Method, device and equipment for evaluating bearing strength of inner wall of thrust chamber and medium

Abstract

The invention discloses a thrust chamber inner wall bearing strength evaluation method, device, equipment and medium, and relates to the field of material analys.The thrust chamber inner wall bearing strength evaluation method comprises the steps that a test load-displacement curve and a test engineering stress-strain curve of a ductile copper alloy test piece are obtained; determining a first constitutive parameter of the ductile copper alloy according to the test engineering stress-strain curve; performing a tensile simulation test on the finite element model of the ductile copper alloy test piece, and determining a second constitutive parameter of the ductile copper alloy when a simulation load-displacement curve generated by the tensile simulation test is consistent with the test load-displacement curve; and based on the first constitutive parameters and the second constitutive parameters, thrust chamber bearing strength evaluation is conducted on the thrust chamber constructed by the ductile copper alloy, and then the bearing capacity of the inner wall of the engine thrust chamber is accurately analyzed.

Description

Technical Field

[0001] The present invention relates to the field of material analysis, and in particular to a method, device, equipment and medium for evaluating the bearing strength of an inner wall of a thrust chamber. Background Art

[0002] In the design of liquid rocket engines, the inner wall of the high-pressure thrust chamber is the core component that bears extreme thermal-mechanical coupling loads, and is usually made of high-ductility copper alloy to meet the strength and plasticity requirements in high-temperature environments. However, during the operation of the engine, the inner wall material is in a state of plastic deformation for a long time due to repeated ultra-high pressure and transient thermal shock.

[0003] When evaluating the bearing capacity of the inner wall of the thrust chamber of a liquid rocket engine, the material constitutive model used in traditional engineering strength analysis cannot effectively process the data after necking in the tensile test of the high-ductility copper alloy. As a result, the true bearing capacity of the high-ductility copper alloy cannot be fully considered, making the evaluation results too conservative.

[0004] Therefore, how to effectively process the data after necking in the tensile test of high-ductility copper alloy in order to accurately analyze the bearing capacity of the inner wall of the engine thrust chamber has become a technical problem that technical personnel in this field urgently need to solve. Summary of the invention

[0005] The purpose of the present invention is to provide a method, device, equipment and medium for evaluating the bearing strength of the inner wall of a thrust chamber, so as to effectively process the data after necking in a tensile test of a high-ductility copper alloy and accurately analyze the bearing capacity of the inner wall of the thrust chamber of an engine.

[0006] In order to achieve the above object, the present invention provides the following technical solutions:

[0007] A method for evaluating the bearing strength of an inner wall of a thrust chamber, comprising:

[0008] The experimental load-displacement curve and experimental engineering stress-strain curve of the ductile copper alloy specimen were obtained.

[0009] According to the experimental engineering stress-strain curve, the first constitutive parameter of the ductile copper alloy is determined.

[0010] A tensile simulation test is performed on the finite element model of the ductile copper alloy test piece to determine a second constitutive parameter of the ductile copper alloy when a simulated load-displacement curve generated by the tensile simulation test is consistent with the test load-displacement curve.

[0011] Based on the first constitutive parameter and the second constitutive parameter, a thrust chamber bearing strength evaluation is performed on the thrust chamber constructed of the ductile copper alloy.

[0012] In an alternative embodiment of the present application, determining the first constitutive parameters of the ductile copper alloy according to the test engineering stress-strain curve includes: determining first curve data in the test engineering stress-strain curve before the necking point; and determining the first constitutive parameters of the ductile copper alloy according to the first curve data.

[0013] In an alternative embodiment of the present application, the first constitutive parameters include: the initial yield stress of the ductile copper alloy, the maximum hardening amount of the yield surface, and the hardening parameter; the first curve data of the test engineering stress-strain curve is represented by the following formula:

[0014]

[0015] where σ represents the stress data of the ductile copper alloy; σ0 represents the initial yield stress; represents the maximum hardening amount of the yield surface; b represents the hardening parameter; represents the equivalent plastic strain; ε p represents the plastic strain tensor.

[0016] In an alternative embodiment of the present application, performing a tensile simulation test on the finite element model of the ductile copper alloy test piece and determining the second constitutive parameters of the ductile copper alloy when the simulated load-displacement curve generated by the tensile simulation test is consistent with the test load-displacement curve includes: combining the first constitutive parameters, performing a tensile simulation test on the finite element model of the ductile copper alloy test piece to generate the simulated load-displacement curve; if the second curve data in the test load-displacement curve after the necking point is inconsistent with the third curve data in the simulated load-displacement curve after the necking point, adjusting the second constitutive parameters of the ductile copper alloy, and determining the second constitutive parameters of the ductile copper alloy when the second curve data is consistent with the third curve data.

[0017] In an alternative embodiment of the present application, evaluating the thrust chamber bearing strength of the thrust chamber constructed from the ductile copper alloy based on the first constitutive parameters and the second constitutive parameters includes: under given working conditions, performing a load test on the thrust chamber model constructed based on the first constitutive parameters and the second constitutive parameters to determine the model stress-strain curve of the inner wall of the thrust chamber model; determining the maximum strain of the inner wall of the thrust chamber model according to the model stress-strain curve; and evaluating the thrust chamber bearing strength of the thrust chamber constructed from the ductile copper alloy based on the maximum strain of the inner wall of the thrust chamber model and the ultimate fracture strain of the ductile copper alloy.

[0018] In an alternative embodiment of the present application, the model stress-strain curve is represented by the following formula:

[0019]

[0020] Among them, σ represents the stress data of the ductile copper alloy; σ u represents the stress data corresponding to the necking point; ε p represents the plastic strain tensor; represents the plastic strain component corresponding to the necking point; F represents the hardening modulus; n represents the second constitutive parameter; ε f represents the ultimate fracture strain of the ductile copper alloy.

[0021] In an alternative embodiment of the present application, the ultimate fracture strain of the ductile copper alloy is determined by the following formula:

[0022]

[0023] Among them, ε f represents the ultimate fracture strain of the ductile copper alloy; represents the reduction of area of the ductile copper alloy.

[0024] Compared with the prior art, the evaluation method for the internal bearing strength of the thrust chamber provided by the present invention combines the test load-displacement curve of the ductile copper alloy test piece obtained from the test and the tensile simulation test of the finite element model of the ductile copper alloy test piece to determine the second constitutive parameter for reflecting the stress-strain response after the necking point of the ductile copper alloy test piece, and determines the first constitutive parameter of the ductile copper alloy according to the test engineering stress-strain curve, and combines the first constitutive parameter and the second constitutive parameter to evaluate the bearing strength of the thrust chamber constructed by the ductile copper alloy, which is beneficial to accurately analyzing the bearing capacity of the inner wall of the engine thrust chamber.

[0025] The present invention also provides an evaluation device for the bearing strength of the inner wall of the thrust chamber, including:

[0026] A test data acquisition unit for acquiring the test load-displacement curve and the test engineering stress-strain curve of the ductile copper alloy test piece.

[0027] A first curve analysis unit for determining the first constitutive parameter of the ductile copper alloy according to the test engineering stress-strain curve.

[0028] A second curve analysis unit for performing a tensile simulation test on the finite element model of the ductile copper alloy to determine the second constitutive parameter of the ductile copper alloy when the simulated load-displacement curve generated by the tensile simulation test is consistent with the test load-displacement curve.

[0029] A thrust chamber evaluation unit for evaluating the load-bearing strength of a thrust chamber constructed of the ductile copper alloy based on the first constitutive parameter and the second constitutive parameter.

[0030] Compared with the prior art, the beneficial effects of the evaluation device for the load-bearing strength of the inner wall of the thrust chamber provided by the present invention are the same as those described in the technical solution of the above-mentioned evaluation method for the load-bearing strength of the inner wall of the thrust chamber, and will not be elaborated here.

[0031] The present invention also provides an electronic device, including:

[0032] A processor;

[0033] A memory for storing instructions executable by the processor;

[0034] The processor is configured to execute the above-mentioned evaluation method for the load-bearing strength of the inner wall of the thrust chamber by running the instructions in the memory.

[0035] Compared with the prior art, the beneficial effects of the electronic device provided by the present invention are the same as those described in the beneficial effects of the above-mentioned technical solution of the evaluation method for the load-bearing strength of the inner wall of the thrust chamber, and will not be elaborated here.

[0036] The present invention also provides a computer storage medium, in which instructions are stored, and when the instructions are run, the above-mentioned evaluation method for the load-bearing strength of the inner wall of the thrust chamber is implemented.

[0037] Compared with the prior art, the beneficial effects of the computer storage medium provided by the present invention are the same as those described in the beneficial effects of the above-mentioned technical solution of the evaluation method for the load-bearing strength of the inner wall of the thrust chamber, and will not be elaborated here. Description of the Drawings

[0038] The drawings described herein are used to provide a further understanding of the present invention, and constitute a part of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0039] Figure 1 It is a flowchart of the evaluation method for the load-bearing strength of the inner wall of the thrust chamber provided by the embodiment of the present application.

[0040] Figure 2 It is a schematic diagram of the test load-displacement curve and the test engineering stress-strain curve provided by the embodiment of the present application.

[0041] Figure 3 It is a schematic diagram of the finite element model of the ductile copper alloy test piece provided by the embodiment of the present application.

[0042] Figure 4 It is a schematic diagram of the 1 / N sector thrust chamber model provided by the embodiment of the present application.

[0043] Figure 5 This is a structural diagram of an evaluation device for the bearing strength of the inner wall of a thrust chamber provided by an embodiment of the present application.

[0044] Figure 6 This is a schematic structural diagram of an electronic device provided by an embodiment of the present application. Detailed implementation manners

[0045] For the convenience of clearly describing the technical solutions of the embodiments of the present invention, in the embodiments of the present invention, terms such as "first" and "second" are used to distinguish identical or similar items with basically the same functions and effects. For example, the first threshold and the second threshold are only used to distinguish different thresholds, and do not limit their order. Those skilled in the art can understand that terms such as "first" and "second" do not limit the quantity and execution order, and terms such as "first" and "second" do not necessarily limit being different.

[0046] It should be noted that in the present invention, words such as "exemplary" or "for example" are used to indicate examples, illustrations or explanations. Any embodiment or design solution described as "exemplary" or "for example" in the present invention should not be construed as being more preferred or having more advantages than other embodiments or design solutions. Exactly, using words such as "exemplary" or "for example" is intended to present relevant concepts in a specific manner.

[0047] In the present invention, "at least one" means one or more, and "a plurality" means two or more. "And / or" describes the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B may represent: A exists alone, A and B exist simultaneously, and B exists alone, where A and B may be singular or plural. The character " / " generally represents an "or" relationship between the associated objects before and after. "At least one (item)" or its similar expression below refers to any combination of these items, including any combination of single item (item) or plural items (items). For example, at least one (item) of a, b or c may represent: a, b, c, the combination of a and b, the combination of a and c, the combination of b and c, or the combination of a, b and c, where a, b and c may be single or multiple.

[0048] In the design of liquid rocket engines, as the core component that bears extreme thermo-mechanical coupling loads, the inner wall of the high-pressure thrust chamber usually uses high-ductility copper alloy to meet the strength and plasticity requirements in high-temperature environments. However, during the operation of the engine, the inner wall material is in a state of plastic deformation for a long time due to repeatedly bearing ultra-high pressure and transient thermal shock.

[0049] When evaluating the bearing capacity of the inner wall of a liquid rocket engine thrust chamber, the material constitutive model used in traditional engineering strength analysis cannot effectively process the data after necking in the tensile test of high-ductility copper alloy, resulting in the inability to comprehensively consider the true bearing capacity of high-ductility copper alloy and making the evaluation results overly conservative.

[0050] Therefore, how to effectively process the data after necking in the tensile test of high-ductility copper alloy to accurately analyze the bearing capacity of the inner wall of the engine thrust chamber has become a technical problem that needs to be solved urgently by those skilled in the art.

[0051] To solve the above technical problems, the present application provides an evaluation method, device, equipment and medium for the bearing strength of the inner wall of the thrust chamber, which will be described in detail one by one in the following embodiments.

[0052] The embodiments of the present application first provide an evaluation method for the bearing strength of the inner wall of the thrust chamber. Please refer to Figure 1 , Figure 1 , which is the flow chart of the evaluation method for the bearing strength of the inner wall of the thrust chamber provided by the embodiments of the present application.

[0053] As Figure 1 shown, the evaluation method for the bearing strength of the inner wall of the thrust chamber includes the following S101 to S104.

[0054] S101, obtain the test load-displacement curve and the test engineering stress-strain curve of the ductile copper alloy test piece.

[0055] The ductile copper alloy test piece refers to a copper alloy with high plastic deformation ability formed by taking copper as the matrix and adding other elements (such as zinc, tin, phosphorus, etc.), and processed into a test sample with a specific shape (such as dumbbell shape) according to standards for mechanical property testing.

[0056] The test load-displacement curve refers to the curve that records the change of the load applied to the ductile copper alloy test piece during the tensile process with the displacement of the ductile copper alloy test piece during the mechanical property test of the ductile copper alloy test piece through the tensile test, so as to reflect the overall deformation resistance of the material.

[0057] The test engineering stress-strain curve refers to the test engineering stress-strain curve obtained by converting the test load-displacement curve to eliminate the size influence of the ductile copper alloy test piece and directly reflect the material constitutive relationship.

[0058] Please refer to Figure 2 , Figure 2 , which is the schematic diagram of the test load-displacement curve and the test engineering stress-strain curve provided by the embodiments of the present application.

[0059] As Figure 2 shown, Figure 2The left curve is the test load-displacement curve, Figure 2 The right curve is the test engineering stress-strain curve. Among them, the horizontal axis of the test load-displacement curve represents displacement, and the vertical axis represents load; the horizontal axis of the test engineering stress-strain curve represents strain, and the vertical axis represents stress.

[0060] During the process of testing the mechanical properties of a ductile copper alloy specimen through a tensile test, a necking point will occur. The necking point refers to the critical point at which the ductile copper alloy specimen transitions from uniform deformation to local concentrated deformation during plastic deformation, and its macroscopic manifestation is that the ductile copper alloy specimen visibly locally thins.

[0061] During the actual application process, the necking phenomenon occurs at the peak of the test load-displacement curve. At this time, the load increment d P is zero. Thus, the necking determination condition for the ductile copper alloy specimen can be expressed by the following formula (1):

[0062]

[0063] where σ u represents the true stress at the necking point; ε u represents the true strain at the necking point.

[0064] However, it should be noted that, as mentioned in the background art, the material constitutive used in traditional engineering strength analysis cannot effectively handle the data after the necking of ductile copper alloy. Therefore, as Figure 2 shown, the data of the test engineering stress-strain curve obtained based on the test load-displacement curve generated by the tensile test is usually inaccurate after the necking point.

[0065] Therefore, in order to comprehensively consider the true load-bearing capacity of high-ductility copper alloy, it is necessary to determine the data after the necking of the ductile copper alloy to improve the accuracy and reliability of the inner wall load-bearing assessment.

[0066] S102. Determine the first constitutive parameter of the ductile copper alloy according to the test engineering stress-strain curve.

[0067] The constitutive parameter of the ductile copper alloy refers to the key parameter in the mathematical model that describes the stress-strain relationship of the ductile copper alloy to predict the mechanical response of the ductile copper alloy under load.

[0068] Specifically, the above S102 includes:

[0069] Determine the first curve data of the test engineering stress-strain curve before the necking point; according to the first curve data, determine the first constitutive parameter of the ductile copper alloy.

[0070] In the actual application process, the first constitutive parameters of the ductile copper alloy include: the initial yield stress of the ductile copper alloy, the maximum hardening amount of the yield surface, and the hardening parameter.

[0071] The first curve data in the test engineering stress-strain curve before the necking point can be expressed by the following formula (2) and formula (3):

[0072]

[0073] Among them, σ represents the stress data of the ductile copper alloy; σ0 represents the initial yield stress; represents the maximum hardening amount of the yield surface; b represents the hardening parameter; represents the equivalent plastic strain; ε p represents the plastic strain tensor.

[0074] S103. Conduct a tensile simulation test on the finite element model of the ductile copper alloy test piece, and determine the second constitutive parameters of the ductile copper alloy when the simulated load-displacement curve generated by the tensile simulation test is consistent with the test load-displacement curve.

[0075] The purpose of S103 is to establish a high-fidelity material model for predicting mechanical behaviors under complex working conditions by iteratively adjusting the second constitutive parameters in the finite element model of the ductile copper alloy to make the simulated load-displacement curve highly coincide with the test load-displacement curve.

[0076] The finite element model is a numerical simulation tool. By discretizing the continuous material into a finite number of small elements (such as tetrahedrons, hexahedrons), combining mechanical equations and material constitutive relations, it simulates the deformation, stress distribution, and failure behavior of the material under the action of loads.

[0077] Please refer to Figure 3 , Figure 3 which is a schematic diagram of the finite element model of the ductile copper alloy test piece provided by the embodiment of the present application.

[0078] In the actual application process, a finite element model for the ductile copper alloy test piece can be established through the finite element software ABAQUS. Then, the model mesh is divided using double second-order axisymmetric elements, and the transition area is further refined. Boundary conditions are applied to the finite element model to set circumferential multi-point constraints on the upper end face of the model to constrain its axial and radial degrees of freedom.

[0079] Further set the initial material parameters of the ductile copper alloy test piece to conduct a tensile simulation test.

[0080] In the process of conducting a tensile simulation test, in order to improve the accuracy of the finite element model in describing the structure and constitutive relationship of the ductile copper alloy test piece, before conducting the tensile test, the finite element model of the ductile copper alloy test piece can be further subjected to mesh sensitivity analysis, that is, the finite element model of the ductile copper alloy test piece is divided into meshes of different sizes, and the load-displacement curves of the ductile copper alloy test piece under each mesh size are obtained. For any mesh, the mesh size when the load-displacement curve within the mesh range tends to converge is determined as the size of the mesh.

[0081] In the embodiment of the present application, the mechanical equations used in the tensile simulation test for the finite element model of the ductile copper alloy test piece are constructed by formula (1), (2) and the following formulas (3), (4), (5). Among them, formulas (1) and (2) correspond to the stress-strain curve before the necking point of the ductile copper alloy test piece, and formulas (3), (4) and (5) correspond to the stress-strain curve after the necking point of the ductile copper alloy test piece.

[0082]

[0083] Among them, σ represents the stress data of the ductile copper alloy; σ u represents the stress data corresponding to the necking point; ε p represents the plastic strain tensor; represents the plastic strain component corresponding to the necking point; F represents the hardening modulus; n represents the second constitutive parameter; ε f represents the ultimate fracture strain of the ductile copper alloy; represents the cross-sectional shrinkage rate of the ductile copper alloy.

[0084] In the actual application process, in order to make the simulated load-displacement curve generated by the tensile simulation test consistent with the test load-displacement curve, when adjusting the constitutive parameters of the finite element model of the ductile copper alloy test piece, the following principles should be followed:

[0085] 1) The necking point of the simulated load-displacement curve should not be later than the test load-displacement curve.

[0086] 2) The simulated load-displacement curve should always be below the test load-displacement curve to ensure a conservative design of the structure.

[0087] 3) The simulated load-displacement curve should include an obvious load drop section to facilitate the identification of the load at the time of structural failure.

[0088] In the process of adjusting the simulated load-displacement curve generated by the tensile simulation test based on the above principles, by adjusting the magnitude of the second constitutive parameter n, the simulated load-displacement curve is adjusted towards the test load-displacement curve until the simulated load-displacement curve is consistent with the test load-displacement curve, and the final second constitutive parameter n is determined.

[0089] S104, based on the first constitutive parameter and the second constitutive parameter, evaluate the load-bearing strength of the thrust chamber constructed of the ductile copper alloy.

[0090] The above S104 means that under given working conditions, a load test is performed on the thrust chamber model constructed based on the first constitutive parameter and the second constitutive parameter to determine the model stress-strain curve of the inner wall of the thrust chamber model; according to the model stress-strain curve, determine the maximum strain of the inner wall of the thrust chamber model; based on the maximum strain of the inner wall of the thrust chamber model and the ultimate fracture strain of the ductile copper alloy, evaluate the load-bearing strength of the thrust chamber constructed of the ductile copper alloy.

[0091] In the actual application process, the model stress-strain curve is the stress-strain curve after the necking point constructed based on the above (3), (4), and (5) to obtain the maximum strain ε of the inner wall of the thrust chamber constructed of the ductile copper alloy through experimental simulation. max 。

[0092] During the test, if the finally measured maximum strain ε of the inner wall of the thrust chamber max is less than the ultimate fracture strain ε of the ductile copper alloy f , it is determined that the inner wall of the thrust chamber meets the strength requirements; when the finally measured maximum strain ε of the inner wall of the thrust chamber max is greater than or equal to the ultimate fracture strain ε of the ductile copper alloy for the first time f , it is determined that the load applied to the thrust chamber model in the current load test is the ultimate load of the inner wall of the thrust chamber.

[0093] In the actual application process, in order to improve the calculation accuracy and efficiency, based on the structural symmetry of the thrust chamber model, the thrust chamber model can be simplified to a 1 / N sector thrust chamber model.

[0094] Please refer to Figure 4 , Figure 4 which is a schematic diagram of the 1 / N sector thrust chamber model provided by the embodiment of the present application.

[0095] As Figure 4As shown in the figure, the 1 / N sector thrust chamber model divides the thrust chamber model into N equal parts circumferentially, and one of the obtained models. During the process of constructing the thrust chamber model, it is also possible to only construct the above-mentioned 1 / N sector thrust chamber model, and add symmetric constraints and fixed constraints on the upper end face on both sides of the 1 / N sector thrust chamber model to simulate the actual situation of the 1 / N sector thrust chamber model in the overall thrust chamber model.

[0096] During the process of model construction, in order to refine the stress concentration parts in the model, the C3D8R element type can also be used to mesh the structure of the model, and on the basis of the meshed grid after division, the model can be refined to improve the reliability and stability of the thrust chamber modeling.

[0097] After obtaining the thrust chamber model through the above method, that is, on the basis of the thrust chamber model, a gradually increasing load is applied to the thrust chamber, and the maximum strain ε of the inner wall of the thrust chamber model under each load is extracted. max and compare the maximum strain ε max with the ultimate fracture strain ε of the ductile copper alloy f to complete the evaluation of the bearing strength of the thrust chamber.

[0098] In summary, the evaluation method for the bearing strength of the inner wall of the thrust chamber combines the test load-displacement curve of the ductile copper alloy test piece obtained from the test and the tensile simulation test of the finite element model of the ductile copper alloy test piece, determines the second constitutive parameter for reflecting the stress-strain response after the necking point of the ductile copper alloy test piece, and determines the first constitutive parameter of the ductile copper alloy according to the test engineering stress-strain curve, and combines the first constitutive parameter and the second constitutive parameter to evaluate the bearing strength of the thrust chamber constructed by the ductile copper alloy, which is beneficial to accurately analyze the bearing capacity of the inner wall of the engine thrust chamber.

[0099] This application also provides an evaluation device for the bearing strength of the inner wall of the thrust chamber. Please refer to Figure 5 , Figure 5 which is the structural diagram of the evaluation device for the bearing strength of the inner wall of the thrust chamber provided by the embodiment of this application.

[0100] As Figure 5 shown, the evaluation device for the bearing strength of the inner wall of the thrust chamber includes:

[0101] The test data acquisition unit 501 is used to obtain the test load-displacement curve and the test engineering stress-strain curve of the ductile copper alloy test piece.

[0102] The first curve analysis unit 502 is used to determine the first constitutive parameter of the ductile copper alloy according to the test engineering stress-strain curve.

[0103] The second curve analysis unit 503 is configured to perform a tensile simulation test on the finite element model of the ductile copper alloy, and determine the second constitutive parameter of the ductile copper alloy when the simulated load-displacement curve generated by the tensile simulation test is consistent with the test load-displacement curve.

[0104] The thrust chamber evaluation unit 504 is configured to evaluate the load-bearing strength of the thrust chamber constructed of the ductile copper alloy based on the first constitutive parameter and the second constitutive parameter.

[0105] In an alternative embodiment of the present application, determining the first constitutive parameter of the ductile copper alloy according to the test engineering stress-strain curve includes: determining first curve data in the test engineering stress-strain curve before the necking point; and determining the first constitutive parameter of the ductile copper alloy according to the first curve data.

[0106] In an alternative embodiment of the present application, the first constitutive parameter includes: the initial yield stress of the ductile copper alloy, the maximum hardening amount of the yield surface, and the hardening parameter; the first curve data of the test engineering stress-strain curve is represented by the following formula:

[0107]

[0108] where σ represents the stress data of the ductile copper alloy; σ0 represents the initial yield stress; represents the maximum hardening amount of the yield surface; b represents the hardening parameter; represents the equivalent plastic strain; ε p represents the plastic strain tensor.

[0109] In an alternative embodiment of the present application, performing a tensile simulation test on the finite element model of the ductile copper alloy test piece, and determining the second constitutive parameter of the ductile copper alloy when the simulated load-displacement curve generated by the tensile simulation test is consistent with the test load-displacement curve includes: combining the first constitutive parameter, performing a tensile simulation test on the finite element model of the ductile copper alloy test piece, and generating the simulated load-displacement curve; if the second curve data after the necking point in the test load-displacement curve is inconsistent with the third curve data after the necking point in the simulated load-displacement curve, adjusting the second constitutive parameter of the ductile copper alloy, and determining the second constitutive parameter of the ductile copper alloy when the second curve data is consistent with the third curve data.

[0110] In an alternative embodiment of the present application, the evaluation of the load-bearing strength of the thrust chamber constructed of the ductile copper alloy based on the first constitutive parameter and the second constitutive parameter includes: under given working conditions, conducting a load test on the thrust chamber model constructed based on the first constitutive parameter and the second constitutive parameter to determine the model stress-strain curve of the inner wall of the thrust chamber model; determining the maximum strain of the inner wall of the thrust chamber model according to the model stress-strain curve; and evaluating the load-bearing strength of the thrust chamber constructed of the ductile copper alloy based on the maximum strain of the inner wall of the thrust chamber model and the ultimate fracture strain of the ductile copper alloy.

[0111] In an alternative embodiment of the present application, the model stress-strain curve is represented by the following formula:

[0112]

[0113] wherein, σ represents the stress data of the ductile copper alloy; σ u represents the stress data corresponding to the necking point; ε p represents the plastic strain tensor; represents the plastic strain component corresponding to the necking point; F represents the hardening modulus; n represents the second constitutive parameter; ε f represents the ultimate fracture strain of the ductile copper alloy.

[0114] In an alternative embodiment of the present application, the ultimate fracture strain of the ductile copper alloy is determined by the following formula:

[0115]

[0116] wherein, ε f represents the ultimate fracture strain of the ductile copper alloy; represents the reduction of area of the ductile copper alloy.

[0117] The above device embodiment provided in this embodiment and the method embodiment of the present application belong to the same inventive concept, and can execute the evaluation method for the load-bearing strength of the inner wall of the thrust chamber provided in any of the above embodiments of the present application, and has the corresponding functional modules and beneficial effects for executing the evaluation method for the load-bearing strength of the inner wall of the thrust chamber. For the technical details not described in detail in this embodiment, reference may be made to the specific processing content of the evaluation method for the load-bearing strength of the inner wall of the thrust chamber provided in the above embodiments of the present application, which will not be elaborated herein.

[0118] This embodiment of the present application also provides an electronic device. Please refer to Figure 6 , Figure 6 which is a schematic structural diagram of an electronic device provided in an embodiment of the present application.

[0119] AsFigure 6 As shown, the electronic device includes:

[0120] A processor 210.

[0121] A memory 200 for storing executable instructions of the processor 210.

[0122] The processor 210 is configured to execute the evaluation method for the bearing strength of the inner wall of the thrust chamber disclosed in any of the above embodiments by running the instructions in the memory 200.

[0123] The processor 210, the memory 200, the communication interface 220, the input device 230, and the output device 240 are interconnected via a bus. Among them:

[0124] The bus may include a path for transmitting information between various components of the computer system.

[0125] The processor 210 may be a general-purpose processor, such as a general-purpose central processing unit (CPU), a microprocessor, etc., or an application-specific integrated circuit (ASIC), or one or more integrated circuits for controlling the execution of the program of the present invention. It may also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components.

[0126] The processor 210 may include a main processor, and may also include a baseband chip, a modem, etc.

[0127] The memory 200 stores a program for executing the technical solution of the present invention, and may also store an operating system and other critical services. Specifically, the program may include program code, and the program code includes computer operation instructions. More specifically, the memory 200 may include a read-only memory (ROM), other types of static storage devices that can store static information and instructions, a random access memory (RAM), other types of dynamic storage devices that can store information and instructions, a disk memory, a flash memory, etc.

[0128] The input device 230 may include a device for receiving data and information input by a user, such as a keyboard, a mouse, a camera, a scanner, a touch screen, etc.

[0129] The output device 240 may include a device for allowing information to be output to a user, such as a display screen, a printer, a speaker, etc.

[0130] The communication interface 220 may include a device such as any transceiver to communicate with other devices or communication networks, such as Ethernet, Radio Access Network (RAN), Wireless Local Area Network (WLAN), etc.

[0131] The processor 210 executes the programs stored in the memory 200 and calls other devices, which can be used to implement each step of any one of the methods for evaluating the bearing strength of the inner wall of the thrust chamber provided in the above embodiments of the present application.

[0132] In addition to the above methods and devices, the embodiments of the present application may also be a computer program product, which includes computer program instructions that cause the processor to execute the steps in the methods for evaluating the bearing strength of the inner wall of the thrust chamber in various embodiments of the present application when the computer program instructions are run by the processor.

[0133] The computer program product can be written in any combination of one or more programming languages for the program code to perform the operations of the embodiments of the present application. The programming languages include object-oriented programming languages such as Java, C++, etc., and also include conventional procedural programming languages such as the "C" language or similar programming languages. The program code can be executed completely on the user computing device, partially on the user device, executed as an independent software package, partially on the user computing device and partially on a remote computing device, or completely on a remote computing device or server.

[0134] In addition, the embodiments of the present application may also be a storage medium on which a computer program is stored, and the computer program is executed by the processor to perform the steps in the methods for evaluating the bearing strength of the inner wall of the thrust chamber in various embodiments of the present application.

[0135] For the foregoing method embodiments, for the sake of simple description, they are all expressed as a series of action combinations. However, those skilled in the art should know that the present application is not limited by the described action sequence, because according to the present application, certain steps can be in other sequences or performed simultaneously. Secondly, those skilled in the art should also know that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily essential to the present application.

[0136] It should be noted that each embodiment in this specification is described in a progressive manner. Each embodiment focuses on the differences from other embodiments. The same or similar parts among the embodiments can be referred to each other. For the device embodiments, since they are basically similar to the method embodiments, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiments.

[0137] The steps in the methods of the embodiments of the present application can be adjusted, combined, and deleted according to actual needs, and the technical features described in the embodiments can be replaced or combined.

[0138] In the devices and terminals in the embodiments of the present application, the modules and sub-modules can be combined, divided, and deleted according to actual needs.

[0139] In several embodiments provided by the present application, it should be understood that the disclosed terminals, devices, and methods can be implemented in other ways. For example, the terminal embodiments described above are only illustrative. For example, the division of modules or sub-modules is only a logical function division, and there can be other division methods in actual implementation. For example, multiple sub-modules or modules can be combined or integrated into another module, or some features can be ignored or not executed. Another point is that the displayed or discussed coupling or direct coupling or communication connection to each other can be through some interfaces, and the indirect coupling or communication connection of devices or modules can be in electrical, mechanical, or other forms.

[0140] The modules or sub-modules described as separate components may or may not be physically separated. The components as modules or sub-modules may or may not be physical modules or sub-modules, that is, they can be located in one place, or they can be distributed to multiple network modules or sub-modules. Some or all of the modules or sub-modules can be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0141] In addition, in each embodiment of the present application, the functional modules or sub-modules can be integrated in a processing module, or each module or sub-module can exist physically alone, or two or more modules or sub-modules can be integrated in one module. The above-mentioned integrated modules or sub-modules can be implemented in the form of hardware or in the form of software functional modules or sub-modules.

[0142] Those skilled in the art can further realize that the units and algorithm steps of each example described in combination with the embodiments disclosed in this article can be implemented by electronic hardware, computer software, or a combination of the two. To clearly illustrate the interchangeability of hardware and software, the composition and steps of each example have been generally described according to functions in the above description. Whether these functions are executed in a hardware or software manner depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered to exceed the scope of the present application.

[0143] The steps of the methods or algorithms described in connection with the embodiments disclosed herein may be implemented directly in hardware, in a software unit executed by a processor, or in a combination thereof. The software unit may be placed in a random access memory (RAM), internal memory, read-only memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, a removable disk, a CD-ROM, or any other form of storage medium well known in the art.

[0144] Finally, it should also be noted that in this document, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variation thereof is intended to cover a non-exclusive inclusion, such that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not expressly listed, or elements inherent to such process, method, article or device. Without further limitation, an element defined by the phrase "comprising a..." does not exclude the presence of additional identical elements in the process, method, article or device comprising the element.

[0145] The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Thus, the present application is not intended to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An evaluation method for the bearing strength of the inner wall of a thrust chamber, characterized in that including: obtaining a test load-displacement curve and a test engineering stress-strain curve of a ductile copper alloy test piece; determining a first constitutive parameter of the ductile copper alloy according to the test engineering stress-strain curve; performing a tensile simulation test on a finite element model of the ductile copper alloy test piece, and determining a second constitutive parameter of the ductile copper alloy when a simulated load-displacement curve generated by the tensile simulation test is consistent with the test load-displacement curve; evaluating the load-bearing strength of a thrust chamber constructed of the ductile copper alloy based on the first constitutive parameter and the second constitutive parameter.

2. The evaluation method for the load-bearing strength of the inner wall of the thrust chamber according to claim 1, characterized in that The determining a first constitutive parameter of the ductile copper alloy according to the test engineering stress-strain curve includes: determining first curve data in the test engineering stress-strain curve before the necking point; determining the first constitutive parameter of the ductile copper alloy according to the first curve data.

3. The evaluation method for the bearing strength of the inner wall of the thrust chamber according to claim 2, characterized in that, The first constitutive parameter includes: an initial yield stress of the ductile copper alloy, a maximum hardening amount of the yield surface, and a hardening parameter; The first curve data of the test engineering stress-strain curve is represented by the following formula: Among them, σ represents the stress data of the ductile copper alloy; σ0 represents the initial yield stress; Q ∞ represents the maximum hardening amount of the yield surface; b represents the hardening parameter; represents the equivalent plastic strain; ε p represents the plastic strain tensor.

4. The evaluation method for the load-bearing strength of the inner wall of the thrust chamber according to claim 1, characterized in that, The performing a tensile simulation test on a finite element model of the ductile copper alloy test piece, and determining a second constitutive parameter of the ductile copper alloy when a simulated load-displacement curve generated by the tensile simulation test is consistent with the test load-displacement curve includes: performing a tensile simulation test on a finite element model of the ductile copper alloy test piece in combination with the first constitutive parameter to generate the simulated load-displacement curve; if second curve data after the necking point in the test load-displacement curve is inconsistent with third curve data after the necking point in the simulated load-displacement curve, adjusting the second constitutive parameter of the ductile copper alloy, and determining the second constitutive parameter of the ductile copper alloy when the second curve data is consistent with the third curve data.

5. The evaluation method for the load-bearing strength of the inner wall of the thrust chamber according to claim 1, characterized in that, The evaluating the load-bearing strength of a thrust chamber constructed of the ductile copper alloy based on the first constitutive parameter and the second constitutive parameter includes: under given working condition conditions, performing a load test on a thrust chamber model constructed based on the first constitutive parameter and the second constitutive parameter, and determining a model stress-strain curve of the inner wall of the thrust chamber model; determining a maximum strain of the inner wall of the thrust chamber model according to the model stress-strain curve; evaluating the load-bearing strength of a thrust chamber constructed of the ductile copper alloy based on the maximum strain of the inner wall of the thrust chamber model and the ultimate fracture strain of the ductile copper alloy.

6. The evaluation method for the load-bearing strength of the inner wall of the thrust chamber according to claim 5, characterized in that, The model stress-strain curve is represented by the following formula: Among them, σ represents the stress data of the ductile copper alloy; σ u represents the stress data corresponding to the necking point; ε p represents the plastic strain tensor; represents the plastic strain component corresponding to the necking point; F represents the hardening modulus; n represents the second constitutive parameter; ε f represents the ultimate fracture strain of the ductile copper alloy.

7. The evaluation method for the load-bearing strength of the inner wall of the thrust chamber according to claim 5, wherein, The ultimate fracture strain of the ductile copper alloy is determined by the following formula: Among them, ε f represents the ultimate fracture strain of the ductile copper alloy; represents the reduction of area of the ductile copper alloy.

8. An evaluation device for the bearing strength of the inner wall of a thrust chamber, characterized in that, including: a test data acquisition unit for obtaining a test load-displacement curve and a test engineering stress-strain curve of a ductile copper alloy test piece; a first curve analysis unit for determining a first constitutive parameter of the ductile copper alloy according to the test engineering stress-strain curve; A second curve analysis unit, configured to perform a tensile simulation test on the finite element model of the ductile copper alloy, and determine the second constitutive parameters of the ductile copper alloy when the simulated load-displacement curve generated by the tensile simulation test is consistent with the test load-displacement curve; A thrust chamber evaluation unit, configured to evaluate the load-bearing strength of a thrust chamber constructed of the ductile copper alloy based on the first constitutive parameters and the second constitutive parameters.

9. An electronic device, characterized in that, Comprising: A processor; A memory for storing instructions executable by the processor; The processor is configured to execute the method for evaluating the load-bearing strength of the inner wall of the thrust chamber according to any one of claims 1 to 7 by running the instructions in the memory.

10. A computer storage medium, characterized in that, Instructions are stored in the computer storage medium, and when the instructions are run, the method for evaluating the load-bearing strength of the inner wall of the thrust chamber according to any one of claims 1 to 7 is implemented.

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