High-precision modeling method and system for solid propellant

Abstract

The invention belongs to the field of solid propellant performance prediction, and discloses a high-precision modeling method and system for a solid propellant, and the method comprises the steps: obtaining parameters of propellant components; the method comprises the following steps: constructing a solid propellant into a discrete system consisting of spherical particle units, and endowing the particle units with real physical parameters according to component thermodynamic parameters, reaction kinetic parameters and mechanical parameters of the propellant; establishing parallel bond bonds among particle units, and endowing the parallel bond bonds with real physical parameters according to the thermodynamic parameters, the reaction kinetic parameters and the mechanical parameters of propellant components; based on the real physical property parameters of the particle units and the parallel keys, a solid propellant high-precision model is established and used for providing a high-precision initial structure model for propellant ignition combustion process simulation and combustion performance prediction. According to the method, the problems that actual formula parameters such as particle size distribution and gradation are insufficiently considered and a microscopic combustion mechanism is difficult to capture in an existing method are solved, and the accuracy of a propellant numerical model is improved.

Description

Technical Field

[0001] This invention relates to the field of solid propellant performance prediction technology, and in particular to a high-precision modeling method and system for solid propellants. Background Technology

[0002] The statements in this section are merely background information related to the present invention and do not necessarily constitute prior art.

[0003] Solid propellants are the energy and working fluid source of solid rocket engines, fundamentally determining the engine's energy characteristics. With the development of computer technology, numerical simulation has become a powerful tool for studying solid propellant combustion. Regarding numerical simulation methods for solid propellants, since the 1950s, many scholars have proposed various one-dimensional models based on experimental phenomena. However, due to the one-dimensional nature of these models, the results differ significantly from the actual combustion process of the propellant. Some scholars have used sandwich models, but because they do not consider key formulation parameters such as particle size distribution and particle size distribution in actual propellants, it is difficult to quantify the differences in combustion performance under different formulations, and even more difficult to capture microscopic phenomena such as differences in local combustion rates caused by uneven particle size distribution. Therefore, to more accurately predict propellant performance, it is necessary not only to provide a more detailed description of the solid phase structure of the propellant, but also to have a clear understanding of the microscopic combustion mechanism of the propellant, the surface agglomeration of metal particles, and the distributed combustion mechanism, and to establish a comprehensive high-precision model of the propellant. Summary of the Invention

[0004] To address the aforementioned issues, this invention proposes a high-precision modeling method and system for solid propellants. This method solves the problems of insufficient consideration of actual formulation parameters such as particle size distribution and gradation in existing methods, as well as the difficulty in capturing microscopic combustion mechanisms, thereby improving the accuracy of propellant numerical models.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: In a first aspect, the present invention provides a high-precision modeling method for solid propellants, comprising the following steps: Obtain the thermodynamic parameters, reaction kinetic parameters, particle characteristic parameters, and mechanical parameters of the propellant components; Based on particle size distribution and gradation ratio in particle characteristic parameters, solid propellant is constructed as a discrete system composed of spherical particle units. According to the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of propellant components, the particle units are given real physical property parameters. Parallel bonding bonds are established between particle units, and the parallel bonding bonds are assigned real physical property parameters based on the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of the propellant components. Based on the real physical properties of particle units and parallel bonds, a high-precision model of solid propellant is established to provide a high-precision initial structural model for simulating the propellant ignition and combustion process and predicting combustion performance.

[0006] As an alternative implementation, the components of the solid propellant other than the binder are equivalent to spherical particle units, and the binder of the solid propellant is equivalent to parallel bonding bonds between spherical particle units.

[0007] As an alternative implementation, all components of the solid propellant are equivalent to spherical particle units, and the interfacial bonding between the spherical particles of each component is equivalent to the parallel bonding bonds between the spherical particle units.

[0008] As an alternative implementation, the particle size of the binder equivalent is not greater than the minimum particle size of the equivalent particles of other components.

[0009] As an alternative implementation, a dual failure triggering condition for the parallel bond is set: if the stress of the parallel bond exceeds the limit, mechanical fracture is triggered and failure occurs immediately, or if the temperature reaches the reaction temperature, a combustion reaction is triggered. Once the parallel bond is broken, it will not be re-established or generate a connecting force.

[0010] As an alternative implementation, the solid propellant is constructed as a discrete system composed of spherical particle units, and the particles are generated and released in descending order of radius range, using a "random release method" and a "cluster release method" to generate large and small particles respectively.

[0011] Secondly, the present invention provides a high-precision modeling system for solid propellants, comprising: The data acquisition module is configured to acquire thermodynamic parameters, reaction kinetic parameters, particle characteristic parameters, and mechanical parameters of propellant components. The particle modeling module is configured to: construct solid propellant as a discrete system composed of spherical particle units based on particle size distribution and gradation ratio in particle characteristic parameters, and assign real physical property parameters to particle units according to the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of propellant components; The parallel bond modeling module is configured to: establish parallel bonding bonds between particle units and assign realistic physical property parameters to the parallel bonding bonds based on the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of the propellant components; The model output and visualization module is configured to: establish a high-precision model of solid propellant based on the real physical property parameters of particle units and parallel bonds, which is used to provide a high-precision initial structural model for the simulation of propellant ignition and combustion process and the prediction of combustion performance.

[0012] Thirdly, the present invention provides an electronic device including a memory and a processor, and computer instructions stored in the memory and running on the processor, wherein the computer instructions, when executed by the processor, perform the method described in the first aspect.

[0013] Fourthly, the present invention provides a computer-readable storage medium for storing computer instructions, which, when executed by a processor, perform the method described in the first aspect.

[0014] Fifthly, the present invention provides a computer program product, including a computer program that, when executed by a processor, implements the method described in the first aspect.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows: This invention proposes a high-precision modeling method and system for solid propellants. By rigorously mapping the component ratios, thermodynamic and mechanical parameters of real propellants, it overcomes the simplification errors of traditional continuous medium models for non-uniform structures, achieving high-precision characterization at the microscale. Based on discrete particle systems, it accurately reproduces the spatial anisotropy of burning rate and differences in flame propagation caused by different particle size distributions and other formulation parameters. Furthermore, it can be combined with combustion models and polymerization models of metal particles, overcoming the bottleneck of traditional models' inability to analyze combustion performance differences caused by different formulations. By coupling parallel bond failure rules with thermodynamic parameters, it supports the mechanistic study of dynamic processes such as particle shedding during combustion, providing a new approach for optimizing propellant combustion stability.

[0016] Advantages of additional aspects of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0017] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an improper limitation of the invention.

[0018] Figure 1 This is a flowchart of a high-precision modeling method for solid propellants according to the present invention; Figure 2 This is a schematic diagram of the propellant model A constructed based on the discrete element method and parallel bonding model of the present invention; Figure 3 This is a schematic diagram of the propellant model B constructed based on the discrete element method and parallel bonding model of the present invention; Figure 4 This is a schematic diagram of the structure of a high-precision modeling system for solid propellants according to the present invention. Detailed Implementation

[0019] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0020] It should be noted that the following detailed description is exemplary and intended to provide further illustration of the invention. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains.

[0021] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments of the invention. As used herein, unless the context clearly indicates otherwise, the singular form is intended to include the plural form as well. Furthermore, it should be understood that the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but includes other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0022] Where there is no conflict, the embodiments and features in the embodiments of the present invention can be combined with each other.

[0023] Example 1 like Figure 1 As shown, this embodiment provides a high-precision modeling method for solid propellants, including the following steps: Step 1: Obtain the thermodynamic parameters, reaction kinetic parameters, particle characteristic parameters, and mechanical parameters of the propellant components; Step 2: Based on particle size distribution and gradation ratio in the particle characteristic parameters, the solid propellant is constructed as a discrete system composed of spherical particle units. According to the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of the propellant components, the particle units are given real physical property parameters. Step 3: Establish parallel bonding bonds between particle units, and assign real physical property parameters to the parallel bonding bonds based on the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of the propellant components; Step 4: Based on the real physical property parameters of particle units and parallel bonds, establish a high-precision model of solid propellant to provide a high-precision initial structural model for propellant ignition and combustion process simulation and combustion performance prediction.

[0024] The specific solution of the present invention is as follows: This invention provides a high-precision modeling method for solid propellants, which is applicable to propellant combustion performance prediction and multi-component formulation optimization. It overcomes the shortcomings of existing models, such as insufficient consideration of actual formulation parameters like particle size distribution and gradation, and difficulty in capturing microscopic combustion mechanisms.

[0025] Microscopic modeling of particle size distribution and particle gradation of solid propellants is performed. The microscopic models of the solid propellants in this invention include two types: Model A: The components other than the binder of the solid propellant are generated into spherical particle units, and the binder of the solid propellant is equivalent to the parallel bonding bonds between the spherical particle units.

[0026] Model B: All components of the solid propellant are generated into spherical particle units, and the interfacial bonding between the spherical particles of each component is equivalent to the parallel bonding bonds between the spherical particle units.

[0027] In Model B, the binder particles are uniformly distributed among the other components, which better matches the actual microscopic cross-section of the propellant, making it more intuitive and easier to understand. However, because the binder is also considered as a particle, and its particle size is smaller, the number of particles in the system increases significantly, thus increasing computational costs. By introducing realistic particle size distribution and gradation ratios into the numerical simulation of solid propellant combustion performance through microscopic modeling, the impact of formulation changes on combustion can be quantified, capturing the microscopic combustion mechanism and improving the accuracy of the numerical simulation.

[0028] Further, step 1 includes: The specific heat capacity of the components is obtained through literature or differential scanning calorimetry experiments, and the heat capacity contribution of interparticle heat conduction is calculated; the thermal conductivity of the components is obtained through literature or thermal conductivity experiments; the calorific value of the components is determined by citing literature or oxygen bomb calorimetry to quantify the intensity of combustion energy release; the activation energy and pre-exponential factor are obtained based on literature data or thermogravimetric analysis to characterize the combustion reaction kinetic process; all data are integrated to construct a parameter database, the source is labeled, and confidence weights are used to accommodate different implementation conditions.

[0029] Particle size distribution is obtained through experimental methods such as laser diffraction or literature data. The volume ratio of different particle size ranges is measured to construct gradation curves, which are used to accurately calculate the number of particles in each particle size range in the discrete system, thereby ensuring that the model is completely consistent with the actual propellant formulation in terms of particle size distribution and volume ratio. The propellant porosity is obtained by calibrating the gradation ratio using particle size distribution data in combination with density or rheological targets. Key mechanical parameters such as the elastic modulus and Poisson's ratio of particles are obtained through contact stiffness response tests or existing literature. The parallel bond strength threshold is obtained by combining interfacial strength tests or literature data. The contact stiffness parameters are derived from literature data or calibration procedures and must meet the requirements of dynamic behavior verification. All data are integrated to construct a parameter database, and confidence weights are assigned according to the data source type to ensure reliability.

[0030] Further, step 2 includes: Based on the discrete element method, a discrete particle sample modeling system is used to determine the range of propellant model samples. Combining particle size distribution, porosity, gradation curves, etc., radius intervals are divided, the total number of particles and the number of particles in each interval are calculated, and a particle radius threshold is set. The first 50%~90% of the radius interval is for large particles and the last 50%~10% is for small particles. Particles are generated and released in descending order of radius interval. The "random release method" and the "cluster release method" are used to generate large and small particles respectively, and a discrete system composed of spherical particle units is constructed to ensure that the particle size distribution meets the gradation ratio specified in step 1.

[0031] Assigning true density values ​​to particles to distinguish the characteristics of different components; mapping thermophysical parameters such as specific heat and thermal conductivity obtained in step 1 to calculate particle temperature; mapping chemical reaction kinetic parameters such as activation energy and pre-exponential factor to calculate particle combustion rate; synchronously associating mechanical properties such as elastic modulus and Poisson's ratio determined in step 1 to calculate particle force; and achieving structural characterization of components such as oxidants and metallic fuels through component identification parameters. The model constructed in this step includes two types. Model A generates spherical units for components other than the binder (such as oxidant and metal fuel) according to the above steps. The binder is not equivalent at the moment, but will be equivalent later through parallel bonding bonds. Model B generates spherical units for all components according to the above steps. The binder is equivalent to particles of 1-10 micrometers (not larger than the smallest particle size of other components). The radius range is divided according to this particle size, the number of particles is calculated and the particles are placed to ensure that the binder particles can fill the gaps between other component particles or coat other particles.

[0032] Further, step 3 includes: Based on the two model types in step 2, parallel bonding bonds between particles are established to represent the bonding effect within the propellant: In Model A, the binder is directly equivalent to the parallel bonding bonds between particle units. Parallel bonding bonds are established between spatially adjacent particle pairs of oxidizer and metallic fuel particles generated in step 2. The physical and chemical functions of the binder are simulated through the characteristics of the bonding bonds. In Model B, only the interfacial bonding effect between the particle components is represented by parallel bonding bonds. Parallel bonding bonds are established between adjacent particle pairs of oxidizer, metallic fuel, and binder particles generated in step 2. The bonding bonds only characterize the interfacial bonding force between particles, and the properties of the binder itself are reflected through the physical properties of its particle units. Assigning realistic parameters to parallel bonds: In Model A, mechanical parameters such as tensile strength, shear strength, elastic modulus, and Poisson's ratio, thermophysical parameters such as specific heat and thermal conductivity, and chemical reaction kinetic parameters such as activation energy and pre-exponential factor of the binder are assigned to the parallel bonds; In Model B, since the binder is also equivalent to particles, the thermophysical parameters and reaction kinetic parameters have already been assigned to the binder particles in step 2, so only the mechanical parameters of the parallel bonds need to be assigned.

[0033] The system sets dual failure trigger conditions for parallel bond bonds: exceeding the stress limit of the parallel bond triggers mechanical fracture and immediate failure; reaching the reaction temperature triggers a combustion reaction; once the parallel bond breaks, it will not be re-established or generate bonding force. This can simulate both normal propellant combustion and unexpected structural damage and instability of the propellant.

[0034] Further, step 4 includes: Based on the microscopic models (Model A and Model B) established in steps 2 and 3, high-precision models of solid propellants are established to provide high-precision initial structural models for propellant ignition and combustion process simulation and combustion performance prediction.

[0035] Model A and Model B are two different branches of high-precision modeling of solid propellants, representing two different equivalent approaches. High-precision models of solid propellants are established based on these two different equivalent approaches. Among them, the high-precision model of solid propellants based on Model B has more particles and a slower calculation speed. However, because the binder particles are uniformly filled in the gaps between other particles, it is closer to the microscopic slice of the actual propellant and has a more intuitive structure.

[0036] The constructed high-precision model is a static, preliminary microstructural mathematical model that can realistically reflect the characteristics of propellant formulation (such as particle size distribution and gradation) and can be used as an initial structural model for calculation. This model can be directly used for subsequent mechanical and thermodynamic numerical simulation analysis: given an initial ignition temperature, the particles are heated and pyrolyzed, releasing gas. The gas undergoes a chemical reaction to generate heat, which is fed back to the particles and parallel bonds, and the temperature continues to rise for pyrolysis and combustion. At the same time, attention is paid to the unexpected structural damage and combustion instability caused by strong gas-structure interaction that may occur during the combustion process. The constructed high-precision model incorporates information such as particle location and mechanical / thermodynamic properties, serving as the basis for coupled analysis of ignition, combustion, and structural response.

[0037] The following is a specific example to illustrate the solution of the present invention.

[0038] A high-precision modeling method for hydroxyl-butadiene three-component solid propellants, specifically including: Step 1: Obtain the thermodynamic parameters and chemical reaction kinetic parameters of the propellant components, and establish a standardized parameter database.

[0039] Specifically, the specific heats of each component were obtained through literature or DSC experiments: AP / HTPB was 1255 J / (kg·K), and Al was 880 J / (kg·K); the calorific value was determined by citing literature or oxygen bomb calorimetry, and HTPB was -1.26 × 10⁻⁶. 6 J / kg, AP is -0.42×10 6 J / kg, Al is 31×10 6 J / kg; thermal conductivity obtained from literature: HTPB is 0.276 W / (m·K), AP is 0.405 W / (m·K), and Al is 237 W / (m·K); pre-exponential factor and activation energy of chemical reactions were obtained through DSC / TGA experimental fitting or literature; specific parameters are shown in Table 1; a structured database was established and confidence weights were assigned according to the source.

[0040] Table 1. Some physical properties of the hydroxyl-butyl three-component propellant;

[0041] Obtain the true particle size distribution, gradation ratio, and basic mechanical parameters of the propellant components.

[0042] Specifically, the particle size distribution of a typical hydroxyl-butadiene (HTPB) three-component propellant was obtained by laser diffraction or literature: AP particle size 75-424 μm (average particle size of types 1, 3, and 4: 424 μm, 140 μm, and 75 μm, respectively), Al average particle size 29 μm, as shown in Table 2; mass percentage AP:Al:HTPB = 70:18:12; particle mechanical parameters were obtained by nanoindentation or literature: AP elastic modulus 10 GPa, Poisson's ratio 0.25, Al elastic modulus 69 GPa, Poisson's ratio 0.33; the HTPB interfacial tensile strength was 1.1 MPa obtained by splitting test and literature, and the cohesion was 5.6 MPa and friction angle was 12° obtained by triaxial shear test and literature; a structured database was established, and confidence weights were assigned according to the source.

[0043] Table 2. Formulation ratio of hydroxyl-butyl three-component propellant;

[0044] Step 2: Based on the discrete element method, the solid propellant is constructed as a discrete system composed of a series of spherical particle units, and the particles are given real physical property parameters.

[0045] Specifically, based on the discrete element method, a multiphase discrete system composed of rigid spherical particles is generated through a discrete particle sample modeling system: ensuring that AP particles are distributed according to the gradation ratio specified in step 1, and Al particles are uniformly filled (Model A); or the binder is also equivalent to spherical particles, uniformly distributed between AP and Al particles (Model B); assigning true density values ​​to the particles to distinguish component characteristics; mapping the thermodynamic parameters and chemical reaction kinetic parameters (specific heat capacity, calorific value, activation energy, etc.) obtained in step 1 to the corresponding particles for subsequent particle temperature and combustion rate calculations; synchronously associating the mechanical properties (elastic modulus, Poisson's ratio, etc.) obtained in step 1 to the corresponding particles for subsequent particle stress calculations; and distinguishing component affiliation by density to achieve spatial structural characterization of propellant component particles.

[0046] Step 3: Based on the parallel bonding model, the binder in the propellant is equivalent to the parallel bonding bonds between spherical particle units, and the parallel bonds are given real properties; Specifically, based on the discrete system generated in step 2, HTPB is equivalent to parallel bonding bonds between particles (Model A); or only the bonding effect between propellant components is equivalent to parallel bonding bonds between particles (Model B); the interface strength data (tensile strength, cohesion, friction angle, etc.) obtained in step 2 is mapped to calculate the force on the parallel bonds, and the thermodynamic and chemical reaction kinetic properties of the binder are given to calculate the combustion rate of the parallel bonds; if the stress of the parallel bonds exceeds the limit, mechanical fracture is triggered and failure occurs immediately; if the temperature reaches the reaction temperature, a combustion reaction is triggered; once the parallel bonds are broken, they will not be re-established or generate bonding force.

[0047] Step 4: Establish a high-precision model of solid propellant for propellant mechanical property analysis and testing, as well as ignition and combustion process simulation.

[0048] Example 2 like Figure 4 As shown, this embodiment provides a high-precision modeling system for solid propellants, including: The data acquisition module is configured to acquire thermodynamic parameters, reaction kinetic parameters, particle characteristic parameters, and mechanical parameters of propellant components. The particle modeling module is configured to: construct solid propellant as a discrete system composed of spherical particle units based on particle size distribution and gradation ratio in particle characteristic parameters, and assign real physical property parameters to particle units according to the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of propellant components; The parallel bond modeling module is configured to: establish parallel bonding bonds between particle units and assign realistic physical property parameters to the parallel bonding bonds based on the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of the propellant components; The model output and visualization module is configured to: establish a high-precision model of solid propellant based on the real physical property parameters of particle units and parallel bonds, which is used to provide a high-precision initial structural model for the simulation of propellant ignition and combustion process and the prediction of combustion performance.

[0049] It should be noted that the above modules correspond to the steps in Embodiment 1, and the examples and application scenarios implemented by the above modules and their corresponding steps are the same, but are not limited to the content disclosed in Embodiment 1. It should also be noted that the above modules can be executed in a computer system as part of the system.

[0050] In further embodiments, the following is also provided: An electronic device includes a memory and a processor, as well as computer instructions stored in the memory and running on the processor, which, when executed by the processor, perform the method described in Embodiment 1. For brevity, further details are omitted here.

[0051] It should be understood that in this embodiment, the processor can be a central processing unit (CPU), or it can be other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. A general-purpose processor can be a microprocessor or any conventional processor.

[0052] A computer-readable storage medium for storing computer instructions that, when executed by a processor, perform the method of Embodiment 1.

[0053] The method in Example 1 can be directly executed by a hardware processor, or it can be executed by a combination of hardware and software modules within the processor. The software modules can reside in readily available storage media in the art, such as random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, or registers. This storage medium is located in memory; the processor reads information from the memory and, in conjunction with its hardware, completes the steps of the above method. To avoid repetition, a detailed description is not provided here.

[0054] A computer program product includes a computer program that, when executed by a processor, implements the method in Embodiment 1.

[0055] The present invention also provides at least one computer program product tangibly stored on a non-transitory computer-readable storage medium. The computer program product includes computer-executable instructions, such as instructions included in program modules, which execute in a device on a target real or virtual processor to perform the processes / methods described above. Typically, program modules include routines, programs, libraries, objects, classes, components, data structures, etc., that perform specific tasks or implement specific abstract data types. In various embodiments, the functionality of program modules can be combined or divided among program modules as needed. The machine-executable instructions for the program modules can execute within a local or distributed device. In a distributed device, the program modules can reside in both local and remote storage media.

[0056] The computer program code used to implement the methods of the present invention may be written in one or more programming languages. This computer program code may be provided to a processor of a general-purpose computer, a special-purpose computer, or other programmable data processing device, such that when executed by the computer or other programmable data processing device, the program code causes the functions / operations specified in the flowcharts and / or block diagrams to be implemented. The program code may be executed entirely on a computer, partially on a computer, as a stand-alone software package, partially on a computer and partially on a remote computer, or entirely on a remote computer or server.

[0057] In the context of this invention, computer program code or related data may be carried by any suitable carrier to enable a device, apparatus, or processor to perform the various processes and operations described above. Examples of carriers include signals, computer-readable media, and the like. Examples of signals may include electrical, optical, radio, sound, or other forms of propagation signals, such as carrier waves, infrared signals, etc.

[0058] Those skilled in the art will recognize that the units and algorithm steps described in conjunction with the embodiments herein can be implemented in electronic hardware or a combination of computer software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.

[0059] While the specific embodiments of the present invention have been described above in conjunction with the accompanying drawings, this is not intended to limit the scope of protection of the present invention. Those skilled in the art should understand that various modifications or variations that can be made by those skilled in the art without creative effort based on the technical solutions of the present invention are still within the scope of protection of the present invention.

Claims

1. A high-precision modeling method for solid propellants, characterized in that, Includes the following steps: Obtain the thermodynamic parameters, reaction kinetic parameters, particle characteristic parameters, and mechanical parameters of the propellant components; Based on particle size distribution and gradation ratio in particle characteristic parameters, solid propellant is constructed as a discrete system composed of spherical particle units. According to the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of propellant components, the particle units are given real physical property parameters. Parallel bonding bonds are established between particle units, and the parallel bonding bonds are assigned real physical property parameters based on the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of the propellant components. Based on the real physical properties of particle units and parallel bonds, a high-precision model of solid propellant is established to provide a high-precision initial structural model for simulating the propellant ignition and combustion process and predicting combustion performance.

2. The high-precision modeling method for solid propellants as described in claim 1, characterized in that, The components of solid propellant other than the binder are equivalent to spherical particle units, and the binder of solid propellant is equivalent to parallel bonding bonds between spherical particle units.

3. The high-precision modeling method for solid propellants as described in claim 1, characterized in that, All components of the solid propellant are equivalent to spherical particle units, and the interfacial bonding between the spherical particles of each component is equivalent to the parallel bonding bonds between the spherical particle units.

4. The high-precision modeling method for solid propellants as described in claim 3, characterized in that, The equivalent particle size of the binder is no larger than the minimum particle size of the equivalent particles of other components.

5. The high-precision modeling method for solid propellants as described in claim 1, characterized in that, The dual failure triggering conditions for parallel bond bonds are set: if the stress of the parallel bond exceeds the limit, mechanical fracture is triggered and failure occurs immediately; or if the temperature reaches the reaction temperature, a combustion reaction is triggered. Once the parallel bond is broken, it will not be re-established or generate bonding force.

6. The high-precision modeling method for solid propellants as described in claim 1, characterized in that, Solid propellant is constructed as a discrete system composed of spherical particle units. Particles are generated and released in descending order of radius range, using both "random release method" and "cluster release method" to generate large and small particles respectively.

7. A high-precision modeling system for solid propellants, characterized in that, include: The data acquisition module is configured to acquire thermodynamic parameters, reaction kinetic parameters, particle characteristic parameters, and mechanical parameters of propellant components. The particle modeling module is configured to: construct solid propellant as a discrete system composed of spherical particle units based on particle size distribution and gradation ratio in particle characteristic parameters, and assign real physical property parameters to particle units according to the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of propellant components; The parallel bond modeling module is configured to: establish parallel bonding bonds between particle units and assign realistic physical property parameters to the parallel bonding bonds based on the thermodynamic parameters, reaction kinetic parameters and mechanical parameters of the propellant components; The model output and visualization module is configured to: establish a high-precision model of solid propellant based on the real physical property parameters of particle units and parallel bonds, which is used to provide a high-precision initial structural model for the simulation of propellant ignition and combustion process and the prediction of combustion performance.

8. An electronic device, characterized in that, It includes a memory and a processor, as well as computer instructions stored in the memory and running on the processor, which, when executed by the processor, perform the method according to any one of claims 1-6.

9. A computer-readable storage medium, characterized in that, Used to store computer instructions, which, when executed by a processor, perform the method described in any one of claims 1-6.

10. A computer program product, characterized in that, Includes a computer program, which, when executed by a processor, implements the method described in any one of claims 1-6.

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