Aerothermo-chemical ablation matching coupling simulation design method
By using the aerodynamic thermal ablation matching coupling simulation design method, the problem of ablation matching and aerodynamic thermal coupling at the joint of heat protection materials was solved, achieving efficient and accurate calculation and shape continuity, thus ensuring the design of the aircraft's thermal protection system.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-14
- Publication Date
- 2026-03-24
AI Technical Summary
In the prior art, the difference in pyrolysis ablation rate at the overlapping parts of different types of heat-resistant materials leads to problems of material ablation matching and aerodynamic-thermal coupling, affecting the continuity of the aircraft's shape.
The aerodynamic thermal ablation matching coupling simulation design method is adopted. Through three-dimensional aerodynamic thermal simulation, ablation simulation analysis and ablation shape modeling, the ablation amount and thermal environment of different heat protection material overlap parts are calculated, and the ablation deterioration factor is iteratively optimized to match the ablation amount of flight test.
It enables accurate and efficient calculation of the overlapping parts of different heat-resistant materials, reduces the number of iterations, improves calculation efficiency, and ensures the continuity of the aircraft's shape and the effectiveness of the thermal protection system.
Smart Images
Figure CN119918186B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to an aerodynamic thermal ablation matched coupling simulation design method, which is applicable to the simulation and design of aerodynamic thermal and thermal protection systems for high-speed aircraft, and belongs to the field of aerodynamic thermal and thermal protection. Background Technology
[0002] When an aircraft flies at high speed within the atmosphere, it experiences intense friction with the surrounding air and strong compression of the air in front. Under the combined effects of viscous dissipation and shock wave compression, a large amount of kinetic energy from the high-speed incoming flow is converted into internal energy, causing the temperature within the shock layer to rise sharply, reaching over 10,000 K, resulting in severe aerodynamic heating of the aircraft surface. Therefore, it is essential to develop advanced thermal protection systems to overcome the "thermal barrier" challenge in the development of high-speed aircraft. Currently, the thermal protection systems for various high-speed aircraft mainly employ ablation-based thermal protection technology. For localized high-heat flux interference areas, using thermal protection materials with higher performance over a relatively large area is a common design approach. However, due to differences in thermal properties, different types of thermal protection materials exhibit varying pyrolysis ablation rates, leading to discontinuous changes in shape at material joints. This further impacts the aerodynamic thermal environment, creating problems related to material ablation matching and aerodynamic thermal coupling. Summary of the Invention
[0003] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide an aerothermal ablation matching coupling simulation design method that can efficiently calculate the ablation shape change of different heat-resistant material overlap parts and the coupling effect of the aerothermal environment.
[0004] The technical solution of the present invention is: Firstly, a method for aerodynamic thermal ablation matching coupling simulation design is provided, wherein:
[0005] S1. Based on the external flow field grid and incoming flow conditions of the unablated aircraft shape, three-dimensional aerodynamic thermal simulation is carried out to provide the thermal environment of the joints of different types of thermal protection materials.
[0006] S2. Conduct ablation simulation analysis on the thermal protection materials on both sides of the overlap to determine the ablation amount and ablation profile on both sides, calculate the difference in ablation amount between the two sides, and record it as the initial ablation matching step height h0.
[0007] S3. Based on experience or ground test results, estimate the ablation degradation factor and the height H of the ablation matching step after the ablation degradation effect; at the same time, based on the ablation degradation factor and the ablation profile obtained in S2, carry out ablation step shape modeling to obtain the aircraft shape with local ablation step shape.
[0008] S4. For the aircraft shape with local ablation step shape obtained in S3, regenerate the external flow field mesh on the aircraft surface and carry out three-dimensional aerodynamic thermal simulation design, and give the thermal environment of the material overlap part considering the change of ablation shape.
[0009] S5. Based on the thermal environment of the material overlap area determined in step S4, conduct ablation simulation analysis on the thermal protection materials on both sides of the material overlap area again to determine the ablation amount and ablation profile on both sides, calculate the difference in ablation amount between the two sides, and record it as the secondary ablation matching step height h1.
[0010] S6. Compare the secondary ablation matching step height h1 obtained in step S5 with the ablation matching step height H estimated in S3. If h1≤H, it is confirmed that the ablation amount estimated in S3 can encompass the ablation amount of the flight test, and the simulation is completed. If h1>H, return to S3, increase the ablation deterioration factor, and iterate again.
[0011] Preferably, parameters of typical state points of the flight trajectory are selected in S1 to calculate the incoming flow conditions.
[0012] Preferably, in S3, the height H of the ablation matching step after the ablation deterioration effect is estimated based on the initial ablation matching step height h0.
[0013] Preferably, in S4, a three-dimensional aerodynamic and thermal simulation design is carried out based on the typical orbital state points selected in S1.
[0014] Preferably, the parameters for typical state points of the flight trajectory include: flight altitude and speed.
[0015] Preferably, the thermal environment data includes heat flow and pressure.
[0016] Secondly, an aerodynamic thermal ablation matched coupling simulation design system is provided, characterized by comprising: an external flow field mesh generation module for the aircraft surface, a thermal environment simulation module for thermal protection materials, an ablation simulation analysis module, an ablation deterioration estimation module, and an ablation amount confirmation module; wherein:
[0017] The aircraft surface external flow field mesh generation module is used to simulate the aircraft shape, generate the corresponding aircraft surface external flow field mesh, and output it to the thermal protection material thermal environment simulation module.
[0018] The thermal environment simulation module for thermal protection materials selects parameters at typical state points of the flight trajectory to calculate the incoming flow conditions. Based on the external flow field grid and the incoming flow conditions, it performs three-dimensional aerodynamic thermal simulation to obtain the thermal environment of the overlapping parts of different types of thermal protection materials and outputs it to the ablation simulation analysis module.
[0019] The ablation simulation analysis module performs ablation simulation analysis on the thermal protection materials on both sides of the overlap area, determines the ablation amount and ablation profile on both sides, calculates the difference in ablation amount between the two sides, and outputs it to the ablation deterioration estimation module or the ablation amount confirmation module.
[0020] The ablation deterioration estimation module estimates the ablation deterioration factor. Based on the difference in ablation amount between the two materials given by the ablation simulation analysis module, it estimates the ablation matching step height H after the ablation deterioration effect and outputs it to the ablation amount confirmation module.
[0021] The ablation amount confirmation module is used to analyze whether the results of the ablation simulation analysis module are within the envelope of the ablation matching step height H after the ablation deterioration effect output by the ablation deterioration estimation module.
[0022] Preferably, in the aerodynamic thermal ablation matching coupling simulation of a single flight trajectory, the system workflow is as follows:
[0023] S1. For the unablated shape of the aircraft, the external flow field mesh generation module generates the external flow field mesh on the aircraft surface; the thermal environment simulation module of thermal protection material selects the parameters of typical state points of the flight trajectory to calculate the incoming flow conditions, and carries out three-dimensional aerodynamic thermal simulation based on the external flow field mesh and the incoming flow conditions to give the thermal environment of the overlapping parts of different types of thermal protection materials.
[0024] S2. The ablation simulation analysis module performs ablation simulation analysis on the thermal protection materials on both sides of the overlap area, determines the ablation amount and ablation profile on both sides, calculates the difference in ablation amount between the two materials, records it as the initial ablation matching step height h0, and outputs it to the ablation deterioration estimation module.
[0025] S3. The ablation deterioration estimation module estimates the ablation deterioration factor based on experience or ground test results. It estimates the ablation matching step height H after the ablation deterioration effect based on the initial ablation matching step height h0 and outputs it to the ablation amount confirmation module.
[0026] Meanwhile, the external flow field mesh generation module on the aircraft surface performs ablation step shape modeling on the aircraft surface based on the ablation deterioration factor and the ablation profile obtained in S2, and obtains the aircraft shape with local ablation step shape.
[0027] S4, the external flow field mesh generation module of the aircraft surface is based on the shape of the aircraft with local ablation steps, and regenerates the external flow field mesh. Based on the typical orbital state points selected in S1, it carries out three-dimensional aerodynamic and thermal simulation design, and gives the thermal environment of the material joint area considering the ablation shape change, and outputs it to the ablation simulation analysis module.
[0028] S5. The ablation simulation analysis module, based on the thermal environment of the material overlap area determined in step S4, performs ablation simulation analysis on the thermal protection materials on both sides of the material overlap area again, determines the ablation amount and ablation profile on both sides, calculates the difference in ablation amount between the two sides, and records it as the secondary ablation matching step height h1, and outputs it to the ablation amount confirmation module.
[0029] S6. The ablation amount confirmation module compares the secondary ablation matching step height h1 obtained in step S5 with the ablation matching step height H estimated in S3. If h1≤H, it is confirmed that the ablation amount estimated in S3 can encompass the ablation amount of the flight test, and the simulation is completed. If h1>H, it returns to S3 and iterates again after increasing the ablation deterioration factor in the ablation deterioration estimation module.
[0030] Preferably, the parameters selected by the thermal environment simulation module for thermal protection materials at typical flight trajectory state points include: flight altitude and speed.
[0031] Compared with the prior art, the present invention has the following advantages:
[0032] (1) The method of the present invention can carry out aerodynamic thermal ablation matching coupling simulation along the flight trajectory, considering the ablation shape change of different heat protection material overlap parts and the coupling effect of aerodynamic thermal environment, and has high accuracy.
[0033] (2) Compared with the aerodynamic thermal / ablation shape tight coupling calculation method, the present invention has higher calculation efficiency and does not require multiple iterations. Attached Figure Description
[0034] Figure 1 This is a schematic diagram illustrating the ablation matching of different heat-resistant materials in this invention;
[0035] Figure 2 This is a flowchart of the aerodynamic thermal ablation matching coupling simulation design method of the present invention. Detailed Implementation
[0036] To address the ablation matching and aerodynamic-thermal coupling issues arising from the overlapping of different thermal protection materials, this invention provides a simulation design method for aerodynamic-thermal ablation matching coupling along a flight trajectory. The technical advantages of this method are: it can consider the coupling process between aerodynamic-thermal changes and ablation shape variations; it has high computational efficiency; and it does not require multiple iterations.
[0037] The method flow of this invention is as follows: Figure 2 As shown, specifically:
[0038] 1. For the unablated shape of the aircraft, generate the aircraft surface and external flow field mesh, select the typical state points of the flight trajectory, and calculate the incoming flow conditions based on the height, velocity and angle of attack. Based on the mesh and the incoming flow conditions, carry out three-dimensional aerodynamic thermal simulation calculations to give the thermal environment (heat flow, pressure) at the joint of different types of thermal protection materials.
[0039] 2. Based on the thermal environment of the material overlap area determined in step 1, ablation simulation analysis is conducted on the thermal protection materials on both sides of the overlap area to determine the ablation amount and ablation profile on both sides. The difference in ablation amount between the two sides is calculated and denoted as the initial ablation matching step height h0. The ablation matching results of different thermal protection materials before and after ablation are as follows: Figure 1 As shown.
[0040] 3. Based on the initial ablation matching step height h0 obtained in step 2, estimate the ablation deterioration factor according to experience or ground test results, and estimate the ablation matching step height H after considering the ablation deterioration effect based on h0; at the same time, according to the ablation deterioration factor and the ablation profile obtained in step 2, carry out ablation step shape modeling to obtain the aircraft shape with local ablation step shape.
[0041] 4. For the aircraft shape with local ablation steps obtained in step 3, regenerate the aircraft surface and external flow field mesh. For the typical orbital state points selected in step 1, carry out three-dimensional aerodynamic and thermal simulation design and give the thermal environment (heat flow, pressure) of the material overlap part considering the ablation shape change.
[0042] 5. Based on the thermal environment of the material overlap area determined in step 4, for the thermal protection materials on both sides of the material overlap area, ablation simulation analysis is carried out again on the basis of the initial ablation matching step height h0 state to determine the ablation amount and ablation profile on both sides, and the difference between the ablation amount of the materials on both sides is calculated and recorded as the secondary ablation matching step height h1.
[0043] 6. Compare the secondary ablation matching step height h1 obtained in step 5 with the ablation matching step height H estimated in step 3. If h1≤H, then the ablation amount estimated in step 3 can be confirmed to include the ablation amount of the flight test, and the simulation is completed; if h1>H, then return to step 3, appropriately increase the ablation deterioration factor, and iterate again.
[0044] Secondly, this invention provides an aerodynamic thermal ablation matched coupling simulation design system, characterized by comprising: a vehicle surface and external flow field mesh generation module, a thermal environment simulation module for thermal protection materials, an ablation simulation analysis module, an ablation deterioration estimation module, and an ablation amount confirmation module; wherein:
[0045] The aircraft surface external flow field mesh generation module is used to simulate the aircraft shape, generate the corresponding aircraft surface and external flow field mesh, and output it to the thermal environment simulation module of thermal protection material;
[0046] The thermal environment simulation module for thermal protection materials selects parameters at typical state points of the flight trajectory to calculate the incoming flow conditions. Based on the external flow field grid and the incoming flow conditions, it performs three-dimensional aerodynamic thermal simulation to obtain the thermal environment of the overlapping parts of different types of thermal protection materials and outputs it to the ablation simulation analysis module.
[0047] The ablation simulation analysis module performs ablation simulation analysis on the thermal protection materials on both sides of the overlap area, determines the ablation amount and ablation profile on both sides, calculates the difference in ablation amount between the two sides, and outputs it to the ablation deterioration estimation module or the ablation amount confirmation module.
[0048] The ablation deterioration estimation module estimates the ablation deterioration factor. Based on the difference in ablation amount between the two materials given by the ablation simulation analysis module, it estimates the ablation matching step height H after the ablation deterioration effect and outputs it to the ablation amount confirmation module.
[0049] The ablation amount confirmation module is used to analyze whether the results of the ablation simulation analysis module are within the envelope of the ablation matching step height H after the ablation deterioration effect output by the ablation deterioration estimation module.
[0050] Furthermore, in an aerodynamic thermal ablation matching coupling simulation of a flight trajectory, the system's workflow is as follows:
[0051] S1. For the unablated shape of the aircraft, the external flow field mesh generation module generates the external flow field mesh on the aircraft surface; the thermal environment simulation module of thermal protection material selects the parameters of typical state points of the flight trajectory to calculate the incoming flow conditions, and carries out three-dimensional aerodynamic thermal simulation based on the external flow field mesh and the incoming flow conditions to give the thermal environment of the overlapping parts of different types of thermal protection materials.
[0052] S2. The ablation simulation analysis module performs ablation simulation analysis on the thermal protection materials on both sides of the overlap area, determines the ablation amount and ablation profile on both sides, calculates the difference in ablation amount between the two materials, records it as the initial ablation matching step height h0, and outputs it to the ablation deterioration estimation module.
[0053] S3. The ablation deterioration estimation module estimates the ablation deterioration factor based on experience or ground test results. It estimates the ablation matching step height H after the ablation deterioration effect based on the initial ablation matching step height h0 and outputs it to the ablation amount confirmation module.
[0054] Meanwhile, the external flow field mesh generation module on the aircraft surface performs ablation step shape modeling on the aircraft surface based on the ablation deterioration factor and the ablation profile obtained in S2, and obtains the aircraft shape with local ablation step shape.
[0055] S4, the external flow field mesh generation module of the aircraft surface is based on the shape of the aircraft with local ablation steps, and regenerates the external flow field mesh. Based on the typical orbital state points selected in S1, it carries out three-dimensional aerodynamic and thermal simulation design, and gives the thermal environment of the material joint area considering the ablation shape change, and outputs it to the ablation simulation analysis module.
[0056] S5. The ablation simulation analysis module, based on the thermal environment of the material overlap area determined in step S4, performs ablation simulation analysis on the thermal protection materials on both sides of the material overlap area again, determines the ablation amount and ablation profile on both sides, calculates the difference in ablation amount between the two sides, and records it as the secondary ablation matching step height h1, and outputs it to the ablation amount confirmation module.
[0057] S6. The ablation amount confirmation module compares the secondary ablation matching step height h1 obtained in step S5 with the ablation matching step height H estimated in S3. If h1≤H, it is confirmed that the ablation amount estimated in S3 can encompass the ablation amount of the flight test, and the simulation is completed. If h1>H, it returns to S3 and iterates again after increasing the ablation deterioration factor in the ablation deterioration estimation module.
[0058] The parameters selected for the thermal environment simulation module of thermal protection materials at typical flight trajectory state points include: flight altitude and speed.
[0059] The contents not described in detail in this specification are existing technologies known to those skilled in the art.
Claims
1. A method for aerodynamic thermal ablation matching coupling simulation design, characterized in that... include: S1. Based on the external flow field grid and incoming flow conditions of the unablated aircraft shape, three-dimensional aerodynamic thermal simulation is carried out to provide the thermal environment of the joints of different types of thermal protection materials. S2. Conduct ablation simulation analysis on the thermal protection materials on both sides of the overlap to determine the ablation amount and ablation profile on both sides, calculate the difference in ablation amount between the two sides, and record it as the initial ablation matching step height h0. S3. Based on experience or ground test results, estimate the ablation degradation factor and the height H of the ablation matching step after the ablation degradation effect; at the same time, based on the ablation degradation factor and the ablation profile obtained in S2, carry out ablation step shape modeling to obtain the aircraft shape with local ablation step shape. S4. For the aircraft shape with local ablation step shape obtained in S3, regenerate the external flow field mesh on the aircraft surface and carry out three-dimensional aerodynamic thermal simulation design, and give the thermal environment of the material overlap part considering the change of ablation shape. S5. Based on the thermal environment of the material overlap area determined in step S4, conduct ablation simulation analysis on the thermal protection materials on both sides of the material overlap area again to determine the ablation amount and ablation profile on both sides, calculate the difference in ablation amount between the two sides, and record it as the secondary ablation matching step height h1. S6. Compare the secondary ablation matching step height h1 obtained in step S5 with the ablation matching step height H estimated in S3. If h1≤H, it is confirmed that the ablation amount estimated in S3 can encompass the ablation amount of the flight test, and the simulation is completed. If h1>H, return to S3, increase the ablation deterioration factor, and iterate again.
2. The aerodynamic thermal ablation matched coupling simulation design method according to claim 1, characterized in that: In S1, parameters of typical state points of the flight trajectory are selected to calculate the incoming flow conditions.
3. The aerodynamic thermal ablation matched coupling simulation design method according to claim 1, characterized in that: In S3, the height H of the ablation matching step after the ablation deterioration effect is estimated based on the initial ablation matching step height h0.
4. The aerodynamic thermal ablation matched coupling simulation design method according to claim 2, characterized in that: In S4, a three-dimensional aerodynamic and thermal simulation design is carried out based on the typical orbital state points selected in S1.
5. The aerodynamic thermal ablation matched coupling simulation design method according to claim 1, characterized in that: The parameters for typical state points of a flight trajectory include: flight altitude and speed.
6. The aerodynamic thermal ablation matched coupling simulation design method according to claim 1, characterized in that: Thermal environment data includes heat flow and pressure.
7. A pneumatic thermal ablation matched coupling simulation design system, characterized in that... include: The system includes modules for generating meshes of external flow fields on the aircraft surface, simulating the thermal environment of thermal protection materials, performing ablation simulation analysis, estimating ablation deterioration, and confirming ablation amount. Among these modules are: The aircraft surface external flow field mesh generation module is used to simulate the aircraft shape, generate the corresponding aircraft surface external flow field mesh, and output it to the thermal protection material thermal environment simulation module. The thermal environment simulation module for thermal protection materials selects parameters at typical state points of the flight trajectory to calculate the incoming flow conditions. Based on the external flow field grid and the incoming flow conditions, it performs three-dimensional aerodynamic thermal simulation to obtain the thermal environment of the overlapping parts of different types of thermal protection materials and outputs it to the ablation simulation analysis module. The ablation simulation analysis module performs ablation simulation analysis on the thermal protection materials on both sides of the overlap area, determines the ablation amount and ablation profile on both sides, calculates the difference in ablation amount between the two sides, and outputs it to the ablation deterioration estimation module or the ablation amount confirmation module. The ablation deterioration estimation module estimates the ablation deterioration factor. Based on the difference in ablation amount between the two materials given by the ablation simulation analysis module, it estimates the ablation matching step height H after the ablation deterioration effect and outputs it to the ablation amount confirmation module. The ablation amount confirmation module is used to analyze whether the results of the ablation simulation analysis module are within the envelope of the ablation matching step height H after the ablation deterioration effect output by the ablation deterioration estimation module.
8. The aerodynamic thermal ablation matched coupling simulation design system according to claim 7, characterized in that: In a simulated aerodynamic thermal ablation matching of a flight trajectory, the system's workflow is as follows: S1. For the unablated shape of the aircraft, the external flow field mesh generation module generates the external flow field mesh on the aircraft surface; the thermal environment simulation module of thermal protection material selects the parameters of typical state points of the flight trajectory to calculate the incoming flow conditions, and carries out three-dimensional aerodynamic thermal simulation based on the external flow field mesh and the incoming flow conditions to give the thermal environment of the overlapping parts of different types of thermal protection materials. S2. The ablation simulation analysis module performs ablation simulation analysis on the thermal protection materials on both sides of the overlap area, determines the ablation amount and ablation profile on both sides, calculates the difference in ablation amount between the two materials, records it as the initial ablation matching step height h0, and outputs it to the ablation deterioration estimation module. S3. The ablation deterioration estimation module estimates the ablation deterioration factor based on experience or ground test results. It estimates the ablation matching step height H after the ablation deterioration effect based on the initial ablation matching step height h0 and outputs it to the ablation amount confirmation module. Meanwhile, the external flow field mesh generation module on the aircraft surface performs ablation step shape modeling on the aircraft surface based on the ablation deterioration factor and the ablation profile obtained in S2, and obtains the aircraft shape with local ablation step shape. S4, the external flow field mesh generation module of the aircraft surface is based on the shape of the aircraft with local ablation steps, and regenerates the external flow field mesh. Based on the typical orbital state points selected in S1, it carries out three-dimensional aerodynamic and thermal simulation design, and gives the thermal environment of the material joint area considering the ablation shape change, and outputs it to the ablation simulation analysis module. S5. The ablation simulation analysis module, based on the thermal environment of the material overlap area determined in step S4, performs ablation simulation analysis on the thermal protection materials on both sides of the material overlap area again, determines the ablation amount and ablation profile on both sides, calculates the difference in ablation amount between the two sides, and records it as the secondary ablation matching step height h1, and outputs it to the ablation amount confirmation module. S6. The ablation amount confirmation module compares the secondary ablation matching step height h1 obtained in step S5 with the ablation matching step height H estimated in S3. If h1≤H, it is confirmed that the ablation amount estimated in S3 can encompass the ablation amount of the flight test, and the simulation is completed. If h1>H, it returns to S3 and iterates again after increasing the ablation deterioration factor in the ablation deterioration estimation module.
9. The aerodynamic thermal ablation matching coupling simulation design system according to claim 7, characterized in that: The parameters selected for the thermal environment simulation module of thermal protection materials at typical flight trajectory state points include: flight altitude and speed.
Citation Information
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