CN115809515A - Optimal design method for multilayer heat insulation structure of high-speed aircraft - Google Patents
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- 238000009413 insulation Methods 0.000 title claims abstract description 74
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- 239000012774 insulation material Substances 0.000 claims abstract description 7
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- 239000004966 Carbon aerogel Substances 0.000 description 3
- 238000000342 Monte Carlo simulation Methods 0.000 description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
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- 239000000377 silicon dioxide Substances 0.000 description 1
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Abstract
The invention discloses an optimal design method of a high-speed aircraft multi-layer heat insulation structure, which relates to the technical field of heat insulation, wherein the high-speed aircraft heat insulation structure is divided into multiple layers of materials, and design variables, namely a selectable material database and the geometric dimensions of each layer of material, are determined; determining an optimized objective function heat insulation efficiency-mass ratio and setting constraint conditions; the optimization objective function and the constraint condition are gathered, and an optimization model is obtained according to the design variables; and solving the optimization model by adopting an intelligent optimization algorithm to obtain optimized heat insulation material selection and the geometric dimension of each layer of heat insulation material. The method introduces the material selection, the geometric dimension and the temperature change characteristic of the thermal conductivity of the material into the optimization design model to obtain the optimized material selection and the geometric dimension of the material, thereby better meeting the requirements of practical application.
Description
Technical Field
The invention relates to the technical field of heat insulation, in particular to a method for optimally designing a multilayer heat insulation structure of a high-speed aircraft.
Background
The heat insulation structure is a key factor for protecting the high-speed aircraft to safely work and complete various tasks, and the effective heat insulation structure can meet the basic requirements of heat prevention and heat insulation of the high-speed aircraft, so that the high-speed aircraft is prevented from being damaged by an extreme aerodynamic thermal environment. With the development and upgrade of the national high-speed aircraft technology, the traditional heat insulation structure is difficult to meet the requirements of low cost, light weight, integration of prevention and heat insulation and the like, so that the design of the multilayer heat insulation structure is widely concerned by various countries. The schematic diagram of the multilayer heat insulation structure of the high-speed aircraft is shown in fig. 1, the high-temperature resistant layer of the multilayer heat insulation structure is heated in a forced convection heat exchange manner in an extreme high-temperature thermal environment borne by the high-speed aircraft in flight, and meanwhile, the burning resistant layer performs radiation heat dissipation to the outer space to remove part of heat. The main heat in the remaining heat is blocked by the insulating layer, and a small part of heat is absorbed and stored by the material of the burning-resistant layer and is delivered to the base layer, and the base layer structure and the internal air perform natural convection heat exchange. The quality of the heat insulation performance of the multilayer heat insulation structure mainly depends on the material parameters of the heat insulation layer and the thickness of each layer, and the equivalent mechanical property of the whole structure is mainly determined by the material parameters of the base layer, so that the base layer is sometimes called as a bearing layer according to the function of the base layer.
At present, the optimized design of the high-speed aircraft heat insulation structure mostly considers that the thermal conductivity of materials is constant, the thermal conductivity of the materials is sensitive to temperature, the heat transfer performance changes violently along with the temperature, the thermal conductivity of the existing aircraft heat insulation material does not consider the condition along with the temperature change, the temperature change characteristic of the thermal conductivity of the heat insulation material influences the heat insulation effect, and the designed high-speed aircraft multilayer heat insulation structure does not consider the influence of the temperature on the thermal conductivity and has larger difference with the actual heat insulation performance; in addition, when the design optimization of the heat insulation structure is carried out, the current material selection is determined, the material preference is not considered, and the material selection and the size variable are not simultaneously taken into the design optimization of the heat insulation structure.
The existing optimization design method cannot simultaneously solve the problems of material optimization and structure optimization, and has large limitation.
Disclosure of Invention
The invention aims to: aiming at the optimal design of the multilayer heat insulation structure of the high-speed aircraft, a material selection design variable and a material heat conductivity temperature variation characteristic are introduced into an optimal design model, so that the problem that the optimization design method of the existing multilayer heat insulation structure of the high-speed aircraft does not consider the material optimization and the influence of the material heat conductivity temperature variation is solved.
The technical scheme adopted by the invention is as follows:
the invention relates to an optimal design method of a high-speed aircraft multi-layer heat insulation structure, the heat insulation structure of the high-speed aircraft is divided into a plurality of layers of materials,
determining design variables of the heat insulation structure, namely a selectable material database and the geometric dimensions of materials of each layer;
determining an optimized objective function heat insulation mass ratio, and setting constraint conditions;
the optimization objective function and the constraint condition are gathered, and an optimization model is obtained according to the design variables;
and solving the optimization model by adopting an intelligent optimization algorithm to obtain optimized design variables, namely optimized material selection and the geometric dimension of each layer of heat insulation material.
Further, the multilayer material specifically comprises an outer layer material, an intermediate layer material and an inner layer material, and the selectable material data are respectively
、
And
then the material database can be selected as
；
The geometric dimensions of the three layers of materials are respectively the thickness of the outer layer of material
Thickness of the interlayer Material
Thickness of inner layer material
。
Further, the optimization objective function thermal insulation efficiency-to-mass ratio, that is, the mass ratio between the thermal insulation efficiency and the thermal insulation structure, is given by the formula:
the heat insulation efficiency is the effective working time length
The thermal insulation rate is as follows:
wherein ,
is the temperature of the heat source and is,
inner wall temperature response;
the heat insulation structure comprises the following components in parts by mass:
wherein ,
the density of the material of the outer layer,
the density of the material of the intermediate layer,
is the density of the material of the inner layer,
according to the concept of the maximum heat insulation efficiency-to-mass ratio, the obtained optimization objective function is as follows:
further, the constraint conditions are specifically:
the inner layer of the heat insulation structure has the temperature of the inner surface wall at one side of the inner cavity
Time of day temperature
Is less than or equal to
；
The thickness dimension of each layer of material satisfies
、
、
, wherein ,
、
、
the upper limit of the thickness dimension of each layer of material,
、
、
the lower limit of the thickness dimension of each layer of material;
equivalent modulus
The equivalent modulus is defined as:
wherein ,
is the minimum value of the modulus body allowed,
is the modulus of the material of the outer layer,
is the modulus of the material of the intermediate layer,
is the modulus of the inner layer material;
material selection belongs to the Material data set
。
Furthermore, the temperature of the inner layer of the heat insulation structure is lower than that of the inner surface wall of one side of the internal cavity
Time of day temperature
It is necessary to solve through a heat transfer equation,
the heat transfer equation:
the boundary conditions are as follows:
wherein ,
in order to obtain the thermal conductivity of the material,
the specific heat capacity is the specific heat capacity,
it is the temperature that is set for the purpose,
as a matter of time, the time is,
is a coordinate of the space, and is,
the thermal conductivity of the material of the inner layer,
the heat exchange coefficient between the inner layer structure and the air,
is the thermal conductivity of the material of the outer layer,
the heat exchange coefficient between the outer layer structure and the air,
is the stefin-boltzmann constant,
it is the temperature of the air inside that,
the temperature of the outer wall surface of the outer layer,
either the outside air temperature or the heat source temperature.
Further, the optimization objective function and the constraint condition are aggregated to obtain an optimization design mathematical model:
the design variables are defined as:
the optimization model is defined as:
furthermore, the design variable is a mixed type of coexistence of discrete variable and continuous variable, which is a mixed design variable optimization problem, and an intelligent optimization algorithm is adopted to solve the optimization model to obtain optimized design variables, namely, the material selection variable M and the geometric dimension of the three layers of materials
、
And
the intelligent optimization algorithm is a genetic algorithm or a particle swarm algorithm.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
the invention relates to an optimal design method of a high-speed aircraft multi-layer heat insulation structure, aiming at the optimal design of the multi-layer heat insulation structure of the high-speed aircraft, the material selection, the geometric dimension and the temperature variation characteristic of the material heat conductivity are introduced into an optimal design model, the problem that the material optimization and the temperature variation influence of the material heat conductivity are not considered in the existing optimal design method of the high-speed aircraft multi-layer heat insulation structure is solved, the optimized material selection and the optimized material geometric dimension are obtained, and the requirements of practical application are better met.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and that for those skilled in the art, other relevant drawings can be obtained according to the drawings without inventive effort, wherein:
FIG. 1 is a schematic view of a high speed aircraft multi-layer insulation structure;
FIG. 2 is a flow chart of the optimization method of the present invention;
FIG. 3 is a diagram of the solution optimized using the Monte Carlo method;
FIG. 4 is a result of a solution using PSO optimization.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the detailed description and specific examples, while indicating the preferred embodiment of the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
It is to be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
As shown in fig. 2, the invention is an optimized design method of a multilayer heat insulation structure of a high-speed aircraft, the heat insulation structure of the high-speed aircraft is divided into multiple layers of materials,
determining design variables of the heat insulation structure, namely a selectable material database and the geometric dimensions of materials of each layer;
specifically, as shown in fig. 1, the multilayer material specifically includes an outer layer material, an intermediate layer material and an inner layer material, and the selectable material data are respectively
、
And
then the material database can be selected as
；
The geometric dimensions of the three layers are respectively the thickness of the outer layer material
Thickness of the interlayer Material
Thickness of inner layer material
。
Determining an optimized objective function heat insulation mass ratio, and setting constraint conditions;
specifically, the optimization objective function is a heat insulation efficiency/heat insulation structure mass ratio, and the formula is as follows:
the heat insulation efficiency is the effective working time length
The thermal insulation rate was:
wherein ,
is the temperature of the heat source,
inner wall temperature response;
the quality of the heat insulation structure is as follows:
wherein ,
the density of the material of the outer layer,
the density of the material of the intermediate layer,
is the density of the material of the inner layer,
according to the concept of the maximum heat insulation efficiency-to-mass ratio, the obtained optimization objective function is as follows:
the optimization objective function is the ratio of quality to efficiency, so the smaller the optimization result of the optimization objective function is, the better the optimization result is.
Specifically, the constraint condition is specifically:
heat insulation structureThe temperature of the inner layer is within the range of the inner surface wall of one side of the internal cavity
Time of day temperature
Is less than or equal to
；
The thickness dimension of each layer of material satisfies
、
、
, wherein ,
、
、
the upper limit of the thickness dimension of each layer of material,
、
、
the lower limit of the thickness dimension of each layer of material;
equivalent modulus
The equivalent modulus is defined as:
wherein ,
is the minimum value of the modulus body allowed,
is the modulus of the material of the outer layer,
is the modulus of the material of the intermediate layer,
is the modulus of the inner layer material;
material selection belongs to the material data set
。
Specifically, the inner layer of the heat insulation structure has the inner surface wall temperature towards one side of the internal cavity body
Time of day temperature
It needs to be solved by the heat transfer equation,
the heat transfer equation:
the boundary conditions are as follows:
wherein ,
in order to obtain the thermal conductivity of the material,
the specific heat capacity is the specific heat capacity,
is the temperature of the liquid to be treated,
as a matter of time, the time is,
is a coordinate of the space, and is,
the thermal conductivity of the material of the inner layer,
the heat exchange coefficient between the inner layer structure and the air,
is the thermal conductivity of the material of the outer layer,
the heat exchange coefficient between the outer layer structure and the air,
is the stefin-boltzmann constant,
the inside air temperature (background temperature in figure 2),
the temperature of the outer wall surface of the outer layer,
either the outside air temperature or the heat source temperature.
The partial differential equation (heat transfer equation) is solved by adopting a finite difference implicit format, and the spatial region sequence is represented by i, and the time sequence is represented by j. The space grid line and the time grid line (i, j) represent a node of a time-space, and the state of the j moment at the space position i replaces the derivative by finite difference, so that the partial differential equation is converted into a differential equation:
using taylor expansion, the finite difference expression of its derivative is:
the above two formulas are known:
the difference in partial differentiation with respect to time is:
the above results are substituted into a heat transfer differential equation, and an iterative recursion format in a discrete form can be obtained:
recur in time by 1, i.e. j becomes j +1, have
Then there are:
the above formula is a finite difference iterative recurrence formula.
The optimization objective function and the constraint condition are gathered, and an optimization model is obtained according to the design variables;
specifically, the optimization objective function and the constraint condition are aggregated to obtain an optimization design mathematical model:
the design variables are defined as:
the optimization model is defined as:
and solving the optimization model by adopting an intelligent optimization algorithm to obtain optimized design variables, namely optimized material selection and the geometric dimension of each layer of heat insulation material.
Specifically, the design variable is a mixed type of coexistence of a discrete variable and a continuous variable, and is a mixed design variable optimization problem, and an intelligent optimization algorithm is adopted to solve an optimization model to obtain an optimized design variable, namely a material selection variable M and the geometric dimension of three layers of materials
、
And
the intelligent optimization algorithm is a genetic algorithm or a particle swarm algorithm, but is not limited to such an optimization algorithm.
Example of the implementation
The optimization method is verified and analyzed by using an example. The parameter values in the optimization model are:
=0.5mm、
=3mm、
=5mm、
=50mm、
=2mm、
=5mm，
=10Gpa，
=1200℃，
=20℃，
=100 ℃, heat exchange coefficient of outer layer structure and air
= 230W/(m 2. DEG C), and the heat exchange coefficient of the inner layer structure and the air
=10 W/（m2·℃），
=300s。
Outer layer materials data set table 1:
TABLE 1 ablation resistance layer (outer layer) Material parameters (outer layer)
| Name of Material | Density (kg)·m-3） | Specific heat capacity (J. (kg. K) -1) | Thermal conductivity coefficient (W. (m. K) -1) | Young's modulus (GPa) |
| C/C composite material | 1600 | 713 | 1.6 | 22.32 |
| C/SiC composite material | 2100 | 1420 | 5 | 49.8 |
| ZrB 2-based composite material | 6300 | 430 | 53 | 490 |
Inner layer material data set:
TABLE 2 bearing layer (inner layer) Material parameters
| Name of Material | Density (kg. M-3)） | Specific heat capacity (J. (kg. K) -1) | Thermal conductivity coefficient (W. (m. K) -1) | Young's modulus (GPa) |
| Aluminum alloy 7075 | 2800 | 962 | 129.4 | 71 |
| GH4099 | 8470 | 624 | 18.9 | 175 |
| Titanium alloy TC4 | 4440 | 659 | 9.13 | 115.85 |
Interlayer material dataset:
TABLE 3 thermal barrier layer (interlayer) Material parameters
| Name of Material | Density (kg. M-3) | Specific heat capacity (J. (kg. K) -1) | Thermal conductivity coefficient (W. (m. K) -1) | Young's modulus (GPa) |
| Carbon aerogels (carbon aerogels) | 811 | 870 | 3.521505E-7T2+7.847416E-4T+1.104313 | 2.84 |
| SiO2 aerogel | 140 | 1050 | 1.135885E-10T3-2.256084E-8T2+1.640566E-5T+1.481429E-2 | 0.010 |
| SiC aerogel | 9.7 | 579 | 5.269242E-11T3-2.221319E-8T2+1.622211E-5T+2.377993E-2 | 0.013 |
And (4) optimizing and solving by adopting a Monte Carlo method to obtain 200 feasible solution optimization results, wherein the optimization results are shown in figure 3.
With PSO optimization, the population number is 50, the number of iterations is 200, and the optimization result is shown in fig. 4.
The PSO optimization method has better effect than the Monte Carlo method, and the PSO optimization method is adopted in the invention.
According to the optimization result of the PSO, the optimal value of the optimization objective function is 10.9167, and the corresponding design variables are as follows: x = (2,2,1,5.4070e-04, 0.0120, 0.0020), namely that the outer layer material is selected from C/SiC composite material, the intermediate layer material is selected from carbon aerogel, the inner layer material is selected from GH4099, the thickness of the outer layer is 5.4070e-01mm, the thickness of the intermediate layer is 12mm, and the thickness of the inner layer is 2mm.
The above description is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be made by those skilled in the art without inventive work within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope defined by the claims.
Claims (7)
1. A method for optimally designing a multilayer heat insulation structure of a high-speed aircraft is characterized in that the heat insulation structure of the high-speed aircraft is divided into multiple layers of materials,
determining design variables of the heat insulation structure, namely a selectable material database and the geometric dimensions of materials of each layer;
determining an optimized objective function heat insulation mass ratio, and setting constraint conditions;
the optimization objective function and the constraint condition are aggregated, and an optimization model is obtained according to design variables;
and solving the optimization model by adopting an intelligent optimization algorithm to obtain optimized design variables, namely optimized material selection and the geometric dimension of each layer of heat insulation material.
2. The method for optimally designing the multilayer heat insulation structure of the high-speed aircraft according to claim 1, wherein the method comprises the following steps of: the multilayer material specifically comprises an outer layer material, an intermediate layer material and an inner layer material, and the selectable material data are respectively
、
And
then, thenThe database of selectable materials is
；
The geometric dimensions of the three layers are respectively the thickness of the outer layer material
Thickness of the interlayer Material
Thickness of inner layer material
。
3. The method for optimally designing the multilayer heat insulation structure of the high-speed aircraft according to claim 2, wherein the optimal objective function is the heat insulation efficiency-to-mass ratio of the heat insulation structure, and the formula is as follows:
the heat insulation efficiency is the effective working time length
The thermal insulation rate was:
wherein ,
is the temperature of the heat source,
inner wall temperature response;
the heat insulation structure comprises the following components in parts by mass:
wherein ,
the density of the material of the outer layer,
the density of the material of the intermediate layer,
is the density of the material of the inner layer,
according to the concept of the maximum heat insulation efficiency-to-mass ratio, the obtained optimization objective function is as follows:
4. the method for optimally designing the multilayer heat insulation structure of the high-speed aircraft according to claim 3, wherein the constraint conditions are specifically as follows:
the inner layer of the heat insulation structure has the temperature of the inner surface wall at one side of the inner cavity
Time of day temperature
Is less than or equal to
；
The thickness dimension of each layer of material satisfies
、
、
, wherein ,
、
、
the upper limit of the thickness dimension of each layer of material,
、
、
the lower limit of the thickness dimension of each layer of material;
equivalent modulus
The equivalent modulus is defined as:
wherein ,
is the minimum value of the modulus body allowed,
is the modulus of the material of the outer layer,
is the modulus of the material of the intermediate layer,
is the modulus of the inner layer material;
material selection falls within material dataCollection
。
5. The method for optimally designing the multilayer heat insulation structure of the high-speed aircraft according to claim 4, wherein the temperature of the inner surface wall of the inner layer of the heat insulation structure on one side of the inner cavity is within the range of the temperature of the inner surface wall on one side of the inner cavity
Time of day temperature
It is necessary to solve through a heat transfer equation,
the heat transfer equation:
the boundary conditions are as follows:
wherein ,
in order to obtain the thermal conductivity of the material,
the specific heat capacity is the specific heat capacity,
is the temperature of the liquid to be treated,
in the form of a time, the time,
is a coordinate of the space, and is,
the thermal conductivity of the material of the inner layer,
the heat exchange coefficient between the inner layer structure and the air,
is the thermal conductivity of the material of the outer layer,
the heat exchange coefficient between the outer layer structure and the air,
is the stefin-boltzmann constant,
it is the temperature of the air inside that,
the temperature of the outer wall surface of the outer layer,
either the outside air temperature or the heat source temperature.
6. The method for optimally designing the multilayer heat insulation structure of the high-speed aircraft according to claim 4, wherein the optimization objective function and the constraint conditions are combined to obtain an optimal design mathematical model:
the design variables are defined as:
the optimization model is defined as:
7. the method for optimally designing the multilayer heat insulation structure of the high-speed aircraft according to claim 6, wherein the method comprises the following steps of: the design variable is a mixed type of coexistence of discrete variable and continuous variable, is a mixed design variable optimization problem, and adopts an intelligent optimization algorithm to carry out optimization model solution to obtain optimized design variables, namely a material selection variable M and the geometric dimension of three layers of materials
、
And
the intelligent optimization algorithm is a genetic algorithm or a particle swarm algorithm.
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| CN116052820A (en) * | 2023-03-22 | 2023-05-02 | 中国空气动力研究与发展中心计算空气动力研究所 | Material thermal performance evaluation method, device, equipment and readable storage medium |
| CN117634313A (en) * | 2023-12-15 | 2024-03-01 | 浙江阿斯克建材科技股份有限公司 | Heat insulation material modularized design method and system |
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