A method, system, device and medium for predicting the blast performance of a composite shell
By constructing a finite element model of composite shell winding and bursting, and combining fiber bundle performance parameters and the generalized three-dimensional Hashin criterion, the influence of residual stress on bursting performance during composite shell winding was solved, and the accurate prediction of shell bursting strength was achieved, guiding the preparation of high-performance shells.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- NORTHWESTERN POLYTECHNICAL UNIV
- Filing Date
- 2023-08-24
- Publication Date
- 2026-07-24
AI Technical Summary
Existing technologies cannot accurately predict the impact of residual stress on the burst performance of composite material shells during the winding process, resulting in an inability to accurately predict the burst strength of composite material shells.
By constructing finite element models of the composite shell winding and bursting processes, and combining the performance parameters of the fiber bundles, the residual stress of the fibers when winding is completed is calculated, and the maximum burst pressure when the shell fails is predicted using the generalized three-dimensional Hashin criterion.
It enables accurate prediction of the burst performance of composite material shells, guiding the preparation of high-performance shells.
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Figure CN117113763B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of mechanical performance analysis technology for solid rocket motor casings, and in particular to a method, system, equipment, and medium for predicting the burst performance of composite material casings. Background Technology
[0002] Composite material shells, serving as propellant tanks and combustion sites in solid rocket motors, withstand the high-pressure gas flow generated by propellant combustion during service. Predicting the burst performance of composite material shells using the finite element method has been a hot research topic. The molding of composite material shells involves fiber winding, during which the winding tension in the fiber direction causes interactions between different fiber layers, leading to non-uniform stress within the composite material shell—residual stress. This residual stress affects the burst strength of the composite material shell during service. Currently, the calculation of residual stress during the winding process and the prediction of burst performance are studied separately, making it impossible to accurately predict the burst strength of composite material shells. Therefore, coupling the influence of residual stress during the winding process to burst performance prediction is crucial for accurately predicting the burst strength of composite material shells. Summary of the Invention
[0003] The purpose of this invention is to provide a method, system, device and medium for predicting the burst performance of composite material shells, so as to accurately predict the maximum burst pressure when the composite material shell fails.
[0004] To achieve the above objectives, the present invention provides the following solution:
[0005] A method for predicting the burst performance of a composite material shell, comprising:
[0006] The performance parameters of the fiber bundles during the winding process of the composite material shell are obtained; the performance parameters of the fiber bundles include the number of layers, width, thickness, density, elastic modulus, Poisson's ratio, shear modulus, strength and winding tension of the fiber bundles;
[0007] A finite element model of the composite material shell winding process is constructed based on the performance parameters of the fiber bundle, and the residual stress of the fiber when winding is completed is determined based on the finite element model of the composite material shell winding process.
[0008] A finite element model of the composite material shell explosion process is constructed, and the maximum explosion pressure when the composite material shell fails is determined based on the fiber residual stress when the winding is completed and the finite element model of the composite material shell explosion process; the maximum explosion pressure when the composite material shell fails characterizes the explosion performance of the composite material shell.
[0009] Optionally, a finite element model of the composite material shell winding process is constructed based on the performance parameters of the fiber bundle, specifically including:
[0010] An initial fiber winding model is established based on the performance parameters of the fiber bundle; the initial fiber winding model includes several winding layers, each of which is obtained by winding the fiber bundle.
[0011] Kill the fiber bundles of all winding layers in the initial fiber winding model;
[0012] The fiber bundles in the initial fiber winding model are activated layer by layer according to the winding process, and the fiber stress and deformation results of the winding layer are determined by the equivalent temperature method until the fiber stress and deformation results of all winding layers are determined, thus obtaining the finite element model of the composite material shell winding process.
[0013] Optionally, for the i-th winding layer, the equivalent temperature method is used to determine the fiber stress and deformation results of the winding layer, specifically including:
[0014] Calculate the fiber winding prestress of the i-th winding layer based on the width, thickness and winding tension of the fiber bundle;
[0015] A virtual temperature field is applied to the fiber bundle of the i-th winding layer;
[0016] Calculate the fiber-direction thermal stress of the i-th winding layer under a virtual temperature field;
[0017] Determine whether the fiber winding prestress of the i-th winding layer is equal to the fiber-direction thermal stress of the i-th winding layer under the virtual temperature field, and obtain the determination result;
[0018] If the result is negative, return to the step of "applying a virtual temperature field to the fiber bundle of the i-th winding layer";
[0019] If the judgment result is yes, then the fiber stress and deformation result of the i-th winding layer are determined according to the virtual temperature field and the performance parameters of the fiber bundle.
[0020] Optionally, the residual fiber stress at the completion of the winding is calculated from the fiber stress and deformation results of all winding layers determined in the finite element model of the composite material shell winding process.
[0021] Optionally, the maximum burst pressure at which the composite shell fails is determined based on the residual stress of the fiber when the winding is completed and the finite element model of the composite shell bursting process, specifically including:
[0022] Using the residual stress of the fiber when the winding is completed as the initial predefined field, the damage of the composite shell under the action of the explosion internal pressure is determined based on the finite element model of the explosion process of the composite shell.
[0023] The maximum burst pressure at which the composite material shell fails is determined based on the damage condition of the composite material shell using composite material failure criteria.
[0024] Optionally, the failure criterion of the composite material is a generalized three-dimensional Hashin criterion; the generalized three-dimensional Hashin criterion includes at least one of the following: fiber tensile failure condition, fiber compressive failure condition, matrix tensile failure condition, matrix compressive failure condition, interlaminar tensile failure condition, and interlaminar shear failure condition.
[0025] The expression for the fiber tensile failure condition is:
[0026]
[0027] The expression for the fiber compression failure condition is:
[0028]
[0029] The expression for the tensile failure condition of the matrix is:
[0030]
[0031] The expression for the matrix compression failure condition is:
[0032]
[0033] The expression for the interlaminar tensile failure condition is:
[0034]
[0035] The expression for the interlaminar shear failure condition is:
[0036]
[0037] Among them, X T X represents the axial tensile strength of a unidirectional composite material. C Y represents the axial compressive strength of a unidirectional composite material; T Y represents the transverse tensile strength of a unidirectional composite material. C Z represents the transverse compressive strength of a unidirectional composite material. T S represents the longitudinal tensile strength of a unidirectional composite material. 12 S represents the in-plane shear strength of a unidirectional composite material. 13 S represents the in-plane shear strength of a unidirectional composite material. 23 σ represents the interlaminar shear strength of a unidirectional composite material. 11 σ represents the first normal stress component of the stress tensor. 22 σ represents the second normal stress component of the stress tensor.33 τ represents the third normal stress component of the stress tensor. 12 τ represents the first shear stress component of the stress tensor. 13 τ represents the second shear stress component of the stress tensor. 23 The stress tensor represents the third shear stress component; the composite material shell is formed from the unidirectional composite material, which includes several layers of fibers and a matrix; the stress tensor characterizes the internal pressure during the explosion of the composite material shell.
[0038] Optionally, both the finite element model of the composite material shell winding process and the finite element model of the composite material shell explosion process are constructed based on the ABAQUS platform.
[0039] A composite material shell burst performance prediction system, comprising:
[0040] The performance parameter acquisition module is used to acquire the performance parameters of the fiber bundles during the winding process of the composite material shell; the performance parameters of the fiber bundles include the number of layers, width, thickness, density, elastic modulus, Poisson's ratio, shear modulus, strength, and winding tension of the fiber bundles;
[0041] The residual stress calculation module is used to construct a finite element model of the composite material shell winding process based on the performance parameters of the fiber bundle, and to determine the fiber residual stress when winding is completed based on the finite element model of the composite material shell winding process.
[0042] The blast strength prediction module is used to construct a finite element model of the blasting process of the composite material shell, and to determine the maximum blast pressure when the composite material shell fails based on the fiber residual stress when the winding is completed and the finite element model of the blasting process of the composite material shell; the maximum blast pressure when the composite material shell fails characterizes the blasting performance of the composite material shell.
[0043] An electronic device includes a memory and a processor, the memory storing a computer program, and the processor running the computer program to enable the electronic device to perform the above-described method for predicting the burst performance of composite material shells.
[0044] A computer-readable storage medium storing a computer program that, when executed by a processor, implements the above-described method for predicting the burst performance of composite material shells.
[0045] According to specific embodiments provided by the present invention, the present invention discloses the following technical effects:
[0046] The method for predicting the burst performance of composite material shells provided by this invention considers the influence of residual fiber stress on the burst performance of composite material shells during the winding process, based on existing research. It predicts the maximum burst pressure of composite material shells by analyzing the damage and failure of the composite material, and can accurately predict the maximum burst pressure when the composite material shell fails. This has important guiding significance for the preparation of high-performance shells. Attached Figure Description
[0047] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0048] Figure 1 A flowchart of the method for predicting the burst performance of composite material shells provided by the present invention;
[0049] Figure 2 A flowchart for constructing a finite element model of the composite material shell winding process provided by the present invention;
[0050] Figure 3 The distribution diagram of fiber circumferential stress after the composite material shell of the present invention is completed;
[0051] Figure 4 A schematic diagram of a three-dimensional model of a fiber-wound composite material shell provided by the present invention;
[0052] Figure 5 This invention provides a schematic diagram of the predicted damage to the first layer of the composite material shell during the explosion process.
[0053] Figure 6 A schematic diagram illustrating the predicted damage to the fourth layer of the composite material shell during the explosion process, provided by this invention.
[0054] Figure 7 A schematic diagram illustrating the predicted damage to the sixth layer of the composite material shell during the blasting process, provided by this invention.
[0055] Figure 8 A schematic diagram illustrating the predicted damage to the eighth layer of the composite material shell during the blasting process, provided by this invention.
[0056] Figure 9 This is a block diagram of the composite material shell burst performance prediction system provided by the present invention. Detailed Implementation
[0057] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.
[0058] The purpose of this invention is to provide a method, system, device and medium for predicting the burst performance of composite material shells, so as to accurately predict the maximum burst pressure when the composite material shell fails.
[0059] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.
[0060] Example 1
[0061] This invention provides a method for predicting the burst performance of composite material shells. For example... Figure 1 As shown, the method includes:
[0062] Step 101: Obtain the performance parameters of the fiber bundles during the winding process of the composite material shell; the performance parameters of the fiber bundles include the number of layers, width, thickness, density, elastic modulus, Poisson's ratio, shear modulus, strength and winding tension of the fiber bundles.
[0063] Step 102: Construct a finite element model of the composite material shell winding process based on the performance parameters of the fiber bundle, and determine the fiber residual stress when winding is completed based on the finite element model of the composite material shell winding process.
[0064] like Figure 2 As shown, a finite element model of the composite material shell winding process is constructed based on the performance parameters of the fiber bundle, specifically including:
[0065] (1) Establish an initial fiber winding model (i.e., an N-layer winding fiber model, where N is the number of winding layers) based on the performance parameters of the fiber bundle; the initial fiber winding model includes several winding layers, each of which is obtained by winding the fiber bundle.
[0066] (2) Kill all fiber bundles in the initial fiber winding model.
[0067] (3) Activate the fiber bundles of the winding layer in the initial fiber winding model layer by layer according to the winding process, and use the equivalent temperature method to determine the fiber stress and deformation results of the winding layer until the fiber stress and deformation results of all winding layers are determined, so as to obtain the finite element model of the composite material shell winding process.
[0068] As a specific implementation method, the equivalent temperature method is used to apply fiber winding tension; contact units simulate the interaction between adjacent winding layers; and the death / birth unit, i.e., the model change function, activates the winding layer fibers layer by layer, thereby simulating the fiber winding process. The equivalent temperature method assigns a coefficient of thermal expansion and a temperature field change to the composite material. When the strain of the composite material caused by thermal expansion is equal to the strain generated by the fiber under winding tension, the thermal stress in the fiber direction can be equivalent to the initial winding stress of the fiber. The contact unit can transmit the radial pressure of the outer fiber on the inner fiber during the winding process. The death / birth unit can kill the composite material outside the current winding layer, activating only the current winding layer and the composite material inside it.
[0069] Specifically, for the i-th winding layer, the equivalent temperature method is used to determine the fiber stress and deformation results of the winding layer, including:
[0070] (1) Calculate the fiber winding prestress of the i-th winding layer based on the width, thickness and winding tension of the fiber bundle, i.e. fiber prestress σ1(i).
[0071]
[0072] Where F represents the winding tension of the fiber bundle, b represents the width of the fiber bundle, and h represents the thickness of the fiber bundle.
[0073] (2) Assign a virtual temperature field to the fiber bundle of the i-th winding layer (i.e., the i-th winding fiber).
[0074] (3) Calculate the fiber-direction thermal stress of the i-th winding layer under the virtual temperature field, i.e., thermal stress σ2(i).
[0075] σ2(i)=β·Δφ
[0076] Where β represents the coefficient of thermal expansion in the fiber direction, and Δφ represents the change in temperature field. Both the coefficient of thermal expansion in the fiber direction and the change in temperature field are determined by the virtual temperature field assigned in step (2).
[0077] (4) Determine whether the fiber winding prestress σ1(i) of the i-th winding layer is equal to the fiber direction thermal stress σ2(i) of the i-th winding layer under the virtual temperature field, and obtain the judgment result.
[0078] (5) If the judgment result is negative, return to the step of “applying a virtual temperature field to the fiber bundle of the i-th winding layer”, i.e., step (2) above.
[0079] (6) If the judgment result is yes, then the fiber stress and deformation result of the i-th winding layer are determined according to the virtual temperature field and the performance parameters of the fiber bundle.
[0080] Since σ1(i) is the theoretically calculated prestress of the winding, but in the simulation process, the prestress is applied to the fiber by the equivalent temperature method. The stress applied by the equivalent temperature method is σ2(i). If the two are equal, it means that the fiber winding prestress is applied indirectly by the equivalent temperature method. At this time, the fiber stress and deformation results of the winding layer can be determined according to the applied virtual temperature field and the performance parameters of the fiber bundle.
[0081] In this embodiment, the residual fiber stress at the completion of winding is calculated from the fiber stress and deformation results of all winding layers determined in the finite element model of the composite material shell winding process. Specifically, the fiber stress and deformation results of each layer are first saved. Since contact units are provided between adjacent winding layers during the simulation, the interaction between winding layers can be transmitted. As the fibers are wound layer by layer, the stress of each fiber will also change. Finally, after the winding is completed, the residual fiber stress can be calculated.
[0082] Step 103: Construct a finite element model of the composite material shell explosion process, and determine the maximum explosion pressure when the composite material shell fails based on the fiber residual stress when the winding is completed and the finite element model of the composite material shell explosion process; the maximum explosion pressure when the composite material shell fails characterizes the explosion performance of the composite material shell.
[0083] Preferably, both the finite element model of the composite material shell winding process and the finite element model of the composite material shell explosion process are constructed based on the ABAQUS platform. Specifically, a three-dimensional model is established in ABAQUS according to the geometric dimensions of the composite material shell, and a gradually increasing pressure is applied inside the shell to obtain the finite element model of the composite material shell explosion process.
[0084] Specifically, determining the maximum burst pressure at which the composite shell fails, based on the residual stress of the fiber upon completion of winding and the finite element model of the composite shell's bursting process, includes:
[0085] (1) The residual stress of the fiber when the winding is completed is used as the initial predefined field, and the damage of the composite shell under the action of the explosion internal pressure is determined based on the finite element model of the explosion process of the composite shell.
[0086] (2) Using the composite material failure criterion, the maximum burst pressure when the composite material shell fails is determined based on the damage condition of the composite material shell.
[0087] As a specific implementation method, the failure criterion of the composite material is a generalized three-dimensional Hashin criterion, which reduces the material stiffness according to the mechanical property degradation model; the generalized three-dimensional Hashin criterion includes at least one of the following: fiber tensile failure condition, fiber compressive failure condition, matrix tensile failure condition, matrix compressive failure condition, interlaminar tensile failure condition, and interlaminar shear failure condition.
[0088] The expression for the fiber tensile failure condition is:
[0089]
[0090] The expression for the fiber compression failure condition is:
[0091]
[0092] The expression for the tensile failure condition of the matrix is:
[0093]
[0094] The expression for the matrix compression failure condition is:
[0095]
[0096] The expression for the interlaminar tensile failure condition is:
[0097]
[0098] The expression for the interlaminar shear failure condition is:
[0099]
[0100] In the formula, X T X represents the axial tensile strength of a unidirectional composite material. C Y represents the axial compressive strength of a unidirectional composite material; T Y represents the transverse tensile strength of a unidirectional composite material. C Z represents the transverse compressive strength of a unidirectional composite material. T S represents the longitudinal tensile strength of a unidirectional composite material. 12 S represents the in-plane shear strength of a unidirectional composite material. 13 S represents the in-plane shear strength of a unidirectional composite material. 23 σ represents the interlaminar shear strength of a unidirectional composite material. 11 σ represents the first normal stress component of the stress tensor. 22 σ represents the second normal stress component of the stress tensor. 33 τ represents the third normal stress component of the stress tensor. 12τ represents the first shear stress component of the stress tensor. 13 τ represents the second shear stress component of the stress tensor. 23 The third shear stress component represents the stress tensor; the composite material shell is formed from the unidirectional composite material, which includes several layers of fibers and a matrix. During the load-bearing process, the fibers and matrix will be damaged, and interlayer cracks will occur; the stress tensor characterizes the internal pressure during the explosion of the composite material shell.
[0101] The following is a specific embodiment, taking the prediction of the burst performance of a fiber-wound composite material shell as an example to demonstrate its technical effect. In this embodiment, progressive damage analysis was performed to obtain the maximum burst pressure of the fiber-wound composite material shell. The specific process includes the following steps:
[0102] 1. Determine the fiber bundle performance parameters, which are shown in Table 1.
[0103] Table 1 Performance parameters of T800S fiber bundles
[0104]
[0105]
[0106] 2. A finite element model of the composite material shell winding process was constructed based on the ABAQUS platform, and the residual stress of the fibers upon completion of winding was calculated. First, all the fibers were killed. Then, the fibers were activated layer by layer according to the winding process. Each layer of fiber was assigned a coefficient of thermal expansion and a temperature field. When the strain of the fiber layer due to thermal expansion equals the strain of the fiber under winding tension, the thermal stress in the fiber direction can be equivalent to the fiber winding prestress, until all fiber layers are wound. The simulation process is as follows: Figure 2 As shown, constant winding tension is used for winding, and the fiber circumferential stress distribution after winding is as follows. Figure 3 As shown, S,S22(CSYS-1) represents the circumferential stress in cylindrical coordinates, which is a component of the fiber residual stress. The final three-dimensional model of the fiber-wound composite shell is as follows. Figure 4 As shown,
[0107] 3. A finite element model of the composite material shell explosion process was constructed based on the ABAQUS platform. The calculated fiber residual stress was used as the initial predefined field of the explosion loading process to predict and analyze the explosion performance of the composite material shell. The maximum pressure when the composite material shell fails was obtained by adopting the composite material failure criterion.
[0108] Specifically, the calculated fiber winding residual stress is used as the initial predefined field for damage analysis of the subsequent blasting process. Gradually increasing internal pressure is applied inside the shell, and the Hashin damage judgment criterion is introduced to calculate the damage of the composite material under the action of blasting internal pressure.
[0109] Based on the damage condition of the composite material, the maximum internal pressure at which the output casing fails is determined, i.e., the maximum burst pressure. The damage conditions of the first, fourth, sixth, and eighth layers of the composite material casing are as follows: Figure 5 , Figure 6 , Figure 7 and Figure 8 As shown, SDV1 represents the fiber tensile failure condition. When SDV1>1, the composite material experiences fiber tensile failure, and the burst pressure of the shell is 42.5MPa.
[0110] Example 2
[0111] To implement the method corresponding to Embodiment 1 above and achieve the corresponding functions and technical effects, a composite material shell burst performance prediction system is provided below. For example... Figure 9 As shown, the system includes:
[0112] The performance parameter acquisition module 901 is used to acquire the performance parameters of the fiber bundle during the winding process of the composite material shell; the performance parameters of the fiber bundle include the number of layers, width, thickness, density, elastic modulus, Poisson's ratio, shear modulus, strength and winding tension of the fiber bundle.
[0113] The residual stress calculation module 902 is used to construct a finite element model of the composite material shell winding process based on the performance parameters of the fiber bundle, and to determine the fiber residual stress when winding is completed based on the finite element model of the composite material shell winding process.
[0114] The blast strength prediction module 903 is used to construct a finite element model of the blasting process of the composite material shell, and to determine the maximum blast pressure when the composite material shell fails based on the fiber residual stress when the winding is completed and the finite element model of the blasting process of the composite material shell; the maximum blast pressure when the composite material shell fails characterizes the blasting performance of the composite material shell.
[0115] Example 3
[0116] This invention also provides an electronic device, including a memory and a processor. The memory stores a computer program, and the processor runs the computer program to enable the electronic device to perform the composite material shell burst performance prediction method of Embodiment 1. The electronic device may be a server.
[0117] In addition, the present invention also provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the method for predicting the burst performance of composite material shells in Embodiment 1.
[0118] In summary, the method, system, equipment, and medium for predicting the burst performance of composite material shells provided by this invention first obtain the performance parameters of the fiber bundles during the winding process of the composite material shell; second, based on the performance parameters of the fiber bundles, a finite element model of the composite material shell winding process is constructed, and the residual stress of the fibers at the completion of winding is calculated; finally, a finite element model of the burst process of the composite material shell is constructed, and the calculated residual stress of the fibers is used as an initial predefined field to perform burst performance prediction analysis on the composite material shell, and the maximum pressure at the time of failure of the composite material shell is predicted using composite material failure criteria. This invention, based on existing research, considers the influence of residual stress of fibers on the burst performance of the composite material shell during the winding process, and predicts the maximum burst pressure of the composite material shell through damage and failure of the composite material, thus accurately predicting the burst performance of the composite material shell, and therefore has important guiding significance for the preparation of high-performance shells.
[0119] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the systems disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the descriptions are relatively simple; relevant parts can be referred to the method section.
[0120] This document uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. Furthermore, those skilled in the art will recognize that, based on the ideas of the present invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of the present invention.
Claims
1. A method for predicting the burst performance of a composite material shell, characterized in that, include: The performance parameters of the fiber bundles during the winding process of the composite material shell are obtained; the performance parameters of the fiber bundles include the number of layers, width, thickness, density, elastic modulus, Poisson's ratio, shear modulus, strength and winding tension of the fiber bundles; Constructing a finite element model of the composite material shell winding process based on the performance parameters of the fiber bundles specifically includes: establishing an initial fiber winding model based on the performance parameters of the fiber bundles; the initial fiber winding model includes several winding layers, each of which is obtained by winding a fiber bundle; killing the fiber bundles of all winding layers in the initial fiber winding model; activating the fiber bundles of the winding layers in the initial fiber winding model layer by layer according to the winding process, and using the equivalent temperature method to determine the fiber stress and deformation results of the winding layers until the fiber stress and deformation results of all winding layers are determined, thereby obtaining the finite element model of the composite material shell winding process; and determining the residual fiber stress when winding is completed based on the finite element model of the composite material shell winding process. Specifically, for the i-th winding layer, the equivalent temperature method is used to determine the fiber stress and deformation results of the winding layer. This includes: calculating the fiber winding prestress of the i-th winding layer based on the width, thickness, and winding tension of the fiber bundle; applying a virtual temperature field to the fiber bundle of the i-th winding layer; calculating the fiber-direction thermal stress of the i-th winding layer under the virtual temperature field; determining whether the fiber winding prestress of the i-th winding layer is equal to the fiber-direction thermal stress of the i-th winding layer under the virtual temperature field, and obtaining the determination result; if the determination result is negative, returning to the step of "applying a virtual temperature field to the fiber bundle of the i-th winding layer"; if the determination result is positive, determining the fiber stress and deformation results of the i-th winding layer based on the virtual temperature field and the performance parameters of the fiber bundle. A finite element model of the composite material shell's explosion process is constructed, and the maximum explosion pressure at which the composite material shell fails is determined based on the fiber residual stress at the completion of winding and the finite element model of the composite material shell's explosion process. Specifically, this includes: using the fiber residual stress at the completion of winding as an initial predefined field, determining the damage condition of the composite material shell under the action of explosion internal pressure based on the finite element model of the composite material shell's explosion process; adopting composite material failure criteria, determining the maximum explosion pressure at which the composite material shell fails based on the damage condition of the composite material shell; the maximum explosion pressure at which the composite material shell fails characterizes the explosion performance of the composite material shell.
2. The method for predicting the burst performance of composite material shells according to claim 1, characterized in that, The residual fiber stress at the completion of winding is calculated from the fiber stress and deformation results of all winding layers determined in the finite element model of the composite material shell winding process.
3. The method for predicting the burst performance of composite material shells according to claim 1, characterized in that, The failure criterion of the composite material is the generalized three-dimensional Hashin criterion; the generalized three-dimensional Hashin criterion includes at least one of the following: fiber tensile failure condition, fiber compressive failure condition, matrix tensile failure condition, matrix compressive failure condition, interlaminar tensile failure condition, and interlaminar shear failure condition. The expression for the fiber tensile failure condition is: ； The expression for the fiber compression failure condition is: ； The expression for the tensile failure condition of the matrix is: ； The expression for the matrix compression failure condition is: ； The expression for the interlaminar tensile failure condition is: ； The expression for the interlaminar shear failure condition is: ； in, Indicates the axial tensile strength of a unidirectional composite material. Indicates the axial compressive strength of a unidirectional composite material; Indicates the transverse tensile strength of a unidirectional composite material. This indicates the transverse compressive strength of a unidirectional composite material; Indicates the longitudinal tensile strength of a unidirectional composite material; Indicates the in-plane shear strength of a unidirectional composite material. This represents the in-plane shear strength of a unidirectional composite material. Indicates the interlaminar shear strength of a unidirectional composite material; This represents the first normal stress component of the stress tensor. This represents the second normal stress component of the stress tensor. This represents the third normal stress component of the stress tensor; This represents the first shear stress component of the stress tensor. This represents the second shear stress component of the stress tensor. The stress tensor represents the third shear stress component; the composite material shell is formed from the unidirectional composite material, which includes several layers of fibers and a matrix; the stress tensor characterizes the internal pressure during the explosion of the composite material shell.
4. The method for predicting the burst performance of composite material shells according to claim 1, characterized in that, Both the finite element model of the composite material shell winding process and the finite element model of the composite material shell explosion process were constructed based on the ABAQUS platform.
5. A composite material shell burst performance prediction system, used to execute the method of claim 1, characterized in that, include: The performance parameter acquisition module is used to acquire the performance parameters of the fiber bundles during the winding process of the composite material shell; the performance parameters of the fiber bundles include the number of layers, width, thickness, density, elastic modulus, Poisson's ratio, shear modulus, strength, and winding tension of the fiber bundles; The residual stress calculation module is used to construct a finite element model of the composite material shell winding process based on the performance parameters of the fiber bundle, and to determine the fiber residual stress when winding is completed based on the finite element model of the composite material shell winding process. The blasting strength prediction module is used to construct a finite element model of the blasting process of the composite material shell, and to determine the maximum blasting pressure when the composite material shell fails based on the fiber residual stress when the winding is completed and the finite element model of the blasting process of the composite material shell. The maximum burst pressure at which the composite material shell fails characterizes the burst performance of the composite material shell.
6. An electronic device, characterized in that, The device includes a memory and a processor, the memory being used to store a computer program, and the processor running the computer program to cause the electronic device to perform the composite material shell burst performance prediction method as described in any one of claims 1 to 4.
7. A computer-readable storage medium, characterized in that, It stores a computer program that, when executed by a processor, implements the method for predicting the burst performance of composite material shells as described in any one of claims 1 to 4.