A modeling method for hexagonal silicon carbide core components for space nuclear power

Abstract

The present invention discloses a modeling method for hexagonal silicon carbide core components for space nuclear power, which relates to the field of space nuclear thermal propulsion fuel technology. The method includes: calculating the number of coated fuel particles, modeling the coated fuel particle composite material into uniform mass particles by reasonably selecting an equivalent method for a physical property model; developing a random distribution strategy, generating random coordinates of equivalent coated fuel particles one by one within a specified cylindrical radius, and dispersing the equivalent coated fuel particles in the hexagonal support structure by running a random algorithm; judging whether the equivalent coated fuel particles have geometric overlap, using Boolean operations to eliminate fuel particles that geometrically overlap with the main component, and judging whether the equivalent coated fuel particles have reached a specified number. The present invention can perform full three-dimensional modeling of the complete structure of the hexagonal silicon carbide core, and realize the random distribution of fuel particles in the hexagonal structure under different coating fuel particle filling rates.

Description

Technical Field

[0001] The present invention relates to the technical field of space nuclear thermal propulsion fuel, and in particular to a modeling method of a hexagonal silicon carbide core component for space nuclear power. Background Art

[0002] Space nuclear thermal propulsion technology, with its advantages of high thrust, high specific impulse, and multiple starts, has become a highly competitive deep space exploration technology in the future. In space nuclear power systems, the extremely harsh service conditions of nuclear fuel elements are one of the bottlenecks restricting the development of nuclear thermal propulsion technology. Hexagonal core components utilize a novel fuel structure consisting of multi-layer coated fuel particles dispersed within a silicon carbide support. These components exhibit high irradiation stability, inherent safety features, high fission product containment, and strong resistance to oxidation and corrosion, making them a key candidate for space nuclear thermal propulsion fuel. The geometric structure of hexagonal silicon carbide core components is complex, and currently mature large-scale commercial reactor analysis programs (such as RELAP5, FRAPCON, and TRAC) typically simplify the core into a one- or two-dimensional geometry during calculations, or perform a rough three-dimensional overall core modeling, making it incapable of performing precise core analysis.

[0003] In recent years, researchers at home and abroad have used numerical simulation methods to model hexagonal or hexagonal-like core structures, and on this basis, carried out core design analysis research.

[0004] For example, in the paper "BR Betzler, B J Ade, PK Jain. Conceptual Design of the Transformational Challenge Reactor, Nuclear Science and Engineering, 2021," the authors modeled the core of a 3MW, helium-cooled, hexagonal space nuclear power reactor. However, this work lacked a model for the multilayered, coated fuel particles within the reactor, only the external silicon carbide components. This modeling approach is too crude, and in particular, it cannot fully simulate the in-core behavior and performance of the fuel elements.

[0005] For example, in the paper "Brian J. Ade, Benjamin R. Betzler, Aaron J. Wysocki 1. Candidate Core Designs for the Transformational Challenge Reactor," J. Nucl. Eng. 2021, 2, 74–85, the authors established a one-dimensional model of a hexagonal core and external flow field and conducted preliminary fluid-structure interaction simulations. However, this study remained at a macroscopic, rough analysis, focusing on a few overall parameters such as core temperature, coolant inlet and outlet temperatures, and pressure drop, and failed to capture detailed three-dimensional core performance parameters.

[0006] For example, in the Oak Ridge National Laboratory report "Key Material Properties for ThermoStructural Analysis of Transformational Challenge Reactor Core Components, ORNL / SPR-2019 / 1277," the authors constructed a cylindrical core structure consisting of 106 coated fuel particles. The core in the model was 4.5 mm high, 9.2 mm in diameter, and had a particle filling rate of 35%. However, the study only geometrically modeled representative volume elements of the dispersed type of multi-layer coated fuel particles and only briefly explored the impact on the core's thermal performance. This modeling method only provides a simple modeling of the cylindrical core and cannot simulate the actual geometry of the hexagonal core in space nuclear power systems.

[0007] In summary, there are few research papers on hexagonal silicon carbide core components for space nuclear power at home and abroad, and the modeling methods for hexagonal core components have certain limitations. At present, there is no method that can achieve full three-dimensional modeling of complete core components with particle dispersion, and the geometric structure of hexagonal core components cannot be fully simulated. Summary of the Invention

[0008] Based on this, in response to the above technical problem: there is currently no method that can achieve full three-dimensional modeling of complete core components with particle dispersion, and thus cannot fully simulate the geometric structure of hexagonal core components. An embodiment of the present invention provides a modeling method for hexagonal silicon carbide core components for space nuclear power.

[0009] An embodiment of the present invention provides a method for modeling a hexagonal silicon carbide core component for space nuclear power, comprising:

[0010] Setting the geometry and dimensions of the hexagonal silicon carbide core components;

[0011] The number of coated fuel particles is determined based on the geometric structure and size of the hexagonal silicon carbide core components, the volume power density and volume filling rate requirements of the fuel elements;

[0012] With the goal of modeling the heat transfer and mechanical properties of coated fuel particles, the coated fuel particles are modeled into uniform particles; and the uniform particles are recorded as equivalent coated fuel particles;

[0013] A random distribution strategy is adopted to generate random coordinates of equivalent coated fuel particles one by one in the hexagonal silicon carbide core component, and the number of random coordinates is consistent with the number of coated fuel particles; and all equivalent coated fuel particles are dispersed at the random coordinates to form a hexagonal silicon carbide core component for space nuclear power.

[0014] Furthermore, the geometric structure and dimensions of the hexagonal silicon carbide core component include:

[0015] The distance between opposite sides of hexagonal prism support structure;

[0016] The radius of the moderator guide tube at the center of the core;

[0017] External coolant flow channel width;

[0018] The geometry and dimensions of the internal coolant flow channels.

[0019] Furthermore, the relationship between the volume power density and the number of coated fuel particles is:

[0020]

[0021]

[0022] Where:

[0023] V h —The volume of the hexagonal core component;

[0024] a — distance across flats of hexagonal prism supporting structure;

[0025] n ——the number of coated fuel particles;

[0026] P n ——Power of each coated fuel particle W;

[0027] P d ——Volume power density W / m 3 .

[0028] Furthermore, the relationship between the volume filling rate and the number of coated fuel particles is:

[0029]

[0030] Where:

[0031] Vol.%——volume filling rate%;

[0032] n ——the number of coated fuel particles;

[0033] V n —The volume of each coated fuel particle;

[0034] V h ——The volume of the hexagonal core component.

[0035] Furthermore, the structure of the coated fuel particles is: a fuel core, a porous medium material coating layer Buffer, an inner dense pyrolytic carbon coating layer IPyC, a ceramic material coating layer SiC, and an inner dense pyrolytic carbon coating layer OPyC arranged in sequence from the inside to the outside.

[0036] Further,

[0037] The mechanical properties include: density, elastic modulus, Poisson's ratio;

[0038] The heat transfer characteristics include: thermal conductivity, thermal expansion coefficient, and specific heat capacity at constant pressure.

[0039] Furthermore, the modeling formula is:

[0040]

[0041] Where:

[0042] V x ——Volume ratio of each coating layer, subscript x represents each coating layer;

[0043] α——equivalent physical properties of coated fuel particles;

[0044] ——Equivalent physical properties of each coating layer, including density (ρ), elastic modulus (E),

[0045] α x Poisson's ratio (ν), thermal conductivity (K), coefficient of thermal expansion (CTE), specific heat capacity at constant pressure (C p ), subscript x represents each coating layer;

[0046] kernel——subscript, indicating the fuel core;

[0047] buffer——subscript, indicating the coating layer of porous medium material;

[0048] dense - subscript, indicating the inner and outer dense pyrolytic carbon material coating layers;

[0049] Ceramic - subscript indicating a coating of ceramic material.

[0050] Furthermore, the random distribution strategy is expressed as:

[0051] x i =(2·rand(0,1)-1)·r h (5)

[0052] y i =rand(0,1)·r h (6)

[0053] z i =rand(0,1)·h h (7)

[0054]

[0055]

[0056]

[0057] Where:

[0058] ——Subscript i represents the i-th uniform particle, x represents the rectangular coordinate

[0059] x i The x-direction coordinate in the reference system;

[0060] ——Subscript i represents the i-th uniform particle, y represents the rectangular coordinate

[0061] y i The y-direction coordinate in the reference system;

[0062] ——Subscript i represents the i-th uniform particle, z represents the rectangular coordinate

[0063] z i The z-direction coordinate in the reference system;

[0064] rand(0,1)——normal distribution random function, its range is (0,1);

[0065] r i ——Radius coordinate of uniform particle in spherical coordinate system;

[0066] θ i ——Vertex coordinates of homogeneous particles in the spherical coordinate system;

[0067] ——azimuthal coordinates of homogeneous particles in the spherical coordinate system;

[0068] ——The diagonal distance of the hexagonal support structure and the opposite side of the regular hexagon

[0069] r h The relationship between the distance a is

[0070] h h ——The height of the hexagonal prism supporting structure.

[0071] Furthermore, an embodiment of the present invention provides a modeling method for a hexagonal silicon carbide core component for space nuclear power, further comprising:

[0072] According to the cyclic algorithm, starting from the i-th uniform mass particle, the judgment formula is used to determine whether the i-th uniform mass particle and all the previous n uniform mass particles have geometric overlap. If there is overlap, the coordinates are regenerated; where i>1;

[0073] The determination formula is:

[0074]

[0075] Where:

[0076] x n ——Subscript n represents the nth (n=i-1) uniform particle, x represents the direct

[0077] The x-direction coordinate in the reference system;

[0078] y n ——Subscript n represents the nth (n=i-1) uniform particle, y represents the direct

[0079] The y-direction coordinate in the reference system;

[0080] z n ——Subscript n represents the nth (n=i-1) uniform particle, z represents the direct

[0081] The z-direction coordinate in the reference system;

[0082] r n ——Subscript n represents the nth (n=i-1) uniform particle, r represents the uniform particle

[0083] The radius of the body particle;

[0084] x i ——Subscript i represents the i-th uniform particle, and x represents the x-direction coordinate in the direct coordinate system;

[0085] y i ——Subscript i represents the i-th uniform particle, and y represents the y-direction coordinate in the direct coordinate system;

[0086] z i ——Subscript i represents the i-th uniform mass particle, and z represents the z-direction coordinate in the direct coordinate system;

[0087] r i ——Subscript i represents the i-th uniform mass particle, r represents the i-th uniform mass particle.

[0088] The radius of the body particle;

[0089] d - the maximum distance between particles, which increases the particle density in a limited space.

[0090] Furthermore, an embodiment of the present invention provides a modeling method for a hexagonal silicon carbide core component for space nuclear power, further comprising:

[0091] Using Boolean operations, geometrically overlapping uniform particles are eliminated.

[0092] The above-mentioned hexagonal silicon carbide core component modeling method for space nuclear power provided by the embodiment of the present invention has the following beneficial effects compared with the prior art:

[0093] (1) The present invention provides an efficient and precise modeling method for hexagonal silicon carbide core components, which can simulate the complex geometry of the actual core as closely as possible, and provides precise and accurate modeling means and methods for the numerical analysis of hexagonal silicon carbide core components, thereby improving the reliability and design accuracy of the numerical simulation. Specifically, the modeling strategy developed by the present invention is applicable to all hexagonal core components involved in space nuclear power systems, which are composed of coated fuel particles filled in silicon carbide structural parts. It is capable of performing full three-dimensional modeling of the complete structure of the hexagonal silicon carbide core, and realizing the random distribution of fuel particles in the hexagonal structural parts at different coated fuel particle filling rates. Specifically, the present invention models the coated fuel particle composite material into uniform mass particles by reasonably selecting an equivalent method for the physical property model, and replaces its physical properties with equivalent physical properties. While improving the calculation efficiency, it can ensure the model accuracy and accuracy of the results when simulating fuel behavior; the method of the present invention is not limited to the geometric model, and its random distribution strategy and method can be extended to all hexagonal core components composed of coated fuel particles filled in silicon carbide structural parts involved in other space nuclear power systems, and has wide versatility.

[0094] (2) The algorithm of the present invention is independent and the method is original. Its modeling method is parametric, logically clear, and highly readable. Moreover, the ideas and methods mentioned in the present invention are also applicable to all hexagonal core components composed of coated fuel particles filled in silicon carbide structural parts involved in space nuclear power systems. BRIEF DESCRIPTION OF THE DRAWINGS

[0095] Figure 1A flow chart of a method for modeling a hexagonal silicon carbide core component for space nuclear power provided in one embodiment;

[0096] Figure 2 A schematic diagram of a hexagonal silicon carbide core component provided in one embodiment. Description of the drawings:

[0098] 1- hexagonal prism support structure, 2- moderator guide tube, 3- internal coolant flow channel, 4- external coolant flow channel, 5- uniform mass particles. DETAILED DESCRIPTION

[0099] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0100] In one embodiment, a method for modeling a hexagonal silicon carbide core component for space nuclear power is provided. This method uses a uniform physical property equivalence method and a random distribution strategy to achieve modeling of a hexagonal silicon carbide core component with equivalent physical properties for space nuclear power. This method is applicable to all hexagonal core components involved in space nuclear power systems, which are composed of coated fuel particles filled in silicon carbide structural parts. Figure 1 , its technical solution is as follows:

[0101] Step 1: Set the geometry and dimensions of the core structural components, including the hexagonal support structure, moderator guide tubes, and internal and external coolant flow channels.

[0102] Step 2: Calculate the number of coated fuel particles according to the power density and filling rate requirements, and model the coated fuel particle composite material into uniform mass particles by reasonably selecting the equivalent method of the physical property model.

[0103] Step 3: Develop a random distribution strategy to generate random coordinates of equivalent coated fuel particles one by one within the specified cylindrical radius, and disperse the equivalent coated fuel particles in the hexagonal support structure by running a random algorithm.

[0104] Step 4: Determine whether the equivalent coated fuel particles have geometric overlap, use Boolean operations to eliminate the fuel particles that geometrically overlap with the main component, and determine whether the equivalent coated fuel particles reach the specified number. The modeling is completed.

[0105] The detailed description of the above steps is as follows:

[0106] Step 1: Define the geometry and dimensions of the core structure, including the hexagonal support structure's across-edge dimensions, the core center moderator guide tube radius, the external coolant channel width, and the internal coolant channel geometry and dimensions. (For example: hexagonal support structure's across-edge dimensions = 120mm; core center moderator guide tube radius = 10mm; external coolant channel width = 4mm; internal coolant channel is cylindrical with a radius of 1mm; or the internal coolant channel is Y-shaped with a width of 1mm and a chamfer radius of 0.3mm.) See [ 1-3 ]. Figure 2 .

[0107] Step 2: Calculate the number of coated fuel particles based on the power density and volume filling rate requirements. The power density is the volume power density of the fuel element. The relationship between the volume power density and the number of coated fuel particles is as follows:

[0108]

[0109]

[0110] Where:

[0111] V h ——The volume of the hexagonal core component.

[0112] a —distance between opposite sides of hexagonal prism supporting structure.

[0113] n is the number of coated fuel particles.

[0114] P n ——Power per coated fuel particle (W).

[0115] P d ——Volume power density (W / m 3 ).

[0116] The relationship between volume filling rate and the number of coated particles is as follows:

[0117]

[0118] Where:

[0119] Vol.% ——Volume filling rate (%).

[0120] n is the number of coated fuel particles.

[0121] V n ——The volume of each coated fuel particle.

[0122] V h ——The volume of the hexagonal core component.

[0123] By rationally selecting an equivalent physical property model, the composite material of coated fuel particles is modeled as a homogeneous mass particle; the physical properties of the homogeneous mass particle are replaced by its equivalent properties. The pellet material of hexagonal prism core fuel elements used in space nuclear power is typically a composite coated fuel particle. The structure of a coated fuel particle generally consists of a fuel core, a porous dielectric buffer, an internally dense pyrolytic carbon (IPyC) layer, a ceramic (SiC) layer, or an internally dense pyrolytic carbon (OPyC) layer. To simplify the geometry, the coated fuel particle composite material is modeled as a homogeneous mass with the goal of modeling the heat transfer and mechanical properties of the coated fuel particle. A linear mixing rule is used to replace the physical properties of the multilayer coated fuel particle (including density, elastic modulus, Poisson's ratio, thermal conductivity, thermal expansion coefficient, and specific heat capacity at constant pressure) with equivalent properties. This step ignores the interaction between the coating materials and assumes that the coating materials are isotropic and linear elastic. The equivalent physical property modeling formula of the coated fuel particles is:

[0124]

[0125] Where:

[0126] V x ——Volume proportion of each coating layer, subscript x represents each coating layer.

[0127] α —Equivalent physical properties of coated fuel particles.

[0128] ——Equivalent physical properties of each coating layer, including density (ρ), elastic modulus (E), Poisson's ratio (ν), thermal conductivity (K), thermal expansion coefficient

[0129] α x

[0130] Number (CTE), constant pressure specific heat capacity (C p ), the subscript x represents each coating layer.

[0131] kernel ——subscript, indicating the fuel core.

[0132] buffer ——subscript indicating the coating layer of porous medium material.

[0133] dense ——subscript, indicating the inner and outer dense pyrolytic carbon material coating layers.

[0134] ceramic ——subscript indicating a coating of ceramic material.

[0135] Step 3: Using a random distribution strategy, random coordinates of equivalent coated fuel particles are generated one by one within the specified cylindrical radius. The equivalent coated fuel particles are dispersed in the hexagonal support structure by running a random algorithm. The formula of the random distribution strategy is:

[0136] x i =(2·rand(0,1)-1)·r h (5)

[0137] y i =rand(0,1)·r h (6)

[0138] z i =rand(0,1)·h h (7)

[0139]

[0140]

[0141]

[0142] Where:

[0143] ——Subscript i represents the i-th uniform particle, and x represents a right angle

[0144] x i The x-coordinate in the coordinate system.

[0145] ——Subscript i represents the i-th uniform particle, y represents the right angle

[0146] y i The y-coordinate in the coordinate system.

[0147] z i ——The subscript i represents the i-th uniform mass particle, and z represents the z-direction coordinate in the rectangular coordinate system.

[0148] rand(0,1) – Normally distributed random function with a range of (0,1).

[0149] r i ——Radius coordinate of uniform particle in spherical coordinate system.

[0150] θ i ——Vertex coordinates of homogeneous particles in the spherical coordinate system.

[0151] ——Azimuth coordinates of homogeneous particles in the spherical coordinate system.

[0152] ——The diagonal distance between the hexagonal support structure and the regular hexagon

[0153] r h The relationship between the side distance a is

[0154] h h ——The height of the hexagonal prism supporting structure.

[0155] Step 4: Determine whether the equivalent coated fuel particles have geometric overlap. Starting from the i-th (i>1) uniform mass particle, determine whether there is geometric overlap with all the previous n uniform mass particles (n=i-1). If there is overlap, regenerate the coordinates. The judgment method is to establish a cyclic algorithm to calculate the spherical center distance between the i-th (i>1) uniform mass particle and all the n uniform mass particles constructed previously. If the spherical center distance is greater than the sum of the radii between the two uniform mass particles, it is determined that there is no geometric overlap. The judgment formula is:

[0156]

[0157] Where:

[0158] x n ——The subscript n represents the nth (n=i-1) uniform mass particle, and x represents the x-direction coordinate in the direct coordinate system.

[0159] y n ——The subscript n represents the nth (n=i-1) uniform mass particle, and y represents the y-direction coordinate in the direct coordinate system.

[0160] z n ——The subscript n represents the nth (n=i-1) uniform mass particle, and z represents the z-direction coordinate in the direct coordinate system.

[0161] r n ——The subscript n represents the nth (n=i-1) uniform mass particle, and r represents the radius of the uniform mass particle.

[0162] x i ——The subscript i represents the i-th uniform mass particle, and x represents the x-direction coordinate in the direct coordinate system.

[0163] y i ——The subscript i represents the i-th uniform mass particle, and y represents the y-direction coordinate in the direct coordinate system.

[0164] z i ——The subscript i represents the i-th uniform mass particle, and z represents the z-direction coordinate in the direct coordinate system.

[0165] r i ——Subscript i represents the i-th uniform particle, r represents the i-th

[0166] The radius of a uniform particle.

[0167] d - the maximum distance between particles, which increases the particle density in a limited space.

[0168] Boolean operations are used to eliminate fuel particles that overlap with the main component geometry, and to determine whether the number of equivalent coated fuel particles reaches the specified number, and the modeling is completed.

[0169] The modeling method involved in the present invention can ultimately realize the modeling of hexagonal silicon carbide core components with equivalent physical properties used in space nuclear power.

[0170] The above-described embodiments merely illustrate several implementations of the present invention, and while their descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent. It should be noted that a person skilled in the art would be able to make numerous variations and improvements without departing from the spirit of the present invention, all of which fall within the scope of protection of the present invention. Therefore, the scope of protection of the patent for this invention shall be determined by the appended claims.

Claims

1. A modeling method for hexagonal silicon carbide core components for space nuclear power, characterized in that: include: Setting the geometry and dimensions of the hexagonal silicon carbide core components; The number of coated fuel particles is determined based on the geometric structure and dimensions of the hexagonal silicon carbide core components, the volume power density and volume filling rate requirements of the fuel elements; With the goal of modeling the heat transfer and mechanical properties of coated fuel particles, the coated fuel particles are modeled into uniform particles; and the uniform particles are recorded as equivalent coated fuel particles; A random distribution strategy is used to generate random coordinates of equivalent coated fuel particles one by one within a hexagonal silicon carbide core component, with the number of random coordinates being consistent with the number of coated fuel particles. All equivalent coated fuel particles are then dispersed at the random coordinates to form a hexagonal silicon carbide core component for space nuclear power. The modeling formula is: Where: V x ——Volume ratio of each coating layer, subscript x represents each coating layer; α——equivalent physical properties of coated fuel particles; α x ——Equivalent physical properties of each coating layer, including density ρ, elastic modulus E, Poisson's ratio ν, thermal conductivity K, coefficient of thermal expansion CTE, specific heat capacity at constant pressure C p , The subscript x represents each coating layer; kernel——subscript, indicating the fuel core; buffer——subscript, indicating the coating layer of porous medium material; dense - subscript, indicating the inner and outer dense pyrolytic carbon material coating layers; Ceramic - subscript indicating a coating of ceramic material.

2. The method for modeling a hexagonal silicon carbide core component for space nuclear power according to claim 1, wherein: The geometric structure and dimensions of the hexagonal silicon carbide core component include: The distance between opposite sides of hexagonal prism support structure; The radius of the moderator guide tube at the center of the core; External coolant flow channel width; The geometry and dimensions of the internal coolant flow channels.

3. The modeling method of hexagonal silicon carbide core components for space nuclear power according to claim 1, characterized in that: The relationship between the volume power density and the number of coated fuel particles is: Where: V h — Volume of hexagonal silicon carbide core components; a——the distance between opposite sides of the hexagonal prism supporting structure; n——the number of coated fuel particles; P n ——Power of each coated fuel particle W; P d ——Volume power density W / m 3 .

4. The modeling method of hexagonal silicon carbide core components for space nuclear power according to claim 1, characterized in that: The relationship between the volume filling rate and the number of coated fuel particles is: Where: Vol.%——volume filling rate%; n——the number of coated fuel particles; V n —The volume of each coated fuel particle; V h ——The volume of the hexagonal silicon carbide core component.

5. The modeling method of hexagonal silicon carbide core components for space nuclear power according to claim 1, characterized in that: The structure of the coated fuel particles is: a fuel core, a porous medium material coating layer Buffer, an inner dense pyrolytic carbon coating layer IPyC, a ceramic material coating layer SiC, and an inner dense pyrolytic carbon coating layer OPyC, which are arranged in sequence from the inside to the outside.

6. The modeling method of hexagonal silicon carbide core components for space nuclear power according to claim 1, characterized in that: The mechanical properties include: density, elastic modulus, Poisson's ratio; The heat transfer characteristics include: thermal conductivity, thermal expansion coefficient, and specific heat capacity at constant pressure.

7. The method for modeling a hexagonal silicon carbide core component for space nuclear power according to claim 1, wherein: The expression of the random distribution strategy is: x i =(2·rand(0,1)-1)·r h (5) y i =rand(0,1)·r h (6) z i =rand(0,1)·h h (7) Where: x i ——Subscript i represents the i-th uniform particle, x represents the rectangular coordinate The x-direction coordinate in the reference system; y i ——Subscript i represents the i-th uniform particle, y represents the rectangular coordinate The y-direction coordinate in the reference system; z i ——Subscript i represents the i-th uniform particle, z represents the rectangular coordinate The z-direction coordinate in the reference system; rand(0,1)——normal distribution random function, its range is (0,1); r i ——Radius coordinate of uniform particle in spherical coordinate system; θ i ——Vertex coordinates of homogeneous particles in the spherical coordinate system; ——azimuthal coordinates of homogeneous particles in the spherical coordinate system; r h ——The diagonal distance of the hexagonal support structure and the opposite side of the regular hexagon The relationship between the distance a is h h ——The height of the hexagonal prism supporting structure.

8. The method for modeling a hexagonal silicon carbide core component for space nuclear power according to claim 1, wherein: Also includes: According to the cyclic algorithm, starting from the i-th uniform mass particle, the judgment formula is used to determine whether the i-th uniform mass particle and all the previous n uniform mass particles have geometric overlap. If there is overlap, the coordinates are regenerated; where i>1; The determination formula is: Where: x n ——Subscript n represents the nth (n=i-1) uniform particle, x represents the direct The x-direction coordinate in the reference system; y n ——Subscript n represents the nth (n=i-1) uniform particle, y represents the direct The y-direction coordinate in the reference system; z n ——Subscript n represents the nth (n=i-1) uniform particle, z represents the direct The z-direction coordinate in the reference system; r n ——Subscript n represents the nth (n=i-1) uniform particle, r represents the uniform particle The radius of the body particle; x i ——Subscript i represents the i-th uniform particle, and x represents the x-direction coordinate in the direct coordinate system; y i ——Subscript i represents the i-th uniform particle, and y represents the y-direction coordinate in the direct coordinate system; z i ——Subscript i represents the i-th uniform mass particle, and z represents the z-direction coordinate in the direct coordinate system; r i ——Subscript i represents the i-th uniform mass particle, r represents the i-th uniform mass The radius of the particle; d - the maximum distance between particles, which increases the particle density in a limited space.

9. The method for modeling a hexagonal silicon carbide core component for space nuclear power according to claim 8, wherein: Also includes: Using Boolean operations, geometrically overlapping uniform particles are eliminated.

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