CN112632772A - Extreme environment-oriented multifunctional collaborative design method for thermal protection material - Google Patents
Extreme environment-oriented multifunctional collaborative design method for thermal protection material Download PDFInfo
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Abstract
The invention relates to the field of aerospace thermal protection, and discloses a multifunctional collaborative design method for a thermal protection material for extreme environments, which comprises the following steps: step one, establishing a high-fidelity theoretical analysis model of the performance of the thermal protection material; step two, establishing a heat-proof/heat-insulation/light-weight integrated collaborative design parameter of the thermal protection material; establishing a heat-proof/heat-insulation/light-weight integrated performance collaborative analysis model of the thermal protection material to form a thermal protection material multifunctional collaborative design platform; and fourthly, aiming at two typical extreme pneumatic thermal environments faced by the next generation of hypersonic aircrafts after entering or returning, designing a thermal protection material with high thermal protection efficiency by adopting a built multifunctional thermal protection material collaborative design platform in the concrete pneumatic thermal load requirement and the thermal protection system performance requirement, and customizing the novel multifunctional thermal protection material meeting the aircraft application environment and performance requirement according to the requirement.
Description
Technical Field
The invention relates to the field of aerospace thermal protection, in particular to a multifunctional collaborative design method for a thermal protection material facing an extreme environment.
Background
The new generation of high supersonic aircraft such as deep space exploration, interplanetary navigation and return reentry face more severe aerodynamic thermal environments (high enthalpy, extremely high heat flow, high pressure and the like), and under the dual constraint conditions of high effective load and limited space, the thermal protection material provides a severe challenge to the heat resistance, the thermal insulation capability and the light weight level. The problems that the existing thermal protection material is serious in ablation retreat, severe in back temperature rise, redundant in weight and the like exist under the harsh working condition, a design method of a novel multifunctional thermal protection material based on the overall consideration of the thermal protection/thermal insulation/lightweight performance is urgently needed to be provided, the thermal protection/thermal insulation/lightweight integrated collaborative design capacity of the thermal protection material is improved, the thermal protection material facing to the extremely complex application environment and performance requirements is customized as required, and the development of the thermal protection material is promoted.
At present, the design and development mode of the thermal protection material in China still stays at a trial-and-error method and a semi-empirical stage, the thermal protection material is designed mainly by adopting a technical means with tests as main and numerical analysis as auxiliary, the thermal protection material is designed according to the calculation result of a single thermal field of an engineering model, the research and development cost is high, the period is long, the overall consideration of the heat-proof/heat-insulation/light-weight synergetic performance of the material is lacked, and the design of the integrated thermal protection material is not based on data. How to realize the multifunctional collaborative design of the thermal protection material facing the extreme environment, improve the design level of the thermal protection material, shorten the development period of new materials and reduce the cost is yet to be solved.
Disclosure of Invention
The invention provides an extreme environment-oriented multifunctional collaborative design method for a thermal protection material, which aims to improve the design level of the thermal protection material, remarkably shorten the development period of a new material, reduce the cost and promote the conversion and application of the new thermal protection material on a next generation hypersonic aircraft thermal protection system.
In order to solve the defects in the prior art, the invention provides a design parameter of thermal protection/heat insulation/lightweight level synergistic performance, namely a specific efficiency factor, of a thermal protection material based on a thermal protection theory, a numerical analysis method, a pneumatic thermodynamic theory and the like, provides a multifunctional synergistic design method of the thermal protection material for extreme environments, and realizes the customization of a novel multifunctional thermal protection material applied to a next generation hypersonic aircraft thermal protection system according to requirements.
A multifunctional collaborative design method for a thermal protection material facing an extreme environment is disclosed, the general technical scheme is shown in figure 1, and the method comprises the following steps:
step one, considering the real physical and chemical process of the material in an extreme environment, and establishing a high-fidelity theoretical analysis model of the performance of the thermal protection material;
step two, establishing a heat-proof/heat-insulation/light-weight integrated collaborative design parameter of the thermal protection material;
organically combining a high-fidelity theoretical analysis model of the performance of the thermal protection material with the multifunctional integrated collaborative design parameters, establishing a thermal protection material heat-proof/heat-insulation/lightweight integrated performance collaborative analysis model, forming a brand-new design method of the thermal protection material based on specific efficiency factors, developing a modularized computer program, and forming a thermal protection material multifunctional collaborative design platform;
and fourthly, aiming at two typical extreme pneumatic thermal environments faced by the next generation of hypersonic aircrafts after entering or returning, designing a thermal protection material with high thermal protection efficiency by adopting a built thermal protection material multifunctional collaborative design platform aiming at specific pneumatic thermal load (heat flow, enthalpy, pressure, oxygen content and the like) requirements and thermal protection system performance requirements, and realizing customization of the novel multifunctional thermal protection material meeting the aircraft application environment and performance requirements as required.
Further, in the step one, the real physical and chemical process of the material in the extreme environment comprises the steps of base pyrolysis and pyrolysis gas generation, pyrolysis gas flowing, material heat and mass transfer, base pyrolysis and carbonization, ablation and retreat of the surface of the thermal protection material, and pyrolysis gas thermal blocking effect, wherein the parameter phi in the boundary condition reflects the thermal blocking coefficient.
Further, in the step one, a mass conservation equation reflecting the pyrolysis of the matrix and the generation of the pyrolysis gas is as follows:
the conservation of momentum equation reflecting the flow of pyrolysis gas is:
the energy conservation equation reflecting the pyrolysis and carbonization of the thermal protection material matrix and the heat and mass transfer of the material, namely the gas/solid phase heat and mass transfer, in the extreme environment is as follows:
the heat and mass transfer process of the material comprises the heat and mass transfer of a solid skeleton of the material and the heat and mass transfer of pyrolysis gas generated after the material is heated.
The boundary conditions reflecting the ablation recession of the surface of the thermal protection material are as follows:
in the formula:
ρ、v、Π、K、μ、p、cp、T、k、φ、qcold、n、mCand Δ hCVolume fraction, density, velocity tensor, pyrolysis gas generation rate, permeability tensor, viscosity coefficient, pressure tensor, specific heat capacity, temperature, heat conductivity tensor, thermal blockage coefficient, cold wall heat flow tensor, normal unit vector of material surface, ablation rate of surface carbon quantity and carbon combustion heat, subscripts g, s and gammawRespectively representing pyrolysis gas, solid phase material and material surface.
Further, the specific method in the second step is to establish a thermal protection efficiency function describing the thermal protection/insulation/lightweight synergistic performance of the material according to the specific ballistic environment, the aircraft payload and the limited space constraint condition of the thermal protection layer and the thermal protection performance requirements of specific application cases, wherein the thermal protection efficiency function is a function of the key thermal physical properties of the material, the material response and the key manufacturing process parameters:
j ═ f (thermophysical parameters, material response, manufacturing process)
On the basis, a design parameter capable of comprehensively evaluating the heat-proof/heat-insulation/light-weight level synergistic performance of the novel thermal protection material, namely a specific efficiency factor, is provided, and is defined as follows: the thermal protection efficiency of the material per unit mass, i.e. SE ═ J ρ.
Further, in step three, as shown in fig. 2, a schematic diagram of the multifunctional collaborative design platform for thermal protection material of the present invention is shown, the multifunctional collaborative design platform for thermal protection material is composed of 4 modules, which are respectively: (1) the device comprises a pretreatment and visualization module, (2) a material performance database module, (3) a core calculation module and (4) a post-treatment and visualization module.
Further, the preprocessing and visualization module is used for 1) parametric modeling of materials with different size and shape characteristics; 2) carrying out structured/unstructured gridding on the material geometric model; 3) visually displaying the complex material model; the material performance database module is used for 1) calling the room temperature to high temperature heat transport performance parameters of the composite materials of different systems; 2) calling thermodynamic performance parameters from room temperature to high temperature of the composite material of different systems; 3) calling pyrolysis reaction kinetic parameters of composite materials of different systems and thermal physical property parameters of pyrolysis gas from room temperature to high temperature; the core computing module is used for 1) dispersing the high-fidelity theoretical analysis model of the performance of the thermal protection material to form a numerical model, and solving the high-fidelity theoretical analysis numerical model by compiling computer codes; 2) dispersing the heat protection material heat prevention/insulation/lightweight integrated performance collaborative analysis model to form a numerical model, and writing computer codes to solve the integrated performance collaborative analysis numerical model; the post-processing and visualization module is used for 1) outputting the ablation retreating amount of the surface of the thermal protection material and visually displaying the deformation process of the material; 2) outputting data of a temperature field, a pressure field and a pyrolysis gas velocity field of the thermal protection material, visually displaying a three-dimensional cloud picture of the thermal-flow field of the material and a two-dimensional cloud picture of the thermal-flow field of the material section, and outputting a thermal protection efficiency calculation result for evaluating the thermal protection/heat insulation/light weight integration performance of the material.
Furthermore, the use method of the multifunctional collaborative design platform for the thermal protection material comprises the following steps: firstly, generating a material geometric and grid model by utilizing a pretreatment and visualization module; secondly, calling thermal physical and thermal chemical performance parameters of the specific material through a material performance database module; then, a core calculation module is used for solving a high-fidelity theoretical analysis model of the performance of the heat-insulation protective material and a heat-proof/heat-insulation/light-weight integrated performance collaborative analysis model, numerically simulating the response of the material and evaluating the heat-proof/heat-insulation/light-weight integrated performance; and finally, displaying and analyzing the results of ablation retreat, temperature, pressure, speed and thermal protection efficiency reflecting the thermal protection/heat insulation/light weight integration performance of the material surface by adopting a post-processing and visualization module.
Further, in the third step, the method for organically combining the high-fidelity theoretical analysis model of the performance of the thermal protection material and the multifunctional integrated collaborative design parameters comprises the following steps: firstly, establishing a high-fidelity theoretical analysis model of the performance of the thermal protection material, which comprises the following steps: a mass conservation equation reflecting the process of matrix pyrolysis and pyrolysis gas generation, a momentum conservation equation reflecting the process of pyrolysis gas flow, an energy conservation equation reflecting the process of pyrolysis and carbonization of a thermal protection material under extreme environment, gas/solid phase heat and mass transfer, and boundary conditions reflecting ablation recession of the surface of the material, wherein the high-fidelity model is a premise for analyzing the thermal protection and heat insulation performance of the material, secondly, a thermal protection efficiency function and a specific efficiency factor describing the performance of the thermal protection/heat insulation/light weight system of the material are provided and established, the thermal protection efficiency and the specific efficiency factor are related to intrinsic characteristics (thermophysical parameters and manufacturing process) of the material on one hand and material response obtained by calculation of a high-fidelity theoretical analysis model on the other hand, then, the high-fidelity theoretical analysis model and the thermal protection efficiency function are combined to form a nonlinear tight coupling equation set, and (4) carrying out discretization and decoupling on the equation set, and realizing numerical simulation of the heat-proof/heat-insulation/light-weight integrated performance of the thermal protection material.
Further, by adopting the brand new thermal protection material design platform in the third step, the thermal protection material thermal protection/thermal insulation/lightweight performance analysis of various material systems can be realized, and a design scheme corresponding to the high-performance thermal protection material is provided, wherein the scheme parameters comprise: fiber/matrix type, fiber/matrix volume fraction, porosity, fiber/matrix blend ratio, heterogeneous material density distribution profile.
Fig. 3 is a flow chart of the multifunctional thermal protection material customized according to needs, and as shown in fig. 3, in step four, the design of the thermal protection material with high thermal protection efficiency by using the built multifunctional thermal protection material collaborative design platform includes the following steps: firstly, determining the back temperature rise, the surface ablation retreating amount and the quality parameters of a thermal protection material according to the pneumatic thermal environment faced by the hypersonic aircraft when the hypersonic aircraft enters or returns and enters and the design limit of a thermal protection system; secondly, use the multi-functional collaborative design platform of thermal protection material to evaluate the novel thermal protection material of design, new material design scheme includes: 1) the material system is regulated and controlled by changing the types of fibers/matrixes, and an optimal material system suitable for a target environment is searched; 2) the hybrid thermal protection materials in different fiber/matrix combination forms are obtained by adjusting the fiber/matrix mixing ratio, and the integration performance is improved by regulating and controlling the hybrid mode; 3) designing a heterogeneous thermal protection material, and improving the lightweight performance of the material by regulating and controlling the material manufacturing process distribution mode in the thickness direction of the thermal protection layer; 4) controlling the volume fraction and porosity of fibers/matrixes in different areas of the material, and regulating and controlling the heat-proof/heat-insulating performance of the material; then, analyzing the heat-proof/heat-insulation/light-weight synergistic performance of the design material based on the simulation result of the multifunctional synergistic design platform of the thermal protection material; and finally, providing a multifunctional collaborative design optimization scheme of the thermal protection material by adopting an optimization algorithm and a sensitivity analysis method.
Further, in the fourth step, the next generation enters or returns to enter the hypersonic aircraft to face two types of typical extreme aerodynamic thermal environments, namely deep space exploration, the interstellar navigation aircraft enters the environment comprising planets of the solar system of the asterias and the asterias, and the environment faced by the planets of the asterias and returns to enter the aircraft again.
Further, the environment faced by the next generation of hypersonic vehicles, entering or returning to, includes 10-40MW/m2The environment facing the environment of Mars detection, return and reentry aircraft comprises 10-60MJ/kg high enthalpy and peak heat flow<6MW/m2Low heat flow, long time environment of more than 200 s.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides an extreme environment-oriented multifunctional collaborative design method for a thermal protection material, which aims to improve the design level of the thermal protection material, remarkably shorten the development period of a new material, reduce the cost and promote the conversion and application of the new thermal protection material on a next generation hypersonic aircraft thermal protection system.
According to the invention, the built multifunctional collaborative design platform of the thermal protection material is adopted to design the thermal protection material with high thermal protection efficiency, so that the novel multifunctional thermal protection material meeting the requirements of the application environment and performance of the aircraft can be customized according to the requirement.
Drawings
FIG. 1 is a flow chart of a multifunctional collaborative design method of an extreme environment-oriented thermal protection material according to the present invention;
FIG. 2 is a multi-functional co-design platform for thermal protective materials of the present invention;
FIG. 3 is a flow chart of the multi-functional thermal protective material customization on demand;
FIG. 4 is a schematic diagram of the physicochemical process of the phenolic resin-based composite material in the extreme environment of example 1;
FIG. 5 shows the design of the multifunctional thermal protective material of example 1;
FIG. 6 is a comparison of the thermal/weight reduction synergy of the different design materials of FIG. 5, wherein the left ordinate represents the areal density (kg/m)2) The right ordinate represents the surface receding thickness (mm) and the back surface temperature (K) in the order from left to right.
Detailed Description
The technical solutions in the embodiments of the present invention are clearly and completely described below with reference to the drawings in the embodiments of the present invention, but it should be understood that the scope of the present invention is not limited by the specific embodiments.
Example 1
Taking a phenolic resin-based thermal protection composite material as an example, when the material is subjected to pneumatic heating in an extreme environment, the physical and chemical behaviors of the material in a section parallel to the thickness direction of the material are shown in fig. 4, namely, a base body generates a pyrolysis reaction to release pyrolysis gas consisting of hydrocarbon, the pyrolysis gas flows to a boundary layer under the driving of a pressure gradient and forms a thermal blockage effect, layering (an original layer, a pyrolysis layer and a carbonization layer) occurs inside the material, oxidizing gas in the boundary layer and carbon on the surface of the material generate a chemical reaction to cause ablation and retreat of the surface of the material, and heat and mass transfer in the material simultaneously acts on porous carbon and pyrolysis gas. In order to exert the heat-proof/heat-insulation/light-weight multifunctional integrated capacity of the material, the embodiment provides a design scheme of a novel heat-protection material with a compact area and a light area, and the design scheme comprises the following steps of designing key manufacturing process parameters of the compact area and the light area: the fiber/matrix volume fraction, porosity and thickness distribution realize the multifunctional collaborative design of the novel thermal protection material.
The specific process is as follows: firstly, establishing a mass conservation equation reflecting the matrix pyrolysis and pyrolysis gas generation process:
establishing a momentum conservation equation reflecting the flow process of the pyrolysis gas:
establishing an energy conservation equation reflecting the pyrolysis and carbonization processes of the thermal protection material and the gas/solid phase heat and mass transfer under the extreme environment:
introducing a thermal protection efficiency function J (J ═ f (thermophysical parameters, material response and manufacturing process)) and comprehensively evaluating the design parameter of the synergistic performance of the thermal protection/insulation/lightweight level of the material, namely a specific efficiency factor SE
And simultaneously establishing boundary conditions reflecting ablation retreat of the material surface and thermal blocking effect of pyrolysis gas:
the equations form a nonlinear tight coupling equation set, the equation set is dispersed, computer codes are compiled to realize nonlinear numerical equation set decoupling, real physical and chemical process numerical simulation of the thermal protection material in the extreme environment is carried out, and the brand new thermal protection material multifunctional collaborative design based on specific efficiency factors is realized.
The specific efficiency factor is a new concept provided by the invention, is a function of the intrinsic performance of the material and the response of the material, and is closely coupled with a high-fidelity analysis model of the performance of the thermal protection material to realize the evaluation of the heat-proof/heat-insulation/light-weight synergistic performance.
In this embodiment, the design thickness of the thermal protection system material is required to be limited to 50mm, and the environmental parameters are: heat flow 0.515MW/m2Pressure 0.35atm, time 500 s. Regulating and controlling the distribution form of the material density, porosity and fiber volume fraction along the thickness direction, providing 7 resin-based composite material design schemes, wherein 7 resin-based composite material matrixes are all phenolic resin-based composite materials, in the example, the design thickness of the material is limited to 50mm, the ablation retreating amount of the surface of the material is limited to be within 16mm, under the design limit condition, when the design schemes of the fiber volume fraction and the initial porosity of different compact areas and light areas are evaluated by adopting a design platform, the heat-proof/heat-insulation/light-weight integrated performance of the material is realized, and on the basis, the thickness values of different areas are regulated, and the material light-weight regulation is carried out.
As shown in fig. 5. Wherein, the scheme 1 is a homogeneous thermal protection material, the fiber volume fraction is 41.67 percent, and the porosity is 7.51 percent; schemes 2-7 are heterogeneous thermal protection material schemes, in order to play a heat prevention/insulation/lightweight multifunctional synergistic capability, the heat prevention capability is played through a compact area directly contacting with an aerodynamic thermal environment, the heat insulation capability is played through a material inner layer which is a light area, lightweight performance regulation and control are realized through thickness distribution of different areas, the thicknesses of the compact areas in the schemes 2-7 are respectively 16mm, 20mm, 24mm, 28mm, 32mm and 36mm, the fiber volume fraction of the compact areas is 41.67%, the initial porosity is 7.51%, the fiber volume fraction of the light areas is 15.00%, and the initial porosity is 0%. The fiber volume fractions and the initial porosities of the compact area and the light area are designed values, the thickness is limited to 50mm according to the design of the material, the ablation retreat amount of the surface of the material is limited within 16mm, and the fiber volume fractions and the initial porosities of the compact area and the light area which meet the conditions can be calculated by adopting a design platform under the design limit conditions.
Aiming at the typical extreme aerodynamic heat environment faced by the new generation Mars detection, return and reentry hypersonic flight vehicle, namely high enthalpy (10-60 MJ/kg) and low heat flow (peak heat flow)<6MW/m2) And for a long time (>200s) environment, adopting a developed brand new heat protection material heat prevention/insulation/lightweight multifunctional collaborative design platform under different aerodynamic heat loads (heat flow, enthalpy, pressure, oxygen content and the like), analyzing the heat prevention/insulation/lightweight integrated performance of materials in different design schemes, and reflecting the heat prevention, insulation and lightweight performance of the materials through surface density, surface receding thickness and back surface temperature, as shown in figure 6. Evaluating the integrated thermal protection performance of the materials of each design scheme by adopting specific efficiency factors, and finally determining the scheme 4 as the design with the highest thermal protection efficiency under the working conditions, wherein the areal density of the four-phenolic resin matrix composite material is as follows: 65.9588kg/m2Surface receding thickness: 15.83mm, backside temperature: 613.9537K, and provides a design scheme of the novel thermal protection material with the highest thermal protection efficiency within the range of 50mm of the design space, and indexes comprise: fiber/matrix type, fiber/matrix volume fraction, porosity, dense and light zone thickness, etc.
Finally, the above disclosure is only one specific embodiment of the present invention, which is provided for the purpose of illustrating the technical solutions of the present invention and not for limiting the same, and it should be understood by those skilled in the art that modifications and equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of the technical solutions of the present invention should be covered by the claims of the present invention.
Claims (10)
1. A multifunctional collaborative design method for a thermal protection material facing an extreme environment is characterized by comprising the following steps:
step one, considering the real physical and chemical process of the material in an extreme environment, and establishing a high-fidelity theoretical analysis model of the performance of the thermal protection material;
step two, establishing a heat-proof/heat-insulation/light-weight integrated collaborative design parameter of the thermal protection material;
organically combining a high-fidelity theoretical analysis model of the performance of the thermal protection material with the multifunctional integrated collaborative design parameters, establishing a thermal protection material heat-proof/heat-insulation/lightweight integrated performance collaborative analysis model, forming a brand-new design method of the thermal protection material based on specific efficiency factors, developing a modularized computer program, and forming a thermal protection material multifunctional collaborative design platform;
and fourthly, aiming at two typical extreme pneumatic thermal environments faced by the next generation of hypersonic aircrafts after entering or returning, designing a thermal protection material with high thermal protection efficiency by adopting a built multifunctional thermal protection material collaborative design platform in the concrete pneumatic thermal load requirement and the thermal protection system performance requirement, and customizing the novel multifunctional thermal protection material meeting the aircraft application environment and performance requirement according to the requirement.
2. The multifunctional collaborative design method for the extreme environment-oriented thermal protection material according to claim 1, wherein in the step one, the actual physical and chemical processes of the material in the extreme environment include matrix pyrolysis and pyrolysis gas generation, pyrolysis gas flow, material heat and mass transfer, matrix pyrolysis and carbonization, pyrolysis gas thermal blocking effect, and thermal protection material surface ablation recession.
3. The multifunctional collaborative design method for the extreme environment-oriented thermal protection material according to claim 2, wherein a mass conservation equation reflecting matrix pyrolysis and pyrolysis gas generation is as follows:
the conservation of momentum equation reflecting the flow of pyrolysis gas is:
the energy conservation equation reflecting the pyrolysis and carbonization of the thermal protection material matrix and the heat and mass transfer of the material in the extreme environment is as follows:
the boundary conditions reflecting the ablation recession of the surface of the thermal protection material are as follows:
in the formula:
ρ、v、Π、K、μ、p、cp、T、k、φ、qcold、n、mCand Δ hCVolume fraction, density, velocity tensor, pyrolysis gas generation rate, permeability tensor, viscosity coefficient, pressure tensor, specific heat capacity, temperature, heat conductivity tensor, thermal blockage coefficient, cold wall heat flow tensor, normal unit vector of material surface, ablation rate of surface carbon quantity and carbon combustion heat, subscripts g, s and gammawRespectively representing pyrolysis gas, solid phase material and material surface.
4. The multifunctional collaborative design method for extreme environment-oriented thermal protection materials according to claim 1, wherein the specific method in the second step is to establish a thermal protection efficacy function describing the thermal protection/insulation/lightweight collaborative performance of the material according to the specific ballistic environment, the aircraft payload and the limited space constraint conditions of the thermal protection layer, in combination with the thermal protection, insulation and lightweight performance requirements of the specific application case, the thermal protection efficacy function being a function of the key thermophysical properties of the material, the material response and the key manufacturing process parameters:
j ═ f (thermophysical parameters, material response, manufacturing process)
On the basis, a design parameter, namely a specific efficiency factor, capable of comprehensively evaluating the heat-proof/heat-insulation/light-weight level synergistic performance of the novel thermal protection material is providedDefined as: thermal protection of materials per unit mass, i.e.
5. The multifunctional collaborative design method for the thermal protection material facing the extreme environment according to claim 1, wherein in step three, the multifunctional collaborative design platform for the thermal protection material is composed of 4 modules, which are respectively: (1) the device comprises a pretreatment and visualization module, (2) a material performance database module, (3) a core calculation module and (4) a post-treatment and visualization module.
6. The multifunctional collaborative design method for the extreme environment-oriented thermal protection material according to claim 5, wherein the preprocessing and visualization module is used for 1) parametric modeling of materials with different size and shape characteristics; 2) carrying out structured/unstructured gridding on the material geometric model; 3) visually displaying the complex material model; the material performance database module is used for 1) calling the room temperature to high temperature heat transport performance parameters of the composite materials of different systems; 2) calling thermodynamic performance parameters from room temperature to high temperature of the composite material of different systems; 3) calling pyrolysis reaction kinetic parameters of composite materials of different systems and thermal physical property parameters of pyrolysis gas from room temperature to high temperature; the core computing module is used for 1) dispersing the high-fidelity theoretical analysis model of the performance of the thermal protection material to form a numerical model, and solving the high-fidelity theoretical analysis numerical model by compiling computer codes; 2) dispersing the heat protection material heat prevention/insulation/lightweight integrated performance collaborative analysis model to form a numerical model, and writing computer codes to solve the integrated performance collaborative analysis numerical model; the post-processing and visualization module is used for 1) outputting the ablation retreating amount of the surface of the thermal protection material and visually displaying the deformation process of the material; 2) outputting data of a temperature field, a pressure field and a pyrolysis gas velocity field of the thermal protection material, visually displaying a three-dimensional cloud picture of the thermal-flow field of the material and a two-dimensional cloud picture of the thermal-flow field of the material section, and outputting a thermal protection efficiency calculation result for evaluating the thermal protection/heat insulation/light weight integration performance of the material.
7. The extreme environment-oriented multifunctional collaborative design method for the thermal protection material is characterized in that the use method of the platform comprises the following steps: firstly, generating a material geometric and grid model by utilizing a pretreatment and visualization module; secondly, calling thermal physical and thermal chemical performance parameters of the specific material through a material performance database module; then, a core calculation module is used for solving a high-fidelity theoretical analysis model of the performance of the heat-insulation protective material and a heat-proof/heat-insulation/light-weight integrated performance collaborative analysis model, numerically simulating the response of the material and evaluating the heat-proof/heat-insulation/light-weight integrated performance; and finally, displaying and analyzing the results of ablation retreat, temperature, pressure, speed and thermal protection efficiency reflecting the thermal protection/heat insulation/light weight integration performance of the material surface by adopting a post-processing and visualization module.
8. The multifunctional collaborative design method for the thermal protection material facing the extreme environment as recited in claim 1, wherein a brand new thermal protection material design platform of step three is adopted, so that the thermal protection material thermal protection/insulation/lightweight performance analysis of multiple material systems can be realized, and a design scheme corresponding to a high-performance thermal protection material is given, and the scheme parameters include: fiber/matrix type, fiber/matrix volume fraction, porosity, fiber/matrix blend ratio, heterogeneous material density distribution profile.
9. The multifunctional collaborative design method for the thermal protection material facing the extreme environment according to claim 8, wherein in the fourth step, the step of designing the thermal protection material with high thermal protection efficiency by using the built multifunctional collaborative design platform for the thermal protection material comprises the following steps: firstly, determining the back temperature rise, the surface ablation retreating amount and the quality parameters of a thermal protection material according to the pneumatic thermal environment faced by the hypersonic aircraft when the hypersonic aircraft enters or returns and enters and the design limit of a thermal protection system; secondly, use the multi-functional collaborative design platform of thermal protection material to evaluate the novel thermal protection material of design, new material design scheme includes: 1) the material system is regulated and controlled by changing the types of fibers/matrixes, and an optimal material system suitable for a target environment is searched; 2) the hybrid thermal protection materials in different fiber/matrix combination forms are obtained by adjusting the fiber/matrix mixing ratio, and the integration performance is improved by regulating and controlling the hybrid mode; 3) designing a heterogeneous thermal protection material, and improving the lightweight performance of the material by regulating and controlling the material manufacturing process distribution mode in the thickness direction of the thermal protection layer; 4) controlling the volume fraction and porosity of fibers/matrixes in different areas of the material, and regulating and controlling the heat-proof/heat-insulating performance of the material; then, analyzing the heat-proof/heat-insulation/light-weight synergistic performance of the design material based on the simulation result of the multifunctional synergistic design platform of the thermal protection material; and finally, providing a multifunctional collaborative design optimization scheme of the thermal protection material by adopting an optimization algorithm and a sensitivity analysis method.
10. The multifunctional collaborative design method for the extreme environment-oriented thermal protection material according to claim 1, wherein in step four, the two typical extreme aerodynamic thermal environments faced by the next generation of hypersonic vehicles for entering or returning are deep space exploration, interstellar navigation aircraft entering environments faced by planets including planets of the solar system of the asterias and the asterias, and environments faced by mars exploration, returning and reentry aircraft; preferably, the environment that the next generation of entering or returning to re-entering hypersonic aircraft faces includes 10-40MW/m2The environment facing the environment of Mars detection, return and reentry aircraft comprises 10-60MJ/kg high enthalpy and peak heat flow<6MW/m2Low heat flow, long time environment of more than 200 s.
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