wherein the boundary conditions comprise boundary conditions of the ablation layer and the thermal insulation layer, boundary conditions of the thermal insulation layer and the bearing structure layer and boundary conditions of an ablation surface of the ablation layer; boundary conditions of the ablation surface of the ablation layer include wall temperature;
the difference dispersion module is used for carrying out difference dispersion on all the equations of the internal temperature field and the boundary conditions to obtain a difference equation;
and the second determination module is used for determining the temperatures of the ablation unit layers, the thermal insulation layer and the internal temperature field of the bearing structure layer which are not ablated and the wall temperature according to the difference equation.
8. The apparatus for processing in sequential ablation of a multilayer thermal structure according to claim 7, further comprising:
a conversion module for converting the equations of all internal temperature fields and boundary conditions of the ablation surface of the ablation layer in a fixed coordinate system to equations and boundary conditions in a moving coordinate system that recedes with the ablation surface;
correspondingly, the differential dispersion module is used for carrying out differential dispersion on the equations of all the converted internal temperature fields and the boundary conditions to obtain a differential equation.
9. An electronic device, comprising:
a memory for storing a computer program;
a processor for implementing the steps of the processing method for the sequential ablation of the multilayer heat-shielding structure according to any one of claims 1 to 6 when the computer program is executed.
10. A computer-readable storage medium, wherein a computer program is stored on the computer-readable storage medium, and when being executed by a processor, the computer program implements the steps of the processing method for the sequential ablation of the multilayer heat protection structure according to any one of claims 1 to 6.
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