Impact detonation simulation method and device of solid engine, medium and equipment

Abstract

The invention relates to the technical field of solid engine safety evaluation, and discloses an impact detonation simulation method and device of a solid engine, a medium and equipment, and the method comprises the steps: building a first geometric model corresponding to the solid engine and a second geometric model corresponding to a fragment, grid division is carried out on the first geometric model and the second geometric model; determining a first material model corresponding to the solid engine and a second material model corresponding to the fragments; in response to a parameter setting operation for the fragment, setting a motion parameter of the fragment; and according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments, simulating the impact initiation characteristics of the solid engine.

Description

Technical Field

[0001] The present application relates to the technical field of solid motor safety assessment, and in particular to a method, device, medium and equipment for simulating impact detonation of a solid motor. Background Art

[0002] Solid engines are the main energy-containing components as the power system of related weapons and new energy vehicles. During service, the entire engine may be subjected to severe fragmentation or shock wave impact due to attacks or explosions of other weapons around it. At this time, the propellant inside the engine will be fractured and damaged by the impact compression effect and form hot spots. When the hot spots are formed, the propellant will undergo a chemical reaction. After the reaction is enhanced, the propellant will burn or even explode. The main purpose of engine shock safety research is to obtain the pressure, impulse and other parameters of critical detonation of different types of weapons, and then avoid the occurrence of shock detonation through reasonable protection and storage structure design.

[0003] The research on engine shock detonation is mainly divided into two categories: simulation calculation and experiment. Among them, the simulation research on shock detonation is low-cost and can verify the experiment numerically to a certain extent, so many studies at this stage are based on simulation. The models currently used in simulation usually adopt a complete modeling method, including the impacted engine, the impact source (fragments or main explosive bomb), etc. Some models also need to model the propagation medium of the shock (such as air). When the parameters such as the model and material strength meet the actual working conditions, the simulation can make a theoretical judgment on the shock detonation situation of the working condition, and use this to guide the design of the experiment.

[0004] The current impact detonation simulation scheme for solid motors usually adopts a complete modeling approach, that is, the focus is mainly on the load formed when the fragments impact and contact the engine, and whether the load will detonate the engine. If an external medium domain is established, it will obviously waste computing resources; and even if the external medium domain is established, the complete modeling method can only control parameters such as fragment velocity and fragment size, and cannot obtain the impact information on the engine, thus making it impossible to accurately perform impact detonation simulation analysis of solid motors. Summary of the invention

[0005] Based on this, the present application provides a method, device, medium and equipment for shock detonation simulation of a solid motor, which can accurately perform shock detonation simulation analysis of the solid motor, thereby making the shock detonation research of the solid motor more in-depth.

[0006] In a first aspect, an embodiment of the present application provides a method for simulating impact detonation of a solid rocket motor, comprising:

[0007] Establishing a first geometric model corresponding to the solid motor and a second geometric model corresponding to the fragments, and meshing the first geometric model and the second geometric model respectively;

[0008] Determining a first material model corresponding to the solid motor and a second material model corresponding to the fragment;

[0009] In response to a parameter setting operation for the fragment, setting a motion parameter of the fragment;

[0010] The impact detonation characteristics of the solid motor are simulated according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments.

[0011] Optionally, in some embodiments of the present application, establishing a first geometric model corresponding to the solid motor and a second geometric model corresponding to the fragments, and meshing the first geometric model and the second geometric model respectively, comprises:

[0012] Get the basic model corresponding to the solid engine;

[0013] Determining design parameters of the solid motor;

[0014] Based on the basic model and design parameters, a first geometric model corresponding to the solid motor is established;

[0015] Creating a basic shape of a fragment, and establishing a second geometric model corresponding to the fragment according to fragment parameters preset in the basic shape;

[0016] The first geometric model and the second geometric model are meshed according to a common characteristic length between the first geometric model and the second geometric model.

[0017] Optionally, in some embodiments of the present application, meshing the first geometric model and the second geometric model according to a common characteristic length between the first geometric model and the second geometric model includes:

[0018] determining an impact location between the first geometric model and the second geometric model;

[0019] Determining a common characteristic length between the first geometric model and the second geometric model according to the impact position, and determining a global grid size corresponding to the common characteristic length;

[0020] The first geometric model and the second geometric model are meshed based on the global mesh size.

[0021] Optionally, in some embodiments of the present application, simulating the impact detonation characteristics of the solid motor according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments includes:

[0022] determining a charge area in the first geometric model;

[0023] Determining a fluid model corresponding to the charge area;

[0024] Setting a coupling interface between the first geometric model and the second geometric model;

[0025] The impact detonation characteristics of the solid motor are simulated according to the fluid model, the coupling interface of the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments.

[0026] Optionally, in some embodiments of the present application, simulating the impact detonation characteristics of the solid motor according to the fluid model, the coupling interface of the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments includes:

[0027] Set the initial state of the charge area;

[0028] adjusting the shape of the second geometric model;

[0029] Based on the fluid model, different shapes of the second geometric model, the coupling interface between the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments, the impact detonation characteristics of the solid motor are simulated.

[0030] Optionally, in some embodiments of the present application, simulating the impact detonation characteristics of the solid motor based on the fluid model, different shapes of the second geometric model, the coupling interface between the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments includes:

[0031] Based on the fluid model, different shapes of the second geometric model, the coupling interface between the first geometric model and the second geometric model, the first material model, the second material model, and the motion parameters of the fragments, simulating the fragment penetration information of the fragments impacting the solid motor and the deformation information of the motor casing;

[0032] The impact detonation characteristics of the solid motor are simulated according to the fragment penetration information and the deformation information.

[0033] Optionally, in some embodiments of the present application, simulating the impact detonation characteristics of the solid motor according to the fragment penetration information and the deformation information includes:

[0034] Determining the impact detonation threshold of the solid motor according to the fragment penetration information and the deformation information;

[0035] Identifying the deformation information to obtain a damage area and a crack propagation path of the fragment after impacting the solid motor;

[0036] The shock detonation characteristics of the solid motor are simulated according to the shock detonation threshold, the damage area and the crack propagation path.

[0037] In a second aspect, the embodiment of the present application further provides an impact detonation simulation device for a solid rocket engine, comprising:

[0038] An establishment module is used to establish a first geometric model corresponding to the solid motor and a second geometric model corresponding to the fragments, and to mesh the first geometric model and the second geometric model respectively;

[0039] A determination module, used to determine a first material model corresponding to the solid motor and a second material model corresponding to the fragment;

[0040] A setting module, configured to set the motion parameters of the fragment in response to a parameter setting operation for the fragment;

[0041] A simulation module is used to simulate the impact detonation characteristics of the solid motor according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments.

[0042] In a third aspect, an embodiment of the present application provides a computer-readable storage medium storing a computer program. When the computer program is executed by a processor, the processor performs the steps of the above-mentioned impact detonation simulation method of the solid motor.

[0043] In a fourth aspect, an embodiment of the present application provides a computer device, including a memory and a processor, wherein the memory stores a computer program, and when the computer program is executed by the processor, the processor executes the steps of the above-mentioned solid engine impact detonation simulation method.

[0044] The embodiment of the present application provides a method, device, medium and equipment for simulating the impact detonation of a solid engine. After establishing a first geometric model corresponding to the solid engine and a second geometric model corresponding to the fragments, and meshing the first geometric model and the second geometric model respectively, the first material model corresponding to the solid engine and the second material model corresponding to the fragments are determined. In response to the parameter setting operation for the fragments, the motion parameters of the fragments are set. Finally, according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments, the impact detonation characteristics of the solid engine are simulated. In the impact detonation simulation scheme of the solid engine provided in the present application, after establishing the first geometric model and the second geometric model, the first geometric model and the second geometric model are meshed respectively to facilitate the subsequent capture of the impact process. In addition, the motion parameters of the fragments can be set according to different verification requirements. Therefore, the accuracy and practicality of the impact detonation simulation results can be ensured. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0046] in:

[0047] Figure 1 It is a flow chart of the impact detonation simulation method of the solid motor provided in the embodiment of the present application;

[0048] Figure 2 It is a geometric model of a cubic fragment impacting a high-energy solid motor provided in an embodiment of the present application;

[0049] Figure 3 It is a simulation schematic diagram of a cubic fragment impacting a high-energy solid engine provided by an embodiment of the present application;

[0050] Figure 4 It is a schematic diagram of simulation results of cubic fragments impacting a high-energy solid rocket engine provided by an embodiment of the present application;

[0051] Figure 5 is a graph showing the relationship between shell thickness and critical detonation speed provided in an embodiment of the present application;

[0052] Figure 6 It is a graph of impact values ​​of fragments of different materials provided in the embodiments of the present application;

[0053] Figure 7This is the result diagram of simulating the engine being detonated by fragments of equal cross-sectional area but different aspect ratios;

[0054] Figure 8 It is a simulation diagram of the aspect ratio of the fragments and the detonation speed of the fragments impacting the engine;

[0055] Fig. 9 It is a graph showing the relationship between the aspect ratio of the fragments and the detonation speed of the fragments impacting the engine;

[0056] Fig.10 It is a structural schematic diagram of an impact detonation simulation device for a solid motor provided in an embodiment of the present application;

[0057] Fig.11 It is a structural schematic diagram of the computer device provided by this application. DETAILED DESCRIPTION

[0058] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0059] The present application provides a method, device, medium and equipment for simulating impact detonation of a solid rocket motor.

[0060] Among them, the impact detonation simulation device of the solid engine provided by the present application can be integrated in a computer device, and the computer device can be directly or indirectly connected to the computer device through wired or wireless communication. The computer device can be a smart phone, a tablet computer, a laptop computer, a desktop computer, a smart speaker or a smart watch, etc., but is not limited to this. In addition, the computer device can also be connected to a server. The server can be an independent physical server, or a server cluster or distributed system composed of multiple physical servers. It can also be a cloud server that provides cloud services, cloud databases, cloud computing, cloud functions, cloud storage, network services, cloud communications, middleware services, domain name services, security services, CDN (Content Delivery Network, Chinese name is content distribution network), and big data and artificial intelligence platforms and other basic cloud computing services. This application does not limit this.

[0061] The present application provides a method for simulating the impact detonation of a solid engine, comprising: establishing a first geometric model corresponding to the solid engine and a second geometric model corresponding to the fragments, and meshing the first geometric model and the second geometric model respectively; determining a first material model corresponding to the solid engine and a second material model corresponding to the fragments; setting motion parameters of the fragments in response to a parameter setting operation for the fragments; and simulating the impact detonation characteristics of the solid engine according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments.

[0062] See also Figure 1 , Figure 1 The following is a flow chart of the impact detonation simulation method of a solid motor provided in this application. The specific flow of the impact detonation simulation method of the solid motor can be as follows:

[0063] 101. Establish a first geometric model corresponding to the solid motor and a second geometric model corresponding to the fragments, and mesh the first geometric model and the second geometric model respectively.

[0064] Among them, establishing the first geometric model corresponding to the solid engine and the second geometric model corresponding to the fragments refers to establishing a digital three-dimensional representation corresponding to the fixed engine and a digital three-dimensional representation corresponding to the fragments. The first geometric model includes all key components of the engine, such as the combustion chamber, nozzle, casing, etc.; the second geometric model can be a preset shape (such as a sphere, a cylinder or an irregular shape) and has a specific size and mass. It should be noted that the number of fragments can be one or more, and can be set according to actual conditions.

[0065] Fragments are pieces of debris that hit the solid engine. Fragments are objects other than the solid engine.

[0066] For example, if the combustion chamber of a solid engine has a diameter of 1 meter and a length of 3 meters, a cylindrical chamber model with a diameter of 1 meter and a length of 3 meters can be created, including other components such as nozzles and casings, to ensure that the size and shape of all components are consistent with the actual design; for fragment models, a spherical fragment model with a diameter of 0.1 meters, or a cylindrical fragment model with a diameter of 0.2 meters, as well as irregularly shaped fragment models with specific masses can be created to adapt to different simulation scenarios.

[0067] Optionally, in some embodiments of the present application, the geometric parameters of the model are shown in Table 1 below:

[0068] Table 1. Engine geometry model and meshing parameters for fragment impact simulation

[0069]

[0070] The geometric model of cubic fragments impacting high-energy solid rocket is as follows: Figure 2 As shown, in Figure 2 In the figure, the first geometric model S1 is the geometric model of the high-energy solid rocket engine, and the second geometric model S2 is the geometric model of the cubic fragments.

[0071] After the geometric model is established, meshing is performed to convert the three-dimensional model into a mesh system composed of multiple small elements for the calculation of physical quantities such as stress and strain in numerical analysis. By simulating the situation where fragments hit the engine at different speeds, the reaction of the engine can be predicted. Optionally, in some embodiments of the present application, a reference point is set every other time on the axis to obtain data, such as Figure 2 shown.

[0072] Optionally, in some embodiments of the present application, the step of “establishing a first geometric model corresponding to the solid motor and a second geometric model corresponding to the fragments, and meshing the first geometric model and the second geometric model respectively” may specifically include:

[0073] Get the basic model corresponding to the solid engine;

[0074] Determine the design parameters of solid rocket motors;

[0075] Based on the basic model and design parameters, a first geometric model corresponding to the solid engine is established;

[0076] Creating a basic shape of the fragment, and establishing a second geometric model corresponding to the fragment according to the fragment parameters preset in the basic shape;

[0077] The first geometric model and the second geometric model are meshed according to a common characteristic length between the first geometric model and the second geometric model.

[0078] Common characteristic length is a term used in simulation and model analysis to refer to a set of basic features or scale parameters used to define the scale of dimensions in a model. This concept is particularly important in geometric models of solid motors and fragments because it helps ensure that the model is scaled consistently in simulation and reflects the key dimensional characteristics of the real object. When performing numerical simulations, the common characteristic length is used to determine the size of the mesh elements. Smaller characteristic lengths may require a finer mesh to capture details, while larger characteristic lengths may allow for a coarser mesh.

[0079] The basic model refers to an initial or reference model of the geometric shape and structure of the solid engine, which can be imported from the data of the computer-aided design software, or generated according to the engineering design drawings and specifications, and can be selected according to the actual situation. Based on the basic model and the determined design parameters, a more detailed and accurate first geometric model can be created. This model will be used for subsequent meshing and simulation analysis. Similar to the model of the solid engine, the basic shape and parameters of the fragments also need to be defined to create the corresponding second geometric model. After the geometric models of the solid engine and the fragments are established, it is necessary to mesh them according to the common characteristic length between them in order to perform subsequent numerical simulations, that is, optionally, in some embodiments of the present application, the step of "meshing the first geometric model and the second geometric model according to the common characteristic length between the first geometric model and the second geometric model" can specifically include:

[0080] determining an impact location between the first geometric model and the second geometric model;

[0081] Determine a common characteristic length between the first geometric model and the second geometric model according to the impact position, and determine a global mesh size corresponding to the common characteristic length;

[0082] The first geometric model and the second geometric model are meshed based on the global mesh size.

[0083] In order to accurately define the location where the fragments (second geometric model) collide with the solid motor (first geometric model). The determination of the impact location is crucial to the accuracy of the simulation because it directly affects the propagation of stress waves, energy transfer, and possible damage modes in the simulation.

[0084] After the impact location is determined, the next step is to determine the common characteristic length between the two geometries. This length is a key parameter used to maintain consistent dimensional ratios in the simulation and ensure that the meshing can capture the details of the impact area. The common characteristic length may be related to the thickness of the engine casing near the impact point, the size of the fragment, or the relative size between the two. Based on the common characteristic length, the global mesh size can be determined. The mesh size refers to the size of the unit or element used in meshing. Choosing the right mesh size is very important to balance the accuracy of the simulation and the computational cost. The mesh size should be small enough to ensure that the stress waves and possible material failure processes generated by the impact can be captured; at the same time, it should be large enough to avoid excessive computational resources. Finally, based on the determined global mesh size, the first geometry model (solid engine) and the second geometry model (fragment) are meshed. This step involves dividing the geometry model into many small mesh cells so that numerical methods can be applied on these meshes to solve physical equations such as stress, strain, velocity, and pressure. Meshing requires using finer meshes in the impact area and possible material failure areas to improve the accuracy of the simulation.

[0085] 102. Determine a first material model corresponding to the solid motor and a second material model corresponding to the fragment.

[0086] The material model of a solid motor needs to reflect the physical and chemical properties of its structural materials and propellants. This typically includes the material's density, elastic modulus, Poisson's ratio, thermal conductivity, stress-strain relationships, etc. For example, if the motor casing is made of a specific alloy, the mechanical properties and chemical stability of the alloy need to be accurately defined and simulated. The material model of the fragments needs to be defined based on the expected material of the fragments, which may include metals, ceramics, or other composite materials. The model needs to include key parameters such as the fracture toughness, hardness, and yield strength of the fragment material. For example, if the fragments are made of high-strength steel, the detailed mechanical properties of the material will be used in the simulation.

[0087] For a solid rocket engine, if the combustion chamber casing is made of a specific aluminum alloy, the first material model needs to be defined based on the actual physical properties of the aluminum alloy. This may include setting the elastic modulus of the material to 70GPa, Poisson's ratio to 0.3, and a stress-strain curve defined based on experimental data or a material database.

[0088] For fragments, if they are made of high carbon steel, the second material model will include parameters such as density, yield strength, tensile strength, etc. of high carbon steel. For example, the elastic modulus of high carbon steel can be set to 210 GPa, Poisson's ratio to 0.29, and a suitable plastic deformation model to describe its response under impact load.

[0089] Optionally, in some embodiments of the present application, the fragments are made of 45# steel, 2024 aluminum or tungsten alloy, the shell is made of 30CrMnSiA steel, and both the fragments and the engine shell are controlled by the Jhonson-Cook model and the Grunesie state equation (also known as the Grüneisen parameter, which is used to measure the thermodynamic state change per unit volume). The Jhonson-Cook model is a widely used constitutive model, which is mainly used to describe the behavior of materials under high strain rate conditions, especially the deformation and fracture characteristics of metals in impact and explosion events. The model combines the plastic flow, strain hardening, strain rate sensitivity and thermal softening effect of the material, and can more accurately predict the behavior of the material under dynamic load.

[0090] The basic form of the Johnson-Cook model is as follows:

[0091] in:

[0092] σ is the von Mises stress (equivalent stress). A and B are parameters related to the yield strength of the material, A represents the initial yield strength of the material, and B represents the strain hardening effect. is the effective plastic strain. n is an exponent related to strain hardening. C is a constant related to the strain rate sensitivity of the material. is the effective plastic strain rate. is a normalized representation of temperature, usually expressed as the ratio of the material's melting point to the current temperature. m is the temperature-dependent thermal softening index.

[0093] A key feature of the Jhonson-Cook (JC) model is its ability to adjust parameters to accommodate the behavior of different materials at different strain rates and temperatures. This makes the model well suited for simulating dynamic events such as the impact detonation characteristics of solid rocket motors, where materials undergo rapid deformation and a variety of complex mechanical processes.

[0094] In practical applications, the parameters of the Jhonson-Cook model need to be determined through experiments, which may include tensile tests, compression tests, high-speed impact tests, etc., to obtain the mechanical response data of the material under different conditions. Once these parameters are determined, they can be input into the simulation software to predict the performance of structures such as solid motors in actual use or testing.

[0095] The Gruneisen equation of state is a physical model that describes the behavior of solid materials under high pressure. It is different from the Jhonson-Cook model and is mainly used to calculate the pressure-volume relationship of materials when they are subjected to shock or blast waves. The Gruneisen equation is often used for dynamic response analysis, such as the response of materials in explosions, impacts, or high-pressure experiments.

[0096] The basic form of the Gruneisen equation of state is:

[0097] Where p is the pressure of the material under compression. p0 is the reference pressure of the material at a reference volume V0, usually taken as zero (i.e. the initial pressure). V is the current volume of the material. V0 is the reference volume of the material (usually the initial volume). γ is the Gruneisen gamma parameter, which is a dimensionless constant that describes the relationship between the change in volume of a material and the change in its pressure.

[0098] In practical applications, the Gruneisen equation of state can be combined with other models (such as constitutive models, damage models, etc.) to provide a more comprehensive description of material response. It is very useful in calculating the compression, expansion and fracture behavior of materials under shock waves, especially in engineering and physics problems involving high pressure and dynamic loading conditions.

[0099] For example, the JC constitutive model parameters of the shell and fragment materials and the Gruneisen equation parameters can be found in Tables 2 and 3, as follows:

[0100] Table 2 JC constitutive model parameters of shell and fragment materials

[0101]

[0102] Table 3 Gruneisen equation parameters for shell and fragment materials

[0103] Material ρ <![CDATA[V0]]> C <![CDATA[E0]]> a <![CDATA[γ0]]> <![CDATA[S1]]> <![CDATA[S2]]> <![CDATA[S3]]> 30CrMnSiA 7.85 1.000 0.1739 0.000 0.90 1.930 1.490 0.000 0.000 Tungsten Alloy 17.70 1.000 0.3850 0.000 0.00 1.58 1.440 0.000 0.00 45 steel 7.80 1.000 0.4569 0.000 0.43 1.670 1.490 0.000 0.000 2024 Aluminum 2.78 1.000 0.5328 0.000 0.48 2.000 1.338 0.000 0.000

[0104] 103. In response to a parameter setting operation for a fragment, set motion parameters of the fragment.

[0105] The motion parameters of the fragment are a set of key variables that define the dynamic behavior of the fragment in the simulation environment. The specific motion parameters of the fragment can include: speed, direction, position, angular velocity, rotation, angle of attack, and mass, etc. The speed is the linear velocity of the fragment when it hits the engine, which is usually one of the most important motion parameters. It directly affects the energy transferred to the engine at the time of impact; the direction can be any angle relative to the engine, such as vertical, horizontal or inclined; the position is the initial position of the fragment, which determines the starting point of its movement; if the fragment rotates in flight, the angular velocity describes the speed of its rotation and the direction of the rotation axis; the angle of attack is the angle between the direction of the fragment's movement and the normal of the engine surface, which affects the dynamic response at the time of impact.

[0106] For example, specifically, determine the key motion parameters in the simulation, including speed, direction, position, angular velocity, mass, shape, etc. Then, set the impact speed of the fragments, which is based on experimental data, theoretical calculations, or the requirements of actual application scenarios. Next, define the direction of the fragment impact, including the impact angle with the target (such as vertical or oblique impact) and any related rotation or attack angle, and set the initial position of the fragment in the simulation space, usually referring to the starting point before the impact. If the fragment rotates in flight, it is necessary to set the rotation speed and rotation axis, which affect the impact effect and stability. Optionally, in some embodiments of the present application, the mass of the fragment and the shape and size of the fragment can also be set. The mass of the fragment is used to calculate the necessary parameters of kinetic energy and impact momentum; the shape and size of the fragment affect the aerodynamic characteristics, impact area, and energy transfer efficiency.

[0107] For example, when simulating a defense system test, the motion parameters of the fragments may be set as follows:

[0108] Initial speed: 1200 m / s

[0109] Impact angle: 90 degrees (vertical impact)

[0110] Initial position: 10 meters from the engine

[0111] Rotation speed: 0 (no rotation)

[0112] Mass: 5 kg

[0113] Shape: Spherical

[0114] Material: High-strength steel

[0115] By setting such parameters, the impact effect of fragments on solid motors can be accurately simulated and possible damage can be predicted, which is crucial for evaluating and improving the impact resistance and safety of solid motors.

[0116] For example, take the example of cube fragments hitting a solid rocket engine. Figure 3 As shown in the figure, the simulated process cloud diagram of the cubic fragments hitting the solid motor with a shell thickness of 5mm at v = 1120m / s. It can be seen from the figure that at t = 3μs, the shock wave pressure generated by the impact of the cubic fragments is incident on the propellant; at t = 6μs, some particles of the solid propellant begin to detonate; at t = 13μs, the shell is pushed up due to the detonation of the solid propellant; at t = 30μs, the solid propellant reaches the CJ detonation state.

[0117] It should be noted that the CJ detonation state, the full name of which is the Chapman-Jouguet detonation state, is a theoretical model that describes the detonation phenomenon that occurs when solid propellants or explosives are impacted or ignited. The Chapman-Jouguet model is based on the theory of one-dimensional reaction waves and is used to analyze and predict the propagation characteristics of detonation waves in solid propellants. The CJ detonation state is used to describe the detonation reaction of high-energy solid propellants after being impacted by fragments. For example, during the simulation, when cubic fragments impact the solid engine, the propellant reaches the CJ detonation state under certain conditions, at which time the pressure reaches a peak value, indicating that the detonation reaction has occurred. Through simulation, researchers can analyze the influence of different factors (such as shell thickness, fragment material and shape, etc.) on the impact detonation characteristics of the engine.

[0118] 104. Simulate the impact detonation characteristics of the solid motor according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments.

[0119] The place where the chemical reaction occurs in the solid motor is generally the charge area of ​​the solid motor. Therefore, it is necessary to determine the charge area in the first geometric model. For the charge area, a fluid model needs to be determined to describe the physical and chemical behavior of the propellant. This model may include the burning rate, energy release, gas generation and other characteristics of the propellant. In addition, it is also necessary to determine the area of ​​interaction between the first geometric model and the second geometric model in order to subsequently simulate the impact detonation characteristics of the solid motor, that is, optionally, in some embodiments of the present application, the step of "simulating the impact detonation characteristics of the solid motor according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments" may specifically include:

[0120] determining a charge region in a first geometric model;

[0121] Determine the fluid model corresponding to the charge area;

[0122] Setting a coupling interface between the first geometric model and the second geometric model;

[0123] The impact detonation characteristics of the solid motor are simulated according to the fluid model, the coupling interface of the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments.

[0124] For example, in the first geometric model of the solid motor, the charge area is defined as a cylindrical volume with a diameter of 1 meter and a length of 2 meters, which is the part filled with propellant. For the charge area, the JWL model is selected as the fluid model to describe the combustion characteristics of the propellant. This model can predict the combustion behavior of the propellant based on pressure, temperature and time. The JWL model (Jones-Wilkins-Lee model) is a mathematical model used to describe the detonation reaction of solid propellants or explosives after impact or ignition. This model is widely used in the study of solid motors, explosives and detonation physics, especially in situations where it is necessary to predict and analyze the propagation characteristics of detonation waves. Furthermore, the coupling interface is set on the inner surface of the motor casing, assuming that the casing thickness is 5 mm, which is the key area for the interaction between the first geometric model and the second geometric model.

[0125] The simulation needs to integrate the following parameters:

[0126] Fluid model: Parameters of the JWL model, such as the burning rate parameters.

[0127] First geometric model: the specific geometry and dimensions of the engine.

[0128] The second geometric model: a spherical fragment with a diameter of 0.1 meters and a mass of 10 kilograms.

[0129] First material model: Mechanical properties of the engine casing material, such as elastic modulus and yield strength.

[0130] Second material model: density and mechanical properties of the fragment material, assuming that the fragment is made of high-strength steel.

[0131] Motion parameters of fragments: Fragments hit the engine at a speed of 2000 m / s.

[0132] Simulating the impact detonation characteristics of solid rocket motors:

[0133] Finally, the process of fragments hitting the engine is simulated. At the moment of impact, a high-pressure shock wave is generated, for example, the wave is reflected and propagated inside the engine, and finally affects the charge area.

[0134] The simulation results show that it may be necessary to increase the thickness of the engine casing or use higher-strength materials to improve the engine's impact resistance.

[0135] It should be noted that the initial state of the charge area needs to be set during the simulation, and the shape and size of the fragments are adjusted according to different simulation scenarios. That is, optionally, in some embodiments of the present application, the step of "simulating the impact detonation characteristics of the solid motor according to the fluid model, the coupling interface of the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments" may specifically include:

[0136] Set the initial state of the charge area;

[0137] adjusting the shape of the second geometric model;

[0138] Based on the fluid model, different shapes of the second geometric model, the coupling interface between the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments, the impact detonation characteristics of the solid motor are simulated.

[0139] The charge region, where the solid propellant is located, needs to have its initial state set. This includes the initial density, initial temperature, initial pressure, and any other relevant initial conditions of the propellant. The second geometry model represents the fragments, and its shape and size may need to be adjusted according to different simulation scenarios. For example, the fragments can be spherical, cylindrical, or other shapes, each of which has a different impact on the impact effect. Choose an appropriate fluid model to describe the combustion behavior of the propellant in the charge region. As mentioned earlier, the JWL model is one of the commonly used fluid models in this type of application. The coupling interface between the first geometry model (solid motor) and the second geometry model (fragment) needs to be clearly set. This interface is the key area where the two interact and is crucial to the accuracy of the simulation. The first material model describes the material properties of the solid motor, such as the material properties of its shell. The second material model describes the material properties of the fragments, which affect the behavior of the fragments during the impact process. Set the motion parameters of the fragments, including their impact velocity, angle, mass, etc. These parameters define the dynamic behavior of the fragments in the simulation environment. Using all the above information, perform simulation calculations. The simulation software will simulate the process of fragments impacting the solid motor, analyze the propagation of the shock wave inside the motor, the response of the charge area, and possible detonation phenomena. The simulation results will provide important information about the behavior of the solid motor when impacted by fragments. The analysis may include the ignition of the propellant, the formation of the detonation wave, the damage to the motor structure, etc. Optionally, in some embodiments of the present application, the engine design may need to be optimized based on the simulation results, such as enhancing the protection of the charge area or improving the material and structure of the engine casing to improve its impact resistance.

[0140] Optionally, in some embodiments of the present application, the step of “simulating the impact detonation characteristics of the solid motor based on the fluid model, different shapes of the second geometric model, the coupling interface of the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments” may specifically include:

[0141] Based on the fluid model, different shapes of the second geometric model, the coupling interface between the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments, the fragment penetration information of the fragments impacting the solid motor and the deformation information of the motor casing are simulated;

[0142] According to the fragment penetration information and deformation information, the impact detonation characteristics of the solid motor are simulated.

[0143] During the simulation process, it is necessary to determine the fluid model corresponding to the charge area, which may involve the gas dynamics and chemical reactions inside the combustion chamber.

[0144] Specifically, the penetration information of the fragments impacting the solid motor and the deformation of the motor casing can be simulated by using the geometric model, coupling interface, material model and fragment motion parameters, wherein the geometric model includes the first geometric model of the solid motor and the second geometric model of the fragments. These models need to accurately reflect their respective shapes and sizes. Coupling interface: Determine the coupling interface between the first geometric model (solid motor) and the second geometric model (fragment), which is the boundary of the interaction between the two models in the simulation. Material model: Determine the first material model and the second material model for the solid motor and the fragment respectively, and these models need to include the physical and chemical properties of the material, such as density, elastic modulus, yield strength, etc. Fragment motion parameters: Set the motion parameters of the fragments, such as speed, direction, mass, etc. These parameters determine the dynamic characteristics of the fragments when they impact the engine. Based on the above models and parameters, simulate the penetration information of the fragments impacting the solid motor and the deformation information of the motor casing. This may involve complex contact and damage models to accurately predict the physical response after the impact. The impact detonation characteristics of the solid motor are further simulated using the fragment penetration information and the deformation information of the motor casing. This includes evaluating the response of the engine after being impacted, such as the ignition, combustion and possible explosion of the propellant, that is, optionally, in some embodiments of the present application, the step of "simulating the impact detonation characteristics of the solid engine according to the fragment penetration information and the deformation information" may specifically include:

[0145] Determine the impact detonation threshold of the solid motor based on the fragment penetration information and deformation information;

[0146] Identifying deformation information to obtain a damage area and a crack propagation path of the fragment after impacting the solid motor;

[0147] The shock detonation characteristics of solid rocket motors are simulated based on shock detonation threshold, damage area and crack propagation path.

[0148] Specifically, the critical conditions or thresholds for impact initiation of the solid motor are determined using information on fragment penetration of the engine casing and deformation data of the casing. Then, the deformation of the engine casing after being impacted by the fragments is analyzed, and the damaged area caused by the fragment impact is determined, that is, the area where the engine casing and internal structure are damaged. At the same time, the crack propagation path is tracked to understand how the crack spreads from the starting point to other areas. Finally, the response of the solid motor in an actual impact event is simulated based on the information on the impact initiation threshold, the damaged area, and the crack propagation path, so as to evaluate the possible combustion, explosion, and other initiation characteristics of the engine after the impact.

[0149] In addition, a 30CrMnSiA steel material model with a thickness of 2 mm to 8 mm can be established, with an increase of 1 mm each time, and a total of 7 thicknesses can be calculated to study the effect of shell thickness on the impact detonation velocity threshold. The fragments are cubic steel fragments (12.7 mm × 12.7 mm × 12.7 mm). Some simulation results are shown in Figure 2. Figure 4 As shown, under the critical detonation speed, it can be seen that the explosion diffusion areas of different shell thicknesses at the same time are different. If the shell thickness increases, the shock wave front will lag behind relatively.

[0150] like Figure 5 As shown in the figure, with the increase of shell thickness, the critical detonation speed shows an approximately linear growth trend. When the shell thickness increases from 2mm to 5mm, the increase of the speed threshold is relatively gentle; when the thickness increases from 5mm to 8mm, the growth rate of the speed threshold is slightly faster, as shown in the figure. Figure 5 Further analysis revealed that the impact detonation velocity (v c ) and the shell thickness (d) is: c =100d+632. The thicker the shell, the higher the detonation speed and the higher the safety of the high-energy solid rocket engine.

[0151] In addition, the impact values ​​of fragments made of different materials are also different. 45 steel, 2024 aluminum, and tungsten alloy fragments are used to simulate the impact value of engine fragments. The calculation results of the detonation velocity under different shell thicknesses are as follows: Figure 6 shown.

[0152] The detonation speed of the three materials is as follows: tungsten alloy fragments (v c =165d+171)>Steel fragments (v c =100d+632)>Aluminum fragments (v c=55d+1261), it can be seen that the higher the material density, the lower the critical detonation speed, and the more dangerous the high-energy solid engine is.

[0153] It should be noted that in the impact detonation simulation of solid rocket motors, the "fragment aspect ratio" is an important parameter, which affects the dynamic behavior and energy transfer efficiency of the fragments when they impact the engine. The aspect ratio is defined as the ratio of the length of the fragment to its width (or diameter).

[0154] Based on the standard cubic fragment, there are two modes of aspect ratio variation:

[0155] (1) The impact area is constant, and the aspect ratio is changed by increasing the fragment height;

[0156] (2) The mass of the fragments is constant, and the aspect ratio is changed by changing the height of the fragments.

[0157] The influence of the aspect ratio of fragments on the simulated engine impact detonation will be analyzed below based on the above two modes.

[0158] (1) Constant impact area

[0159] like Figure 7 As shown in Table 4, Figure 7 This is a diagram showing the result of simulating the engine being detonated by fragments of equal cross-sectional area but different aspect ratios.

[0160] Table 4 Simulated engine detonation velocity due to impact of fragments with equal cross-sectional area and different aspect ratios

[0161]

[0162] When the aspect ratio is in the range of 0.1-0.25, the detonation speed shows a strong correlation with the aspect ratio. The larger the aspect ratio, the easier it is to detonate. When the aspect ratio exceeds 0.25, the detonation speed no longer increases. This is because the fragments are not rigid bodies. When the aspect ratio exceeds 0.25, the deformation of the fragments will first absorb part of the energy. This results in the incident shock wave intensity of the simulated engine not being significantly increased, and the detonation speed has no obvious change.

[0163] (2) Constant fragment mass

[0164] Without changing the mass of the fragments, the influence of the fragments on the impact detonation is explored by adjusting the aspect ratio. Figure 8 As shown in the figure, with the increase of aspect ratio, the detonation speed of the fragments hitting the engine shows a nonlinear growth trend. For fragments of equal mass but different aspect ratios, the relationship between aspect ratio (HD) and detonation speed is approximately: c =605+587(HD)-85(H / D) 2That is, under the condition of equal mass, the closer the shape of the fragment is to a cube, the lower the critical detonation velocity is, and the more dangerous it is for a high-energy solid motor to be impacted by such fragments.

[0165] All the above working conditions are based on the assumption that the contact between the fragments and the high-energy solid motor is surface contact, and the velocity direction is perpendicular to the surface of the solid motor casing. However, in reality, there is often an angle between the fragments and the motor, and the velocity direction is also different from the angle direction. Based on this, this section conducts numerical calculations of simulated engine impact detonation under different fragment-motor angles and different velocity directions, aiming to obtain the influence of the fragment angle and velocity direction on the impact detonation of the high-energy solid motor. Spherical fragments do not have an angle with the engine, so this section only calculates cylindrical fragments and cubic fragments.

[0166] The aforementioned working conditions are all based on the fact that the contact between the fragments and the high-energy solid motor is surface contact, and the velocity direction is perpendicular to the surface of the solid motor casing. However, in actual situations, there is often an angle between the fragments and the motor, and the velocity direction is also different from the angle direction. Accordingly, in some embodiments of the present application, numerical calculations of simulated engine impact detonation under different fragment-motor angles and different velocity directions are performed to obtain the influence of the fragment angle and velocity direction on the impact detonation of the high-energy solid motor. Spherical fragments do not have an angle with the engine.

[0167] (1) Cylindrical fragments

[0168] A new parameter θ is introduced to represent the angle between the central axis of the cylindrical fragment and the impact plane, such as Figure 8 As shown in the figure. Based on the change of angle θ, the posture of the cylindrical fragment during impact will be horizontal, vertical or oblique. In order to further study the influence of this parameter on the impact effect, two different working conditions were designed.

[0169] Normal impact: Although the fragments are tilted at a certain angle, the direction of their movement speed remains perpendicular to the surface of the engine casing.

[0170] Oblique impact: The velocity direction of the fragment is consistent with its own central axis.

[0171] (2) Cube fragments

[0172] Numerical calculations are performed on three forms of surface impact, edge impact and vertex impact, such as Fig. 9 As shown. Under the point impact condition, α = 45° remains unchanged, and the law of engine impact detonation is simulated by changing the angle of β.

[0173] The above completes the impact detonation simulation process of the solid rocket motor of this application.

[0174] As described above, the present application provides a method for simulating the impact detonation of a solid engine, including: establishing a first geometric model corresponding to the solid engine and a second geometric model corresponding to the fragments, and meshing the first geometric model and the second geometric model respectively; determining a first material model corresponding to the solid engine and a second material model corresponding to the fragments; setting the motion parameters of the fragments in response to the parameter setting operation for the fragments; simulating the impact detonation characteristics of the solid engine according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments. In the impact detonation simulation scheme for a solid engine provided in the present application, after establishing the first geometric model and the second geometric model, the first geometric model and the second geometric model are meshed respectively to facilitate the subsequent capture of the impact process. In addition, the motion parameters of the fragments can be set according to different verification requirements, so that the accuracy and practicality of the impact detonation simulation results can be ensured.

[0175] Accordingly, see Fig.10 The embodiment of the present application provides a simulation device for impact detonation of a solid rocket engine (hereinafter referred to as a simulation device). The prompt device includes an establishment module 201, a determination module 202, a setting module 203 and a simulation module 204, which are as follows:

[0176] Establishing module 201, used to establish a first geometric model corresponding to the solid motor and a second geometric model corresponding to the fragments, and to perform mesh division on the first geometric model and the second geometric model respectively;

[0177] A determination module 202, for determining a first material model corresponding to the solid motor and a second material model corresponding to the fragment;

[0178] The setting module 203 is used to set the motion parameters of the fragments in response to the parameter setting operation for the fragments.

[0179] The simulation module 204 is used to simulate the impact detonation characteristics of the solid motor according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments.

[0180] As described above, the present application provides a shock detonation simulation device for a solid engine, wherein the establishment module 201 establishes a first geometric model corresponding to the solid engine and a second geometric model corresponding to the fragments, and meshes the first geometric model and the second geometric model respectively; the determination module 202 determines the first material model corresponding to the solid engine and the second material model corresponding to the fragments; the setting module 203 sets the motion parameters of the fragments in response to the parameter setting operation for the fragments; the simulation module 204 simulates the shock detonation characteristics of the solid engine according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments. In the shock detonation simulation scheme for a solid engine provided in the present application, after the first geometric model and the second geometric model are established, the first geometric model and the second geometric model are meshed respectively to facilitate the subsequent capture of the impact process. In addition, the motion parameters of the fragments can be set according to different verification requirements, so the accuracy and practicality of the shock detonation simulation results can be ensured.

[0181] In addition, the present application also provides a computer device, such as Fig.11 , which shows a schematic diagram of the structure of the computer device involved in the present application. Specifically, the computer device may include one or more processing core processors 301, one or more computer-readable storage media memories 302, a power supply 303, an input unit 304 and other components. Those skilled in the art can understand that Fig.11 The computer device structure shown in the figure does not constitute a limitation on the computer device, and may include more or fewer components than shown in the figure, or combine certain components, or arrange the components differently. Among them:

[0182] The processor 301 is the control center of the computer device. It uses various interfaces and lines to connect various parts of the entire computer device. By running or executing software programs and / or modules stored in the memory 302 and calling data stored in the memory 302, it executes various functions of the computer device and processes data, thereby monitoring the computer device as a whole. Optionally, the processor 301 may include one or more processing cores; preferably, the processor 301 may integrate an application processor and a modem processor, wherein the application processor mainly processes the operating system, user interface, and application programs, and the modem processor mainly processes wireless communications. It is understandable that the above-mentioned modem processor may not be integrated into the processor 301.

[0183] The memory 302 can be used to store software programs and modules. The processor 301 executes various functional applications and data processing by running the software programs and modules stored in the memory 302. The memory 302 may mainly include a program storage area and a data storage area, wherein the program storage area may store an operating system, an application required for at least one function (such as a sound playback function, an image playback function, etc.), etc.; the data storage area may store data created according to the use of the computer device, etc. In addition, the memory 302 may include a high-speed random access memory, and may also include a non-volatile memory, such as at least one disk storage device, a flash memory device, or other volatile solid-state storage devices. Accordingly, the memory 302 may also include a memory controller to provide the processor 301 with access to the memory 302.

[0184] The computer device also includes a power supply 303 for supplying power to various components. Preferably, the power supply 303 can be logically connected to the processor 301 through a power management system, so as to manage charging, discharging, and power consumption through the power management system. The power supply 303 can also include any components such as one or more DC or AC power supplies, recharging systems, power failure detection circuits, power converters or inverters, and power status indicators.

[0185] The computer device may further include an input unit 304, which may be used to receive input digital or character information and generate keyboard, mouse, joystick, optical or trackball signal input related to user settings and function control.

[0186] Although not shown, the computer device may further include a display unit, etc., which will not be described in detail herein. Specifically in this embodiment, the processor 301 in the computer device will load the executable files corresponding to the processes of one or more application programs into the memory 302 according to the following instructions, and the processor 301 will run the application programs stored in the memory 302, thereby realizing various functions, as follows:

[0187] A first geometric model corresponding to the solid engine and a second geometric model corresponding to the fragments are established, and the first geometric model and the second geometric model are meshed respectively; a first material model corresponding to the solid engine and a second material model corresponding to the fragments are determined; in response to a parameter setting operation for the fragments, the motion parameters of the fragments are set; according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments, the impact detonation characteristics of the solid engine are simulated.

[0188] The specific implementation of the above operations can be found in the previous embodiments, which will not be described in detail here.

[0189] The embodiment of the present application establishes a first geometric model corresponding to the solid engine and a second geometric model corresponding to the fragments, and meshes the first geometric model and the second geometric model respectively; determines a first material model corresponding to the solid engine and a second material model corresponding to the fragments; sets the motion parameters of the fragments in response to a parameter setting operation for the fragments; and simulates the impact detonation characteristics of the solid engine according to the first geometric model, the second geometric model, the first material model, the second material model, and the motion parameters of the fragments. In the impact detonation simulation scheme of the solid engine provided in the present application, after establishing the first geometric model and the second geometric model, meshes are respectively performed on the first geometric model and the second geometric model to facilitate the subsequent capture of the impact process. In addition, the motion parameters of the fragments can be set according to different verification requirements, thereby ensuring the accuracy and practicality of the impact detonation simulation results.

[0190] A person of ordinary skill in the art will appreciate that all or part of the steps in the various methods of the above embodiments may be completed by instructions, or by controlling related hardware through instructions. The instructions may be stored in a computer-readable storage medium and loaded and executed by a processor.

[0191] To this end, the present application provides a storage medium in which a plurality of instructions are stored, and the instructions can be loaded by a processor to execute the steps in any of the impact detonation simulation methods for solid motors provided in the present application. For example, the instructions can execute the following steps:

[0192] A first geometric model corresponding to the solid engine and a second geometric model corresponding to the fragments are established, and the first geometric model and the second geometric model are meshed respectively; a first material model corresponding to the solid engine and a second material model corresponding to the fragments are determined; in response to a parameter setting operation for the fragments, the motion parameters of the fragments are set; according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments, the impact detonation characteristics of the solid engine are simulated.

[0193] The specific implementation of the above operations can be found in the previous embodiments, which will not be described in detail here.

[0194] The storage medium may include: a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk, etc.

[0195] Since the instructions stored in the storage medium can execute the steps in any of the impact detonation simulation methods for solid engines provided in the present application, the beneficial effects that can be achieved by any of the impact detonation simulation methods for solid engines provided in the present application can be achieved. Please refer to the previous embodiments for details and will not be repeated here.

[0196] According to one aspect of the present application, a computer program product or a computer program is provided, the computer program product or the computer program comprising computer instructions, the computer instructions being stored in a computer-readable storage medium. A processor of a computer device reads the computer instructions from the computer-readable storage medium, and the processor executes the computer instructions, so that the computer device executes the methods provided in the above-mentioned various optional implementations.

[0197] The above is a detailed introduction to the impact detonation simulation method, device, medium and equipment of a solid engine provided by the present application. Specific examples are used in this article to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method of the present application and its core idea; at the same time, for technical personnel in this field, according to the idea of ​​the present application, there will be changes in the specific implementation method and application scope. In summary, the content of this specification should not be understood as a limitation on the present application.

Claims

1. A method for simulating impact detonation of a solid rocket engine, characterized in that: include: Establishing a first geometric model corresponding to the solid motor and a second geometric model corresponding to the fragments, and meshing the first geometric model and the second geometric model respectively; Determining a first material model corresponding to the solid motor and a second material model corresponding to the fragment; In response to a parameter setting operation for the fragment, setting a motion parameter of the fragment; The impact detonation characteristics of the solid motor are simulated according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments.

2. The impact detonation simulation method of a solid rocket motor according to claim 1, characterized in that: The step of establishing a first geometric model corresponding to the solid motor and a second geometric model corresponding to the fragments, and meshing the first geometric model and the second geometric model respectively, includes: Get the basic model corresponding to the solid engine; Determining design parameters of the solid motor; Based on the basic model and design parameters, a first geometric model corresponding to the solid motor is established; Creating a basic shape of a fragment, and establishing a second geometric model corresponding to the fragment according to fragment parameters preset in the basic shape; The first geometric model and the second geometric model are meshed according to a common characteristic length between the first geometric model and the second geometric model.

3. The impact detonation simulation method of a solid rocket engine according to claim 2, characterized in that: The meshing of the first geometric model and the second geometric model according to the common characteristic length between the first geometric model and the second geometric model comprises: determining an impact location between the first geometric model and the second geometric model; Determining a common characteristic length between the first geometric model and the second geometric model according to the impact position, and determining a global grid size corresponding to the common characteristic length; The first geometric model and the second geometric model are meshed based on the global mesh size.

4. The impact detonation simulation method of a solid rocket motor according to claim 1, characterized in that: The method of simulating the impact detonation characteristics of the solid motor according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments includes: determining a charge area in the first geometric model; Determining a fluid model corresponding to the charge area; Setting a coupling interface between the first geometric model and the second geometric model; The impact detonation characteristics of the solid motor are simulated according to the fluid model, the coupling interface of the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments.

5. The impact detonation simulation method of a solid rocket motor according to claim 4, characterized in that: The method of simulating the impact detonation characteristics of the solid motor according to the fluid model, the coupling interface between the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments includes: Set the initial state of the charge area; adjusting the shape of the second geometric model; Based on the fluid model, different shapes of the second geometric model, the coupling interface between the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments, the impact detonation characteristics of the solid motor are simulated.

6. The impact detonation simulation method of a solid rocket motor according to claim 5, characterized in that: The method of simulating the impact detonation characteristics of the solid motor based on the fluid model, different shapes of the second geometric model, the coupling interface between the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments includes: Based on the fluid model, different shapes of the second geometric model, the coupling interface between the first geometric model and the second geometric model, the first material model, the second material model and the motion parameters of the fragments, simulate the fragment penetration information of the fragments impacting the solid motor and the deformation information of the motor casing; The impact detonation characteristics of the solid motor are simulated according to the fragment penetration information and the deformation information.

7. The impact detonation simulation method of a solid rocket motor according to claim 6, characterized in that: The simulating the impact detonation characteristics of the solid motor according to the fragment penetration information and the deformation information includes: Determining the impact detonation threshold of the solid motor according to the fragment penetration information and the deformation information; Identifying the deformation information to obtain a damage area and a crack propagation path of the fragment after impacting the solid motor; The shock detonation characteristics of the solid motor are simulated according to the shock detonation threshold, the damage area and the crack propagation path.

8. A solid rocket engine impact detonation simulation device, characterized in that: include: An establishment module is used to establish a first geometric model corresponding to the solid motor and a second geometric model corresponding to the fragments, and to mesh the first geometric model and the second geometric model respectively; A determination module, used to determine a first material model corresponding to the solid motor and a second material model corresponding to the fragment; A setting module, configured to set the motion parameters of the fragment in response to a parameter setting operation for the fragment; A simulation module is used to simulate the impact detonation characteristics of the solid motor according to the first geometric model, the second geometric model, the first material model, the second material model and the motion parameters of the fragments.

9. A computer-readable storage medium storing a computer program, wherein when the computer program is executed by a processor, the processor executes the steps of the impact detonation simulation method for a solid motor according to any one of claims 1 to 7.

10. A computer device comprising a memory and a processor, wherein the memory stores a computer program, and when the computer program is executed by the processor, the processor executes the steps of the impact detonation simulation method of a solid rocket engine as claimed in any one of claims 1 to 7.

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