Propellant mesomechanical property optimization method

Abstract

The invention discloses a propellant mesoscopic mechanical property optimization method, and belongs to the technical field of aerospace mechanics, and the method comprises the steps: building a propellant three-dimensional mesoscopic polyhedral mesh model based on the real mesoscopic morphology of a propellant; carrying out numerical simulation of the propellant three-dimensional mesoscopic polyhedral mesh model based on the virtual unit and the phase field to obtain an overall stiffness matrix of the propellant; constant-speed stretching simulation of the propellant is carried out, and a simulation force-displacement curve of the propellant is obtained; based on the simulation force-displacement curve and the overall stiffness matrix of the propellant, performance related parameters of the propellant are inverted; based on the performance related parameters of the propellant, formula optimization is performed on the propellant, and micro-mechanical performance optimization of the propellant is achieved; wherein the performance related parameters of the propellant comprise matrix damage factors of the propellant, matrix and particle interface breaking strength and matrix and particle interface critical strain energy release rate. According to the method, the micro-mechanical property optimization of the propellant can be realized.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace mechanics, and specifically relates to a method for optimizing the microscopic mechanical properties of a propellant. Background Art

[0002] Solid propellants are typical three-dimensional particle-reinforced materials. When loaded, propellant matrix damage, matrix-particle interface debonding, and particle breakage will seriously affect the mechanical properties of the propellant.

[0003] Traditional finite element simulation methods are difficult to obtain effective simulation results when dealing with the three types of propellant failure: matrix damage, debonding between the matrix and particle interface, and particle crushing. Summary of the invention

[0004] The purpose of the present invention is to provide a method for optimizing the microscopic mechanical properties of propellants, which can effectively simulate propellant matrix damage, matrix-particle interface debonding, and particle crushing, thereby optimizing the microscopic mechanical properties of propellants.

[0005] In order to achieve the above object, the present invention provides the following technical solutions: In a first aspect, the present invention provides a method for optimizing the microscopic mechanical properties of a propellant, comprising: Based on the real mesoscopic morphology of the propellant, a three-dimensional mesoscopic polyhedral mesh model of the propellant is constructed; Carry out numerical simulation of the three-dimensional mesoscopic polyhedral mesh model of the propellant based on virtual elements and phase field to obtain the overall stiffness matrix of the propellant; Carry out constant-speed stretching simulation of propellant to obtain the simulated force-displacement curve of propellant; Based on the simulated force-displacement curve and the 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 formula is optimized to achieve the optimization of the propellant's microscopic mechanical properties; Among them, the performance-related parameters of the propellant include the matrix damage factor of the propellant, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface.

[0006] In combination with the first aspect, further, based on the real microscopic morphology of the propellant, constructing a three-dimensional microscopic polyhedral mesh model of the propellant includes: Based on the real mesoscopic morphology of the propellant, a three-dimensional mesoscopic geometric model of the propellant is constructed using the dynamic method; The three-dimensional microscopic geometric model of the propellant is divided into polyhedral meshes, and polyhedral cohesion units are set at the interface between the matrix and particles of the propellant to obtain the three-dimensional microscopic polyhedral mesh model of the propellant.

[0007] Combined with the first aspect, further, a numerical simulation of the three-dimensional microscopic polyhedral mesh model of the propellant based on virtual units and phase fields is carried out to obtain the overall stiffness matrix of the propellant including: The virtual element method is used to carry out numerical simulation of the three-dimensional microscopic polyhedral mesh model of the propellant based on virtual elements 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 the interface between the matrix and particles. The phase field-based numerical simulation of the propellant three-dimensional microscopic polyhedral mesh model is carried out to obtain the phase field stiffness matrix of the propellant. The overall stiffness matrix of the propellant is obtained according to the displacement field stiffness matrix and phase field stiffness matrix of the propellant.

[0008] In combination with the first aspect, further, the overall stiffness matrix of the propellant is: ; in, represents the global stiffness matrix of the propellant, represents the displacement field stiffness matrix of the propellant, represents the phase field stiffness matrix of the propellant.

[0009] In combination with the first aspect, further, based on the simulated force-displacement curve and the overall stiffness matrix of the propellant, the performance-related parameters of the inverted propellant include: Based on the simulated force-displacement curve and the 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; Among them, the actual force-displacement curve of the propellant is obtained by conducting a constant-speed tensile test of the propellant.

[0010] In combination with the first aspect, further, based on the performance-related parameters of the propellant, the formulation optimization of the propellant includes: The propellant is coarsely divided into grids. Based on the performance-related parameters of the propellant, the particle swarm optimization algorithm is used to optimize the formula of the propellant under coarse grid division to obtain the local optimal solution for the propellant formula optimization; The propellant is meshed and divided, and based on the performance-related parameters of the propellant, the formula of the propellant is optimized under the condition of local optimal solution.

[0011] In combination with the first aspect, further, the coarse meshing of the propellant includes: dividing a single particle of the propellant as a whole into a single unit, and meshing the matrix of the propellant using the entire polyhedral unit; The mesh refinement of the propellant includes: based on the coarse mesh division of the propellant, the propellant is again divided into polyhedral meshes.

[0012] In a second aspect, the present invention provides a propellant micromechanical properties optimization system, comprising: Model building module, used to build a three-dimensional mesoscopic polyhedral mesh model of the propellant based on the real mesoscopic morphology of the propellant; Numerical simulation module, used to carry out numerical simulation of the three-dimensional microscopic polyhedral mesh model of the propellant based on virtual units and phase field, and obtain the overall stiffness matrix of the propellant; The constant speed stretching simulation module is used to carry out constant speed stretching simulation of the propellant and obtain the simulated force-displacement curve of the propellant; Inversion module, used to invert the performance-related parameters of the propellant based on the simulated force-displacement curve and the overall stiffness matrix of the propellant; The optimization module is used to optimize the propellant formula based on the performance-related parameters of the propellant to achieve the optimization of the propellant's microscopic mechanical properties; Among them, the performance-related parameters of the propellant include the matrix damage factor of the propellant, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface.

[0013] In a third aspect, the present invention provides a computer device, comprising: Storage medium: used to store computer programs; Processor: used to execute a computer program to implement the method for optimizing the microscopic mechanical properties of the propellant as described in any one of the first aspects.

[0014] In a fourth aspect, the present invention provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the method for optimizing the microscopic mechanical properties of a propellant as described in any one of the first aspects.

[0015] In a fifth aspect, the present invention provides a computer program product, comprising a computer program, which, when executed by a processor, implements the method for optimizing the microscopic mechanical properties of a propellant as described in any one of the first aspects.

[0016] Compared with the prior art, the present invention has the following beneficial effects: The method for optimizing the microscopic mechanical properties of a propellant provided by the present invention obtains the overall stiffness matrix of the propellant by carrying out numerical simulation of a three-dimensional microscopic polyhedral mesh model of the propellant based on virtual units and phase fields, and inverts the matrix damage factor of the propellant, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface based on the simulated force-displacement curve and the overall stiffness matrix of the propellant, thereby optimizing the formulation of the propellant. The method can address the three types of damage, namely, propellant matrix damage, matrix-particle interface debonding, and particle crushing, to achieve optimization of the microscopic mechanical properties of the propellant. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a flow chart of a method for optimizing the microscopic mechanical properties of a propellant provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the three-dimensional true microscopic morphology of the propellant provided by an embodiment of the present invention; Figure 3 is a schematic diagram of propellant polyhedron mesh division provided by an embodiment of the present invention; Figure 4 Schematic diagram of a polyhedral cohesive unit of a propellant provided in an embodiment of the present invention; wherein (a) is a schematic diagram of a polyhedral cohesive unit before deformation, and (b) is a schematic diagram of a polyhedral cohesive unit after deformation; Figure 5 It is a schematic diagram of the structure of a propellant containing diffuse cracks provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0018] The technical solution of the present application is further described in detail below in conjunction with specific implementation methods.

[0019] The embodiments of the present application are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present application, and should not be construed as limitations on the present application. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments may be combined with each other.

[0020] The embodiment of the present application provides a method for optimizing the microscopic mechanical properties of a propellant. The method for optimizing the microscopic mechanical properties of a propellant provided in the embodiment of the present application can be applied to a terminal and can be executed by a propellant microscopic mechanical properties optimization system. The propellant microscopic mechanical properties optimization system can be implemented by software and / or hardware. The propellant microscopic mechanical properties optimization system can be integrated in a terminal, for example: any tablet computer or computer device with communication function.

[0021] Figure 1 is a flow chart of the method for optimizing the microscopic mechanical properties of propellants provided in this embodiment. This flow chart only shows the logical sequence of the method of this embodiment. Different methods can be used without conflict. Figure 1 The steps shown or described are accomplished in the order shown.

[0022] like Figure 1 As shown, the method for optimizing the microscopic mechanical properties of the propellant provided in this embodiment includes: Based on the real mesoscopic morphology of the propellant, a three-dimensional mesoscopic polyhedral mesh model of the propellant is constructed; Carry out numerical simulation of the three-dimensional mesoscopic polyhedral mesh model of the propellant based on virtual elements and phase field to obtain the overall stiffness matrix of the propellant; Carry out constant-speed stretching simulation of propellant to obtain the simulated force-displacement curve of propellant; Based on the simulated force-displacement curve and the 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 formula is optimized to achieve optimization of the propellant's microscopic mechanical properties.

[0023] In this embodiment, the performance-related parameters of the propellant include the matrix damage factor of the propellant, the fracture strength of the interface between the matrix and the particles, and the critical strain energy release rate of the interface between the matrix and the particles.

[0024] The method for optimizing the mesoscopic mechanical properties of propellants provided in this embodiment obtains the overall stiffness matrix of the propellant by carrying out numerical simulation of a three-dimensional mesoscopic polyhedral mesh model of the propellant based on virtual units and phase fields, and inverts the matrix damage factor of the propellant, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface based on the simulated force-displacement curve and the overall stiffness matrix of the propellant, thereby optimizing the formulation of the propellant. This method can address the three types of damage, namely, propellant matrix damage, matrix-particle interface debonding, and particle crushing, to achieve optimization of the mesoscopic mechanical properties of the propellant.

[0025] In a possible embodiment, constructing a three-dimensional mesoscopic polyhedral mesh model of the propellant based on the actual mesoscopic morphology of the propellant includes: Based on the real mesoscopic morphology of the propellant, a three-dimensional mesoscopic geometric model of the propellant is constructed using the dynamic method; The three-dimensional microscopic geometric model of the propellant is divided into polyhedral meshes, and polyhedral cohesion units are set at the interface between the matrix and particles of the propellant to obtain the three-dimensional microscopic polyhedral mesh model of the propellant.

[0026] Specifically, Figure 2 As shown in the figure, the propellant is CT scanned to obtain the real microscopic morphology of the propellant. Based on the real microscopic morphology of the propellant, a three-dimensional microscopic geometric model of the propellant is constructed using the dynamic method. Figure 3 As shown in Figure 2, the three-dimensional micro-geometric model of the propellant is divided into polyhedral meshes, as shown in Figure 2. Figure 4 As shown, a polyhedral cohesion unit is set at the interface between the matrix and the particles of the propellant to obtain a three-dimensional microscopic polyhedral mesh model of the propellant. Figure 4 In the figure, (a) is a schematic diagram of the polyhedral internal cohesive unit before deformation, and (b) is a schematic diagram of the polyhedral internal cohesive unit after deformation. Indicates the amount of deformation.

[0027] In a possible embodiment, a numerical simulation of a three-dimensional microscopic polyhedral mesh model of a propellant based on virtual elements and phase fields is performed to obtain an overall stiffness matrix of the propellant, including: The virtual element method is used to carry out numerical simulation of the three-dimensional microscopic polyhedral mesh model of the propellant based on virtual elements 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 the interface between the matrix and particles. The phase field-based numerical simulation of the propellant three-dimensional microscopic polyhedral mesh model is carried out to obtain the phase field stiffness matrix of the propellant. The overall stiffness matrix of the propellant is obtained according to the displacement field stiffness matrix and phase field stiffness matrix of the propellant.

[0028] Specifically, Figure 5 As shown, the region described by the phase field is , Figure 5 middle, represents the boundary subjected to distributed force, represents the displacement boundary, Indicates the area affected by diffuse cracks. D is used to indicate the degree of propellant damage, D=0 means that the propellant has no damage, and D=1 means that the propellant is completely destroyed.

[0029] In this embodiment, the overall stiffness matrix of the propellant is: ; in, represents the global stiffness matrix of the propellant, represents the displacement field stiffness matrix of the propellant, represents the phase field stiffness matrix of the propellant.

[0030] In a possible embodiment, inverting the performance-related parameters of the propellant based on the simulated force-displacement curve and the overall stiffness matrix of the propellant includes: inverting the performance-related parameters of the propellant based on the simulated force-displacement curve and the overall stiffness matrix of the propellant using a particle swarm optimization algorithm, 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.

[0031] In this embodiment, the actual force-displacement curve of the propellant is obtained by carrying out a propellant constant speed tensile test.

[0032] In a possible embodiment, based on the performance-related parameters of the propellant, optimizing the formulation of the propellant includes: The propellant is coarsely divided into grids. Based on the performance-related parameters of the propellant, the particle swarm optimization algorithm is used to optimize the formula of the propellant under coarse grid division to obtain the local optimal solution for the propellant formula optimization; The propellant is meshed and divided, and based on the performance-related parameters of the propellant, the formula of the propellant is optimized under the condition of local optimal solution.

[0033] Specifically, the coarse meshing of the propellant includes: dividing the individual particles of the propellant into individual units as a whole, and using the entire polyhedral unit to mesh the matrix of the propellant; the fine meshing of the propellant includes: on the basis of the coarse meshing of the propellant, the propellant is again meshed with a polyhedron.

[0034] The present application embodiment provides a propellant microscopic mechanical property optimization system, comprising: A pre-training module, used to pre-train the drilling rig formation recognition model using the actual construction label data of the drilling rig, and obtain a pre-trained drilling rig formation recognition model; A secondary training module is used to perform secondary training on the pre-trained drilling rig formation recognition model using the drilling rig comparison label data to obtain a trained drilling rig formation recognition model; The identification module is used to input the current construction data of the drilling rig into the trained formation identification model of the drilling rig to perform formation identification and obtain the current formation type of the drilling rig; Among them, the drilling rig formation recognition model is built based on the long short-term memory network.

[0035] The propellant micromechanical properties optimization system provided in this embodiment can execute the propellant micromechanical properties optimization method provided in the embodiment of this application, and has the corresponding functional modules and beneficial effects of the execution method.

[0036] An embodiment of the present application provides a computer device, including: Storage medium for storing computer programs; A processor is used to execute a computer program to implement the method for optimizing the microscopic mechanical properties of a propellant provided in an embodiment of the present application.

[0037] An embodiment of the present application provides a computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, the method for optimizing the microscopic mechanical properties of a propellant provided in the embodiment of the present application is implemented.

[0038] The embodiment of the present application provides a computer program product, including a computer program. When the computer program is executed by a processor, the method for optimizing the microscopic mechanical properties of the propellant provided in the embodiment of the present application is implemented.

[0039] Those skilled in the art will appreciate that the embodiments of the present application may be provided as methods, systems or computer program products. Therefore, the present application may take the form of a complete hardware embodiment, a complete software embodiment or an embodiment combining software and hardware. Moreover, the present application may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program codes.

[0040] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems) and computer program products according to the embodiments of the present application. It should be understood that each process and / or block in the flowchart and / or block diagram and the combination of the processes and / or blocks in the flowchart and / or block diagram can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0041] These computer program instructions may also be stored in a computer-readable memory capable of directing a computer or other programmable data processing device to operate in a specific manner, so that the instructions stored in the computer-readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 A process or multiple processes and / or boxes Figure 1 A function specified in one or more boxes.

[0042] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing instructions for implementing the process. Figure 1 A process or multiple processes and / or boxes Figure 1 A step that specifies a function in one or more boxes.

[0043] The above are only preferred implementations of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.

Claims

1. A method for optimizing the microscopic mechanical properties of a propellant, characterized in that: include: Based on the real mesoscopic morphology of the propellant, a three-dimensional mesoscopic polyhedral mesh model of the propellant is constructed; Carry out numerical simulation of the three-dimensional mesoscopic polyhedral mesh model of the propellant based on virtual elements and phase field to obtain the overall stiffness matrix of the propellant; Carry out constant-speed stretching simulation of propellant to obtain the simulated force-displacement curve of propellant; Based on the simulated force-displacement curve and the 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 formula is optimized to achieve the optimization of the propellant's microscopic mechanical properties; Among them, the performance-related parameters of the propellant include the matrix damage factor of the propellant, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface.

2. The method for optimizing the microscopic mechanical properties of a propellant according to claim 1, characterized in that: Based on the real microscopic morphology of the propellant, the three-dimensional microscopic polyhedral mesh model of the propellant is constructed, including: Based on the real mesoscopic morphology of the propellant, a three-dimensional mesoscopic geometric model of the propellant is constructed using the dynamic method; The three-dimensional microscopic geometric model of the propellant is divided into polyhedral meshes, and polyhedral cohesion units are set at the interface between the matrix and particles of the propellant to obtain the three-dimensional microscopic polyhedral mesh model of the propellant.

3. The method for optimizing the microscopic mechanical properties of a propellant according to claim 1, characterized in that: Carry out numerical simulation of the three-dimensional microscopic polyhedral mesh model of the propellant based on virtual elements and phase field to obtain the overall stiffness matrix of the propellant including: The virtual element method is used to carry out numerical simulation of the three-dimensional microscopic polyhedral mesh model of the propellant based on virtual elements 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 the interface between the matrix and particles. The phase field-based numerical simulation of the propellant three-dimensional microscopic polyhedral mesh model is carried out to obtain the phase field stiffness matrix of the propellant. The overall stiffness matrix of the propellant is obtained according to the displacement field stiffness matrix and phase field stiffness matrix of the propellant.

4. The method for optimizing the microscopic mechanical properties of a propellant according to claim 3, characterized in that: The overall stiffness matrix of the propellant is: ； in, represents the global stiffness matrix of the propellant, represents the displacement field stiffness matrix of the propellant, represents the phase field stiffness matrix of the propellant.

5. The method for optimizing the microscopic mechanical properties of a propellant according to claim 1, characterized in that: Based on the simulated force-displacement curve and the overall stiffness matrix of the propellant, the performance-related parameters of the inverted propellant include: Based on the simulated force-displacement curve and the 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; Among them, the actual force-displacement curve of the propellant is obtained by conducting a constant-speed tensile test of the propellant.

6. The method for optimizing the microscopic mechanical properties of a propellant according to claim 1, characterized in that: Based on the performance-related parameters of the propellant, the propellant formulation optimization includes: The propellant is coarsely divided into grids. Based on the performance-related parameters of the propellant, the particle swarm optimization algorithm is used to optimize the formula of the propellant under coarse grid division to obtain the local optimal solution for the propellant formula optimization; The propellant is meshed and divided, and based on the performance-related parameters of the propellant, the formula of the propellant is optimized under the condition of local optimal solution.

7. The method for optimizing the microscopic mechanical properties of a propellant according to claim 6, characterized in that: The coarse meshing of the propellant includes: dividing the individual particles of the propellant into individual units as a whole, and meshing the matrix of the propellant using the entire polyhedral unit; The mesh refinement of the propellant includes: based on the coarse mesh division of the propellant, the propellant is again divided into polyhedral meshes.

8. A propellant micromechanical properties optimization system, characterized in that: include: Model building module, used to build a three-dimensional mesoscopic polyhedral mesh model of the propellant based on the real mesoscopic morphology of the propellant; Numerical simulation module, used to carry out numerical simulation of three-dimensional microscopic polyhedral mesh model of propellant based on virtual unit and phase field, and obtain the overall stiffness matrix of propellant; The constant speed stretching simulation module is used to carry out constant speed stretching simulation of propellant and obtain the simulated force-displacement curve of the propellant; Inversion module, used to invert the performance-related parameters of the propellant based on the simulated force-displacement curve and the overall stiffness matrix of the propellant; The optimization module is used to optimize the propellant formula based on the performance-related parameters of the propellant to achieve the optimization of the propellant's microscopic mechanical properties; Among them, the performance-related parameters of the propellant include the matrix damage factor of the propellant, the fracture strength of the matrix-particle interface, and the critical strain energy release rate of the matrix-particle interface.

9. A computer device comprising: Storage medium for storing computer programs; A processor, used to execute the computer program to implement the method for optimizing the mesomechanical properties of a propellant according to any one of claims 1 to 7.

10. 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 mesomechanical properties of a propellant according to any one of claims 1 to 7.

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