Propellant mesoscopic mechanics performance optimization method

Abstract

The application discloses a propellant mesoscopic mechanics performance optimization method, and belongs to the technical field of aerospace mechanics. The method comprises the following steps: constructing a three-dimensional mesoscopic polyhedral grid model of a propellant based on the real mesoscopic morphology of the propellant; carrying out numerical simulation of the three-dimensional mesoscopic polyhedral grid model of the propellant based on virtual elements and phase fields, and obtaining the overall stiffness matrix of the propellant; carrying out constant-speed tensile simulation of the propellant, and obtaining the simulation force-displacement curve of the propellant; inversely calculating the performance related parameters of the propellant based on the simulation force-displacement curve and the overall stiffness matrix of the propellant; and optimizing the formula of the propellant based on the performance related parameters of the propellant, so as to realize the mesoscopic mechanics performance optimization of the propellant. The performance related parameters of the propellant comprise a matrix damage factor, an interfacial fracture strength of the matrix and particles, and an interfacial critical strain energy release rate of the matrix and particles. The method can realize the mesoscopic mechanics performance optimization of the propellant.

Description

Technical Field

[0001] This invention belongs to the field of aerospace mechanics technology, specifically relating to a method for optimizing the micromechanical properties of propellants. Background Technology

[0002] Solid propellants are typical three-dimensional particle-reinforced materials. Under load, matrix damage, debonding at the matrix-particle interface, and particle breakage can severely affect the mechanical properties of the propellant.

[0003] Traditional finite element simulation methods struggle to achieve effective simulation results when dealing with three types of damage in propellants: matrix damage, debonding at the matrix-particle interface, and particle breakage. Summary of the Invention

[0004] The purpose of this invention is to provide a method for optimizing the micromechanical properties of propellants, which can effectively simulate propellant matrix damage, matrix-particle interface debonding, and particle breakage, thereby achieving optimization of the micromechanical properties of propellants.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] In a first aspect, the present invention provides a method for optimizing the micromechanical properties of a propellant, comprising:

[0007] Based on the actual microstructure of the propellant, a three-dimensional microstructure polyhedral mesh model of the propellant is constructed.

[0008] Numerical simulation of a three-dimensional mesoscopic polyhedral mesh model of propellant based on virtual elements and phase field was carried out to obtain the overall stiffness matrix of the propellant;

[0009] Conduct constant-velocity tensile simulations of the propellant to obtain the simulated force-displacement curves of the propellant;

[0010] Based on the simulated force-displacement curves and overall stiffness matrix of the propellant, the performance-related parameters of the propellant are inverted;

[0011] Based on the performance-related parameters of the propellant, the propellant formulation is optimized to achieve the optimization of the propellant's micromechanical properties;

[0012] Among them, the performance-related parameters of the propellant include the matrix damage factor, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface.

[0013] In conjunction with the first aspect, further, based on the actual microstructure of the propellant, a three-dimensional microscopic polyhedral mesh model of the propellant is constructed, including:

[0014] Based on the actual microstructure of the propellant, a three-dimensional microgeometric model of the propellant is constructed using dynamic methods;

[0015] A polyhedral mesh was generated for the three-dimensional mesoscopic geometric model of the propellant, and polyhedral cohesive elements were set at the interface between the matrix and the particles of the propellant to obtain a three-dimensional mesoscopic polyhedral mesh model of the propellant.

[0016] In conjunction with the first aspect, further numerical simulations of a three-dimensional mesoscopic polyhedral mesh model of the propellant based on virtual elements and phase fields are conducted to obtain the overall stiffness matrix of the propellant, including:

[0017] Numerical simulation of a three-dimensional mesoscopic polyhedral mesh model of propellant based on virtual elements was carried out using the virtual element method to obtain the displacement field stiffness matrix of the propellant.

[0018] The phase field is used to describe the damage of the propellant matrix, particles, and matrix-particle interface. Numerical simulation of the three-dimensional mesoscopic polyhedral mesh model of the propellant based on the phase field is carried out to obtain the phase field stiffness matrix of the propellant.

[0019] The overall stiffness matrix of the propellant is obtained from the displacement field stiffness matrix and the phase field stiffness matrix of the propellant.

[0020] In conjunction with the first aspect, the overall stiffness matrix of the propellant is further defined as follows:

[0021] ;

[0022] in, This represents the overall stiffness matrix of the propellant. This represents the displacement field stiffness matrix of the propellant. This represents the phase field stiffness matrix of the propellant.

[0023] In conjunction with the first aspect, further, based on the simulated force-displacement curves and overall stiffness matrix of the propellant, the performance-related parameters of the propellant can be inverted, including:

[0024] Based on the simulated force-displacement curve and overall stiffness matrix of the propellant, the performance-related parameters of the propellant are inverted using the particle swarm optimization algorithm, and combined with the minimum variance criterion, the simulated force-displacement curve of the propellant is controlled to be consistent with the actual force-displacement curve.

[0025] The actual force-displacement curve of the propellant was obtained by conducting constant-velocity tensile tests on the propellant.

[0026] In conjunction with the first aspect, further optimization of the propellant formulation based on propellant performance-related parameters includes:

[0027] The propellant is coarsely meshed, and based on the performance-related parameters of the propellant, the particle swarm optimization algorithm is used to optimize the propellant formulation under the coarse mesh, thereby obtaining the local optimum solution of the propellant formulation optimization.

[0028] The propellant is subjected to mesh refinement, and the formulation of the propellant is optimized under the condition of local optimum, based on the performance-related parameters of the propellant.

[0029] In conjunction with the first aspect, further, the coarse meshing of the propellant includes: dividing the individual particles of the propellant into individual units, and using the entire polyhedral unit to mesh the propellant matrix;

[0030] The process of refining the propellant mesh includes: based on the initial coarse mesh division of the propellant, further dividing the propellant into a polyhedral mesh.

[0031] In a second aspect, the present invention provides a propellant micromechanical property optimization system, comprising:

[0032] The model building module is used to construct a three-dimensional mesoscopic polyhedral mesh model of the propellant based on its true microscopic morphology.

[0033] The numerical simulation module is used to conduct numerical simulations of the three-dimensional mesoscopic polyhedral mesh model of the propellant based on virtual elements and phase fields, and to obtain the overall stiffness matrix of the propellant.

[0034] The constant-speed tensile simulation module is used to conduct constant-speed tensile simulations of propellants and obtain the simulated force-displacement curves of the propellants.

[0035] The inversion module is used to simulate force-displacement curves and overall stiffness matrix based on propellants, and to invert propellant performance-related parameters.

[0036] The optimization module is used to optimize the propellant formulation based on the propellant's performance-related parameters, thereby optimizing the propellant's micromechanical properties.

[0037] Among them, the performance-related parameters of the propellant include the matrix damage factor, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface.

[0038] Thirdly, the present invention provides a computer device, comprising:

[0039] Storage medium: used to store computer programs;

[0040] Processor: for executing computer programs to implement the method for optimizing the micromechanical properties of propellants as described in any of the first aspects.

[0041] Fourthly, the present invention provides a computer-readable storage medium having a computer program stored thereon, wherein the computer program, when executed by a processor, implements the method for optimizing the micromechanical properties of propellants as described in any of the first aspects.

[0042] Fifthly, the present invention provides a computer program product, including a computer program that, when executed by a processor, implements the method for optimizing the micromechanical properties of propellants as described in any of the first aspects.

[0043] Compared with the prior art, the beneficial effects of the present invention are:

[0044] The propellant micromechanical property optimization method provided by this invention obtains the overall stiffness matrix of the propellant by conducting numerical simulation of a three-dimensional microscopic polyhedral mesh model of the propellant based on virtual elements and phase field. Based on the simulated force-displacement curve and the overall stiffness matrix of the propellant, the matrix damage factor, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface are inverted, and then the propellant formulation is optimized. This method can address three types of damage in propellant: matrix damage, debonding of the matrix-particle interface, and particle breakage, thereby optimizing the micromechanical properties of the propellant. Attached Figure Description

[0045] Figure 1 This is a flowchart of the propellant micromechanical property optimization method provided in the embodiments of the present invention;

[0046] Figure 2 This is a schematic diagram of the three-dimensional real microstructure of the propellant provided in an embodiment of the present invention;

[0047] Figure 3 This is a schematic diagram of propellant polyhedral mesh division provided in an embodiment of the present invention;

[0048] Figure 4 This is a schematic diagram of a propellant polyhedral cohesive unit provided in an embodiment of the present invention; wherein, (a) represents a schematic diagram of the polyhedral cohesive unit before deformation, and (b) represents a schematic diagram of the polyhedral cohesive unit after deformation;

[0049] Figure 5 This is a schematic diagram of a propellant structure containing dispersed cracks provided in an embodiment of the present invention. Detailed Implementation

[0050] The technical solution of this application will be further described in detail below with reference to specific embodiments.

[0051] The embodiments of this application are described in detail below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this application, and should not be construed as limiting this application. Unless otherwise specified, the embodiments of this application and the technical features within them can be combined with each other.

[0052] This application provides a method for optimizing the micromechanical properties of propellants. This method can be applied to a terminal and can be executed by a propellant micromechanical property optimization system. The propellant micromechanical property optimization system can be implemented by software and / or hardware and can be integrated into the terminal, such as any tablet computer or computer device with communication functions.

[0053] Figure 1 This is a flowchart illustrating the method for optimizing the micromechanical properties of propellants provided in this embodiment. This flowchart only shows the logical sequence of the method in this embodiment; however, different methods may be used without conflict. Figure 1 Complete the steps shown or described in the order indicated.

[0054] like Figure 1 As shown, the method for optimizing the micromechanical properties of propellants provided in this embodiment includes:

[0055] Based on the actual microstructure of the propellant, a three-dimensional microstructure polyhedral mesh model of the propellant is constructed.

[0056] Numerical simulation of a three-dimensional mesoscopic polyhedral mesh model of propellant based on virtual elements and phase field was carried out to obtain the overall stiffness matrix of the propellant;

[0057] Conduct constant-velocity tensile simulations of the propellant to obtain the simulated force-displacement curves of the propellant;

[0058] Based on the simulated force-displacement curves and overall stiffness matrix of the propellant, the performance-related parameters of the propellant are inverted;

[0059] Based on the performance-related parameters of the propellant, the propellant formulation is optimized to achieve the optimization of the propellant's micromechanical properties.

[0060] In this embodiment, the performance-related parameters of the propellant include the matrix damage factor, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface.

[0061] The propellant micromechanical property optimization method provided in this embodiment obtains the overall stiffness matrix of the propellant by conducting numerical simulation of a three-dimensional microscopic polyhedral mesh model of the propellant based on virtual elements and phase field. Based on the simulated force-displacement curve and the overall stiffness matrix of the propellant, the matrix damage factor, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface are inverted. Then, the propellant formulation is optimized, which can cope with the three types of damage of the propellant matrix, debonding of the matrix-particle interface, and particle breakage to achieve the optimization of the propellant micromechanical properties.

[0062] In one possible embodiment, constructing a three-dimensional mesoscopic polyhedral mesh model of the propellant based on its actual microstructure includes:

[0063] Based on the actual microstructure of the propellant, a three-dimensional microgeometric model of the propellant is constructed using dynamic methods;

[0064] A polyhedral mesh was generated for the three-dimensional mesoscopic geometric model of the propellant, and polyhedral cohesive elements were set at the interface between the matrix and the particles of the propellant to obtain a three-dimensional mesoscopic polyhedral mesh model of the propellant.

[0065] Specifically, such as Figure 2 As shown, CT scanning of the propellant was performed to obtain its true microstructure. Based on this true microstructure, a three-dimensional microgeometric model of the propellant was constructed using dynamic methods. Figure 3 As shown, the three-dimensional mesoscopic geometric model of the propellant is meshed using polyhedral meshes, as follows: Figure 4 As shown, polyhedral cohesive elements are set at the interface between the propellant matrix and particles to obtain a three-dimensional mesoscopic polyhedral mesh model of the propellant. Figure 4 In the diagram, (a) shows a schematic diagram of the polyhedral cohesive element before deformation, and (b) shows a schematic diagram of the polyhedral cohesive element after deformation. Indicates the amount of deformation.

[0066] In one possible embodiment, numerical simulation of a three-dimensional mesoscopic polyhedral mesh model of the propellant based on virtual elements and phase field is performed to obtain the overall stiffness matrix of the propellant, including:

[0067] Numerical simulation of a three-dimensional mesoscopic polyhedral mesh model of propellant based on virtual elements was carried out using the virtual element method to obtain the displacement field stiffness matrix of the propellant.

[0068] The phase field is used to describe the damage of the propellant matrix, particles, and matrix-particle interface. Numerical simulation of the three-dimensional mesoscopic polyhedral mesh model of the propellant based on the phase field is carried out to obtain the phase field stiffness matrix of the propellant.

[0069] The overall stiffness matrix of the propellant is obtained from the displacement field stiffness matrix and the phase field stiffness matrix of the propellant.

[0070] Specifically, such as Figure 5 As shown, the region described by the phase field is , Figure 5 middle, Indicates the boundary subject to distributed force. Indicates the boundary subject to displacement. This indicates the area affected by dispersed cracks. The degree of propellant damage is represented by D, where D=0 indicates no propellant damage and D=1 indicates complete propellant failure.

[0071] In this embodiment, the overall stiffness matrix of the propellant is:

[0072] ;

[0073] in, This represents the overall stiffness matrix of the propellant. This represents the displacement field stiffness matrix of the propellant. This represents the phase field stiffness matrix of the propellant.

[0074] In one possible embodiment, the performance-related parameters of the propellant are inverted based on the simulated force-displacement curve and the overall stiffness matrix of the propellant. This includes: using a particle swarm optimization algorithm to invert the performance-related parameters of the propellant based on the simulated force-displacement curve and the overall stiffness matrix of the propellant, and combining the minimum variance criterion to control the simulated force-displacement curve of the propellant to be consistent with the actual force-displacement curve.

[0075] In this embodiment, the actual force-displacement curve of the propellant was obtained by conducting a constant-velocity tensile test on the propellant.

[0076] In one possible embodiment, propellant formulation optimization based on propellant performance-related parameters includes:

[0077] The propellant is coarsely meshed, and based on the performance-related parameters of the propellant, the particle swarm optimization algorithm is used to optimize the propellant formulation under the coarse mesh, thereby obtaining the local optimum solution of the propellant formulation optimization.

[0078] The propellant is subjected to mesh refinement, and the formulation of the propellant is optimized under the condition of local optimum, based on the performance-related parameters of the propellant.

[0079] Specifically, the coarse meshing of the propellant includes dividing the individual particles of the propellant into individual units and using the entire polyhedral unit to mesh the propellant matrix; the fine meshing of the propellant includes further meshing the propellant into polyhedral units based on the coarse meshing of the propellant.

[0080] This application provides a propellant micromechanical property optimization system, including:

[0081] The pre-training module is used to pre-train the drilling rig formation identification model using actual drilling rig construction label data, and obtain the pre-trained drilling rig formation identification model.

[0082] The secondary training module is used to perform secondary training on the pre-trained drilling rig formation identification model using drilling rig comparison label data, and obtain the trained drilling rig formation identification model.

[0083] The identification module is used to input the current construction data of the drilling process into the trained drilling rig formation identification model to identify the formation and obtain the current formation type during the drilling process.

[0084] Among them, the drilling rig formation identification model is constructed based on a long short-term memory network.

[0085] The propellant micromechanical property optimization system provided in this embodiment can execute the propellant micromechanical property optimization method provided in this application embodiment, and has the corresponding functional modules and beneficial effects of the method.

[0086] This application provides a computer device, including:

[0087] Storage medium used to store computer programs;

[0088] A processor is used to execute computer programs to implement the propellant micromechanical property optimization method provided in the embodiments of this application.

[0089] This application provides a computer-readable storage medium storing a computer program thereon. When the computer program is executed by a processor, it implements the propellant micromechanical property optimization method provided in this application.

[0090] This application provides a computer program product, including a computer program that, when executed by a processor, implements the propellant micromechanical property optimization method provided in this application.

[0091] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product embodied on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0092] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, as well as combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0093] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0094] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0095] The above are merely preferred embodiments of this application. It should be noted that, for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

Claims

1. A method for optimizing the micromechanical properties of propellants, characterized in that, include: Based on the actual microstructure of the propellant, a three-dimensional microstructure polyhedral mesh model of the propellant is constructed. Numerical simulation of a three-dimensional mesoscopic polyhedral mesh model of propellant based on virtual elements and phase field was carried out to obtain the overall stiffness matrix of the propellant; Conduct constant-velocity tensile simulations of the propellant to obtain the simulated force-displacement curves of the propellant; Based on the simulated force-displacement curves and overall stiffness matrix of the propellant, the performance-related parameters of the propellant are inverted; Based on the performance-related parameters of the propellant, the propellant formulation is optimized to achieve the optimization of the propellant's micromechanical properties; Among them, the performance-related parameters of the propellant include the matrix damage factor, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface. Numerical simulations of a three-dimensional mesoscopic polyhedral mesh model of the propellant based on virtual elements and phase fields were conducted to obtain the overall stiffness matrix of the propellant, including: Numerical simulation of a three-dimensional mesoscopic polyhedral mesh model of propellant based on virtual elements was carried out using the virtual element method to obtain the displacement field stiffness matrix of the propellant. The phase field is used to describe the damage of the propellant matrix, particles, and matrix-particle interface. Numerical simulation of the three-dimensional mesoscopic polyhedral mesh model of the propellant based on the phase field is carried out to obtain the phase field stiffness matrix of the propellant. The overall stiffness matrix of the propellant is obtained from the displacement field stiffness matrix and the phase field stiffness matrix of the propellant. The overall stiffness matrix of the propellant is: ； in, This represents the overall stiffness matrix of the propellant. This represents the displacement field stiffness matrix of the propellant. The phase field stiffness matrix represents the propellant. Propellant formulation optimization based on propellant performance parameters includes: The propellant is coarsely meshed, and based on the performance-related parameters of the propellant, the particle swarm optimization algorithm is used to optimize the propellant formulation under the coarse mesh, thereby obtaining the local optimum solution of the propellant formulation optimization. The propellant is subjected to mesh refinement, and the formulation of the propellant is optimized under the condition of local optimum, based on the performance-related parameters of the propellant. The process of coarse meshing of propellant includes dividing the individual particles of propellant into individual cells and meshing the propellant matrix using the entire polyhedral cell. The process of refining the propellant mesh includes: based on the initial coarse mesh division of the propellant, further dividing the propellant into a polyhedral mesh.

2. The method for optimizing the micromechanical properties of propellants according to claim 1, characterized in that, Based on the actual microstructure of the propellant, the construction of a three-dimensional microscopic polyhedral mesh model of the propellant includes: Based on the actual microstructure of the propellant, a three-dimensional microgeometric model of the propellant is constructed using dynamic methods; A polyhedral mesh was generated for the three-dimensional mesoscopic geometric model of the propellant, and polyhedral cohesive elements were set at the interface between the matrix and the particles of the propellant to obtain a three-dimensional mesoscopic polyhedral mesh model of the propellant.

3. The method for optimizing the micromechanical properties of propellants according to claim 1, characterized in that, Based on the simulated force-displacement curves and overall stiffness matrix of the propellant, the performance-related parameters of the propellant can be inverted, including: Based on the simulated force-displacement curve and overall stiffness matrix of the propellant, the performance-related parameters of the propellant are inverted using the particle swarm optimization algorithm, and combined with the minimum variance criterion, the simulated force-displacement curve of the propellant is controlled to be consistent with the actual force-displacement curve. The actual force-displacement curve of the propellant was obtained by conducting constant-velocity tensile tests on the propellant.

4. A propellant micromechanical property optimization system, characterized in that, include: The model building module is used to construct a three-dimensional mesoscopic polyhedral mesh model of the propellant based on its true microscopic morphology. The numerical simulation module is used to conduct numerical simulations of the three-dimensional mesoscopic polyhedral mesh model of the propellant based on virtual elements and phase fields, and to obtain the overall stiffness matrix of the propellant. The constant-speed tensile simulation module is used to conduct constant-speed tensile simulations of propellants and obtain the simulated force-displacement curves of the propellants. The inversion module is used to simulate force-displacement curves and overall stiffness matrix based on propellants, and to invert propellant performance-related parameters. The optimization module is used to optimize the propellant formulation based on the propellant's performance-related parameters, thereby optimizing the propellant's micromechanical properties. Among them, the performance-related parameters of the propellant include the matrix damage factor, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface. Numerical simulations of a three-dimensional mesoscopic polyhedral mesh model of the propellant based on virtual elements and phase fields were conducted to obtain the overall stiffness matrix of the propellant, including: Numerical simulation of a three-dimensional mesoscopic polyhedral mesh model of propellant based on virtual elements was carried out using the virtual element method to obtain the displacement field stiffness matrix of the propellant. The phase field is used to describe the damage of the propellant matrix, particles, and matrix-particle interface. Numerical simulation of the three-dimensional mesoscopic polyhedral mesh model of the propellant based on the phase field is carried out to obtain the phase field stiffness matrix of the propellant. The overall stiffness matrix of the propellant is obtained from the displacement field stiffness matrix and the phase field stiffness matrix of the propellant. The overall stiffness matrix of the propellant is: ； in, This represents the overall stiffness matrix of the propellant. This represents the displacement field stiffness matrix of the propellant. The phase field stiffness matrix represents the propellant. Propellant formulation optimization based on propellant performance parameters includes: The propellant is coarsely meshed, and based on the performance-related parameters of the propellant, the particle swarm optimization algorithm is used to optimize the propellant formulation under the coarse mesh, thereby obtaining the local optimum solution of the propellant formulation optimization. The propellant is subjected to mesh refinement, and the formulation of the propellant is optimized under the condition of local optimum, based on the performance-related parameters of the propellant. The process of coarse meshing of propellant includes dividing the individual particles of propellant into individual cells and meshing the propellant matrix using the entire polyhedral cell. The process of refining the propellant mesh includes: based on the initial coarse mesh division of the propellant, further dividing the propellant into a polyhedral mesh.

5. A computer device, comprising: Storage medium used to store computer programs; A processor for executing the computer program to implement the propellant micromechanical property optimization method according to any one of claims 1 to 3.

6. A computer-readable storage medium having a computer program stored thereon, wherein the computer program, when executed by a processor, implements the method for optimizing the micromechanical properties of a propellant according to any one of claims 1 to 3.

Images