Stainless steel rocket storage tank cylinder section forming method, device, equipment and medium

Abstract

The invention relates to the technical field of machine manufacturing, and provides a stainless steel rocket storage tank barrel section forming method, device, equipment and medium, the method comprises the steps that an X-ray diffraction test is conducted on a sample, and the martensite volume fraction and dislocation density are obtained based on an obtained diffraction curve; constructing a first function based on the martensite volume fraction, the corresponding environmental parameters and the deformation amount of the deformed sample; obtaining yield strength according to the dislocation density, and constructing a quantitative model according to the yield strength and a first function; and actual operation parameters are obtained and input into the quantitative model, corresponding optimal operation parameters are obtained, and the rocket tank cylinder section is manufactured. According to the method, the base metal and the welding seam are deformed at the same time by adopting the obtained optimal operation parameters such as low-temperature parameters to conduct a low-temperature deformation method, so that the base metal and the welding seam are both subjected to deformation strengthening, the joint strength coefficient of the cylinder section welding seam is improved, the integrity and reliability of the component structure are improved, resource waste is reduced, and the production efficiency is remarkably improved; and the comprehensive performance of the rocket tank is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of mechanical manufacturing, in particular to a stainless steel rocket tank cylinder segment forming method, device, equipment and medium. BACKGROUND

[0002] In recent years, with the increasing demand for deep space exploration, satellite networking, moon exploration and fire exploration in China, the launch frequency and effective payload of the carrier rocket are required to be greatly improved, calling for the development of the next generation of high carrying capacity, reusable and low cost rockets. Improving the structural strength of the rocket, reducing the manufacturing cost and improving the production efficiency have become the key direction of the current aerospace technology innovation.

[0003] Currently, although aluminum alloy has superior performance as a traditional material for rocket body structure, it has limitations such as high production cost, low processing efficiency, complex assembly and difficulty in large-scale manufacturing, which restricts the further development of aerospace technology. In contrast, stainless steel, with its low production and processing cost, wide service temperature range, excellent fatigue performance and relatively simple manufacturing process, has gradually become the preferred material for the next generation of rocket body structure.

[0004] In the prior art, the cylinder segment is one of the important structures of the rocket tank, which has a thin-walled cylindrical structure. The existing forming method is to bend a flat plate into a wall plate, and then weld multiple wall plates into a cylinder segment. However, the density of stainless steel itself is relatively high, and the specific strength of the solid solution state plate material is significantly lower than that of traditional aluminum alloy. Although the semi-hard state stainless steel has high strength, it lacks ductility and is difficult to meet the forming requirements of complex-shaped components of the rocket, resulting in that the rocket tank cylinder segment has low specific strength of solid solution state stainless steel plate material and low deformation capacity of hardened state stainless steel plate material during manufacturing, which leads to weak work hardening enhancement effect and cannot meet the processing requirements of complex shapes; the joint coefficient of hardened state plate material is low, a large amount of reinforcing structure is needed, which greatly increases the total weight of the rocket. At the same time, the stainless steel tank adopts tailor-welded forming, which has low integrity, resulting in reduced reusability. SUMMARY

[0005] The present application aims to solve at least one of the above technical problems.

[0006] To solve the above problems, the present application provides a stainless steel rocket tank cylinder segment forming method, device, equipment and medium.

[0007] In a first aspect, the present application provides a stainless steel rocket tank cylinder segment forming method, comprising: X-ray diffraction test is performed on the deformed sample after pretreatment under different environmental parameters, and the volume fraction of martensite and the dislocation density are obtained based on the obtained diffraction curve; A first function is constructed based on the volume fraction of martensite, the corresponding environmental parameter and the deformation amount of the deformed sample; According to the dislocation density, a yield strength is obtained, and a quantitative model is constructed according to the yield strength and the first function; An actual operation parameter is input into the quantitative model to obtain corresponding optimal operation parameters, wherein the actual operation parameter includes an actual temperature and an actual deformation amount, and the optimal operation parameters include an optimal deformation amount corresponding to the actual temperature and an optimal temperature corresponding to the actual deformation amount; A rocket tank cylinder segment is manufactured according to the optimal operation parameters.

[0008] Optionally, the first function is constructed based on the martensite volume fraction, the corresponding environmental parameter and the deformation amount of the deformation sample, and the first function includes: The first function is expressed by a first formula, and the first formula includes: , wherein f α̍ T represents the martensite volume fraction when the environmental parameter T is T, f s T represents the martensite volume fraction when the environmental parameter T is T, β T represents the fitting parameter when the environmental parameter T is T, and ε represents the deformation amount.

[0009] Optionally, the yield strength includes an austenite yield strength and a martensite yield strength, and the quantitative model is constructed according to the yield strength and the first function, and the method includes: A difference between a preset value and the martensite volume fraction is obtained, and a first value is obtained according to a product of the difference and the austenite yield strength; A second value is obtained according to a product of the martensite yield strength and the martensite volume fraction, wherein the martensite volume fraction is obtained according to the first function; The first value and the second value are summed to obtain the quantitative model.

[0010] Optionally, the quantitative model is expressed by a second formula, and the second formula includes: = (1-f α̍ T ) + f α̍ T =f(T,ε), wherein represents the yield strength when the environmental parameter T is T, represents the martensite yield strength when the environmental parameter T is T, The austenite yield strength when the environmental parameter T is represented, and f(T, ε) represents a relationship function between the yield strength and the environmental parameter T and the deformation amount.

[0011] Optionally, the manufacturing of the rocket tank cylinder segment according to the optimal operation parameter comprises: Obtaining the cylinder blank diameter according to the actual deformation amount or the optimal deformation amount; Obtaining the material according to the cylinder blank diameter, and performing a forming process on the material to obtain a cylinder blank part; Obtaining the initial yield stress and the film-attaching pressure of the cylinder blank part, and placing the cylinder blank part into a low-temperature bulging die, and pre-cooling according to the initial yield stress and the film-attaching pressure, and bulging to completely attach the film; Obtaining the rocket tank cylinder segment by removing the process segment after the cylinder blank part is expanded.

[0012] Optionally, the obtaining of the martensite volume fraction and the dislocation density based on the obtained diffraction curve comprises: Obtaining the martensite volume fraction according to the integral intensity of the diffraction peak of the martensite phase and the integral intensity of the diffraction peak of the austenite phase in the diffraction curve.

[0013] Optionally, the obtaining of the martensite volume fraction and the dislocation density based on the obtained diffraction curve comprises: Obtaining the half-height width characteristics of the austenite phase and the martensite phase in the diffraction curve respectively, and obtaining the first diffraction vector variation and the first diffraction vector of the austenite phase crystal face and the second diffraction vector variation and the second diffraction vector of the martensite phase crystal face according to the half-height width characteristics; Obtaining the austenite curve slope according to the first diffraction vector variation and the first diffraction vector based on the diffraction vector variation and the dislocation density variation relationship, and obtaining the martensite curve slope according to the second diffraction vector variation and the second diffraction vector; Obtaining the austenite dislocation density according to the austenite curve slope, and obtaining the martensite dislocation density according to the martensite curve slope.

[0014] In a second aspect, the present application provides a stainless steel rocket tank cylinder segment forming device, comprising: A test module is configured to perform X-ray diffraction testing on the pretreated deformation sample under different environmental parameters, and obtain the martensite volume fraction and the dislocation density based on the obtained diffraction curve; A generation module is configured to construct a first function based on the martensite volume fraction, the corresponding environmental parameter and the deformation amount of the deformation sample; A construction module is configured to obtain the yield strength according to the dislocation density, and construct a quantitative model according to the yield strength and the first function; An execution module is configured to input actual operation parameters into the quantitative model to obtain corresponding optimal operation parameters, wherein the actual operation parameters include an actual temperature and an actual deformation amount, and the optimal operation parameters include an optimal deformation amount corresponding to the actual temperature and an optimal temperature corresponding to the actual deformation amount. A manufacturing module is configured to manufacture a rocket tank cylinder segment according to the optimal operation parameters.

[0015] In a third aspect, the present application provides an electronic device including a memory and a processor. The memory is configured to store a computer program. The processor is configured to implement the stainless steel rocket tank cylinder segment forming method according to the first aspect when executing the computer program.

[0016] In a fourth aspect, the present application provides a computer readable storage medium having a computer program stored thereon, and the computer program, when executed by a processor, implements the stainless steel rocket tank cylinder segment forming method according to the first aspect.

[0017] The stainless steel rocket tank cylinder segment forming method has the following advantages: by performing X-ray diffraction tests on deformation samples at different temperatures and deformation amounts, diffraction curves are obtained, and the volume fraction of martensite and the dislocation density are calculated, thereby accurately quantifying the microstructure characteristics during low-temperature deformation of stainless steel and providing reliable data basis for establishing the correlation between microstructure and macroscopic performance. A first function is constructed based on the volume fraction of martensite, deformation temperature and deformation amount, which quantitatively describes the evolution law of the martensite phase change with process parameters, and can directly guide the control of the volume fraction of martensite by adjusting the temperature and deformation amount, thereby improving the strength while ensuring the deformation capacity, and breaking through the limitations of traditional solid solution state stainless steel with low specific strength and hardening state stainless steel with poor deformation capacity. The yield strength is calculated by the dislocation density, and a quantitative model is constructed by combining the first function, thereby accurately correlating the yield strength with the operation parameters, providing a theoretical basis for optimizing the process to reduce the strength difference between the weld and the base material, avoiding excessive reinforcement to reduce the weight, and comprehensively optimizing the operation parameters. By inputting the actual operation parameters into the quantitative model, the optimal operation parameters are quickly output, and the rocket tank cylinder segment is manufactured according to the optimal operation parameters (such as low-temperature parameters, etc. to perform a low-temperature forming method), so that the base material and the weld are deformed at the same time, the base material and the weld are both deformed and strengthened, the joint strength coefficient of the weld of the cylinder segment is improved, the overall structure of the component structure is improved, the resource waste caused by blind tests is reduced, the production efficiency is significantly improved, the operation parameters and the yield strength are accurately matched, the size precision of the cylinder segment after forming is high, the overall performance is uniform, the structural weak points caused by splicing are reduced, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of 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cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is improved, the overall performance of the cylinder segment is 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[0018] Figure 1 Flow chart of the method for forming a stainless steel rocket tank cylinder segment according to an embodiment of the present application; Figure 2 Flow chart of the method for manufacturing a rocket tank cylinder segment according to optimal operating parameters according to an embodiment of the present application; Figure 3 Flow chart of the method for manufacturing a rocket tank cylinder segment according to optimal operating parameters according to an embodiment of the present application; Figure 4 Structure diagram of the device for forming a stainless steel rocket tank cylinder segment according to an embodiment of the present application; Figure 5 Structure diagram of the electronic device according to an embodiment of the present application. DETAILED DESCRIPTION

[0019] In order to make the above objectives, characteristics and advantages of the present application more obvious and easy to understand, the specific embodiments of the present application will be described in detail below with reference to the drawings. Although some embodiments of the present application are shown in the drawings, it should be understood that the present application can be implemented in various forms, and should not be interpreted as being limited to the embodiments described herein, on the contrary, these embodiments are provided to make the present application more thorough and complete. It should be understood that the drawings and embodiments of the present application are only for exemplary purposes, and are not intended to limit the scope of protection of the present application.

[0020] It should be understood that each step described in the method embodiments of the present application can be performed in different order and / or in parallel. In addition, the method embodiments can include additional steps and / or omit the steps shown. The scope of the present application is not limited in this respect.

[0021] The term "comprising" and variations thereof as used herein are open-ended, that is "including, but not limited to"; the term "based on" is "based, at least in part, on"; the term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments"; the term "optionally" means "optional embodiments". Related definitions will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in the present application are only used to distinguish different devices, modules or units, and are not intended to limit the order or interdependence of the functions performed by these devices, modules or units.

[0022] It should be noted that the modification of "one" or "multiple" mentioned in the present application is illustrative and not limiting, and those skilled in the art should understand that, unless otherwise explicitly indicated in the context, it should be understood as "one or more".

[0023] The names of the messages or information exchanged between the plurality of devices in the embodiments of the present application are only for illustrative purposes, and are not intended to limit the scope of the messages or information.

[0024] To solve the problems in the related art, the present embodiment provides a stainless steel rocket tank cylinder segment forming method, device, equipment and medium.

[0025] As shown in the figure, the stainless steel rocket tank cylinder segment forming method provided by the present embodiment comprises: Figure 1 Step S1, X-ray diffraction test is performed on the pretreated deformation sample under different environmental parameters, and the martensite volume fraction and dislocation density are obtained based on the obtained diffraction curve. Specifically, before constructing the quantitative model, a data set required for fitting the quantitative model should be constructed. First, the sample needs to be pretreated. The sample can be a solid solution, a hardened state or a rolled reinforced state stainless steel plate. According to the standard of, for example, GB / T228.1, the sample is pretreated on the stainless steel plate, for example, a tensile sample is cut to obtain a deformation sample, which is used as a basic sample for subsequent data set acquisition. The tensile sample is subjected to low temperature tensile deformation under different environmental parameters, for example, the temperature parameter can be in the temperature range of 25℃ to -196℃, with liquid nitrogen, liquid oxygen or liquid helium as the cooling medium, at a temperature interval of 10℃, under the condition of 0-30% variable range and 5% variable interval, to obtain deformation samples under different temperatures and deformation amounts, and record the corresponding deformation temperature and deformation amount. Then, the uniform deformation region of the deformation sample is sampled, and the sample is subjected to X-ray diffraction (XRD) test, the diffraction curve is recorded, and the martensite volume fraction and dislocation density under the corresponding environmental parameters can be obtained based on the curve.

[0026] Optionally, the martensite volume fraction and dislocation density obtained based on the obtained diffraction curve comprises:

[0027] The martensite volume fraction is obtained according to the integral intensity of the martensite phase crystal face diffraction peak and the integral intensity of the austenite phase crystal face diffraction peak. The formula is as follows: , , Wherein, f αʹ represents the martensite volume fraction, represents the integral intensity of the j crystal face diffraction peak of the martensite phase, which can be directly obtained from the diffraction curve, such as the integral intensity of the martensite phase crystal area, including γ(111), γ(200), γ(220), represents the integral intensity of the j crystal face diffraction peak of the austenite phase, which can be directly obtained from the diffraction curve, such as the integral intensity of the austenite phase crystal area, includinga' (110), a' (200), a' (211)。

[0028] The dislocation density can be calculated by the following formula: , wherein, p represents the dislocation density, m represents the slope of the fitting curve, which is calculated based on the parameters obtained in the diffraction curve, M represents the dislocation contribution constant, which is 2, b represents the Burgers vector, which is 0.252 mm when corresponding to the martensite, and 0.254 mm when corresponding to the austenite. When the slope m of the corresponding fitting curve is calculated according to the relevant parameters of the martensite phase crystal face, the martensite dislocation density p is obtained by bringing the above formula αʹ When the slope m of the corresponding fitting curve is calculated according to the relevant parameters of the austenite phase crystal face, the austenite dislocation density p is obtained by bringing the above formula γʹ .

[0029] By accurately measuring the martensite volume fraction and dislocation density of the deformed sample at different temperatures and deformation amounts, key data support is provided for subsequent establishment of the relationship between material performance and process parameters, which helps to deeply understand the microstructure change rule of the stainless steel in the low-temperature deformation process, thereby laying a foundation for optimizing the cylinder segment forming process.

[0030] Step S2, constructing a first function based on the martensite volume fraction, the corresponding environmental parameter and the deformation amount of the deformed sample.

[0031] Specifically, the martensite volume fraction obtained at different temperatures and deformation amounts is taken as the data basis, the fitting parameters at different temperatures and the martensite volume fraction are determined through fitting analysis of a large amount of data, and thus the functional relationship between the martensite volume fraction and the deformation temperature and the deformation amount is constructed, which can quantitatively describe the change rule of the martensite volume fraction with the deformation temperature and the deformation amount, provides a mathematical model for further analyzing the relationship between material performance and process parameters, and facilitates subsequent control of the martensite volume fraction by adjusting the deformation temperature and the deformation amount, so as to realize the regulation and control of the material performance.

[0032] Optionally, the constructing a first function based on the martensite volume fraction, the corresponding environmental parameter and the deformation amount of the deformed sample comprises: The first function is represented by a first formula, and the first formula comprises: , wherein, f α̍ T represents the martensite volume fraction when the environmental parameter T is T, f s Ta martensite volume fraction at the environmental parameter T, β T a fitting parameter at the environmental parameter T, ε represents the deformation amount.

[0033] Step S3, obtaining a yield strength according to the dislocation density, and constructing a quantitative model according to the yield strength and the first function.

[0034] Specifically, based on the obtained martensite dislocation density and austenite dislocation density, the following formula is used for representation: , , wherein, a martensite yield strength, an austenite yield strength, ρ T αʹ a martensite dislocation density at the environmental parameter (such as temperature) T, ρ T γʹ an austenite dislocation density at the environmental parameter (such as temperature) T.

[0035] According to the first function and the relationship between the dislocation density and the yield strength, the relationship between the yield strength and the temperature and the deformation amount is established, and a quantitative model is obtained.

[0036] Optionally, the yield strength includes an austenite yield strength and a martensite yield strength; and the constructing a quantitative model according to the yield strength and the first function includes: obtaining a difference value between a preset numerical value and the martensite volume fraction, and obtaining a first numerical value according to a product of the difference value and the austenite yield strength, obtaining a second numerical value according to a product of the martensite yield strength and the martensite volume fraction, wherein the martensite volume fraction is obtained according to the first function.

[0037] summing the first numerical value and the second numerical value to obtain the quantitative model.

[0038] Optionally, the quantitative model is represented by a second formula, and the second formula includes: = (1-f α̍ T ) + f α̍ T =f(T,ε), wherein, the yield strength at the environmental parameter T, the martensite yield strength at the environmental parameter T, the austenite yield strength at the environmental parameter T, f(T, ε) representing a function of the yield strength with respect to the environmental parameter T and the deformation amount.

[0039] The established quantitative model links the martensite volume fraction, dislocation density and yield strength, and can accurately predict the yield strength of the material under different process parameters, providing a theoretical basis for determining the optimal forming process parameters, and helping to improve the strength and performance uniformity of the stainless steel rocket tank cylinder segment.

[0040] Step S4, inputting the actual operation parameters into the quantitative model to obtain the corresponding optimal operation parameters, wherein the actual operation parameters include actual temperature and actual deformation amount, and the optimal operation parameters include optimal deformation amount corresponding to the actual temperature and optimal temperature corresponding to the actual deformation amount.

[0041] Specifically, in actual production, actual operation parameters such as a given target yield strength index, actual temperature or actual deformation amount are obtained. The actual temperature is substituted into the quantitative model to obtain the optimal deformation amount corresponding thereto, or the actual deformation amount is substituted into the quantitative model to obtain the optimal temperature corresponding thereto. For example, given the actual processing temperature, it is substituted into the quantitative model, and the minimum deformation amount satisfying the target yield strength index is found through numerical calculation or drawing analysis, which is the optimal deformation amount; conversely, given the actual deformation amount, the minimum temperature satisfying the target yield strength index is obtained by substituting it into the model, which is the optimal temperature.

[0042] By inputting the actual operation parameters into the quantitative model to obtain the optimal operation parameters, the optimal deformation temperature and deformation amount combination can be quickly determined according to the actual production conditions, avoiding the problems of resource waste and low production efficiency caused by blind attempts of different process parameters, improving the accuracy and efficiency of production, and ensuring that the produced cylinder segment meets the design strength requirements.

[0043] Step S5, manufacturing the rocket tank cylinder segment according to the optimal operation parameters.

[0044] Specifically, the rocket tank can be subjected to operations such as blanking according to the optimal operation parameters, for example, the cylinder blank diameter is calculated according to the optimal deformation amount and blanking is performed, and then welding forming, low temperature expansion and other operations are performed to obtain the required rocket tank cylinder segment.

[0045] In the present embodiment, by performing X-ray diffraction tests on the deformed samples at different temperatures and deformation amounts, diffraction curves are obtained and the martensite volume fraction and dislocation density are calculated, thereby realizing accurate quantification of the microstructure characteristics during low-temperature deformation of the stainless steel, and providing a reliable data basis for subsequent establishment of the correlation between the microstructure and the macroscopic performance. A first function is constructed based on the martensite volume fraction, the deformation temperature and the deformation amount, which quantitatively describes the evolution law of the martensite phase transformation with the process parameters, and can directly guide the control of the martensite volume fraction by adjusting the temperature and the deformation amount, so as to improve the strength while ensuring the deformation ability, thereby breaking through the limitations of the traditional solid solution state stainless steel with low specific strength and the hardening state stainless steel with poor deformation ability. The yield strength is calculated by the dislocation density, and a quantitative model is constructed by combining the first function, thereby realizing accurate correlation between the yield strength and the operating parameters, providing a theoretical basis for optimizing the process to reduce the strength difference between the weld and the base material, and avoiding the weight increase caused by excessive reinforcement, and comprehensively optimizing the operating parameters. By inputting the actual operating parameters into the quantitative model, the optimal operating parameters are quickly output, and the rocket tank cylinder segment is manufactured according to the optimal operating parameters (such as low-temperature parameters, etc. to perform a low-temperature forming method), so that the base material and the weld are deformed at the same time, the base material and the weld are both deformed and strengthened, the joint strength coefficient of the weld of the cylinder segment is improved, the integrity and reliability of the component structure are improved, the resource waste caused by blind test is reduced, the production efficiency is significantly improved, and meanwhile, the accurate matching between the operating parameters and the yield strength is ensured, so that the size precision of the cylinder segment after forming is high, the overall performance is uniform, the structural weak points caused by splicing are reduced, the integrity and reusability of the cylinder segment are improved, the requirements of the next generation of rockets on structural reliability are met, and the comprehensive performance of the rocket tank is improved.

[0046] Optionally, as shown in Figure 2 manufacturing the rocket tank cylinder segment according to the optimal operating parameters comprises: The cylinder blank diameter is obtained according to the actual deformation amount or the optimal deformation amount.

[0047] Specifically, the deformation amount in the operating parameters is used to obtain the cylinder blank diameter of the rocket tank cylinder segment. That is, the cylinder blank diameter is first calculated according to the optimal deformation amount or the actual deformation amount according to the following formula: , wherein ε represents the optimal deformation amount or the actual deformation amount, D0 represents the cylinder blank diameter, and D1 represents the target cylinder segment diameter.

[0048] The cylinder blank size is accurately calculated through the quantitative relationship between the deformation amount and the diameter, so that the cylinder blank can exactly reach the target cylinder segment diameter after subsequent expansion, the waste rate caused by size deviation is avoided, and the problem of low size precision caused by traditional experience-based blanking is solved, thereby laying a foundation for subsequent forming quality.

[0049] The blank is cut to obtain material according to the diameter of the cylindrical blank, and the material is then formed to obtain the cylindrical blank part.

[0050] Specifically, such as Figure 2 As shown in (a) and (b), stainless steel plates (such as 304, 316L, etc.) are selected according to the diameter of the cylindrical blank. Laser cutting or plasma cutting technology is used to cut the material. The material can be a rectangular stainless steel plate or multiple rectangular stainless steel plates. The cut rectangular plates are rolled into a cylindrical shape by, for example, a CNC bending machine. Then, the longitudinal joints are welded by, for example, laser welding or argon arc welding technology. After welding, the weld beads are removed by grinding to obtain the cylindrical blank part.

[0051] Obtain the initial yield stress and film-applying pressure of the cylindrical blank part, place the cylindrical blank part into a low-temperature bulging mold, and pre-cool it according to the optimal temperature corresponding to the actual deformation amount or the actual temperature corresponding to the optimal deformation amount, the initial yield stress and the film-applying pressure, and bulge it at low temperature until it is fully molded.

[0052] Specifically, the initial yield stress can be expressed by the following formula: , Where p represents the yield stress, t represents the slab thickness, and σ s T This represents the yield strength of the slab at temperature T.

[0053] The film application pressure can be expressed using the following formula: , Where, p ’ The pressure of the film application is represented by r, which represents the minimum fillet radius of the mold, and σ represents the pressure of the film application. i T This indicates the tensile strength of the slab at temperature T.

[0054] like Figure 2 As shown in (c), after obtaining the above operating parameters, the cylindrical blank part is placed into the matching low-temperature bulging mold, and pre-cooled according to the above-obtained optimal temperature or actual temperature, initial yield stress and film-applying pressure, and then bulged at low temperature until fully film-applied.

[0055] After removing the expanded cylindrical blank part, the process section is cut off to obtain the rocket storage tank section.

[0056] Specifically, after the bulging process is completed, the pressure is slowly released and the mold is opened. The cylindrical blank part that fits the mold is removed, and the process sections at both ends of the blank (i.e., the clamping parts during bulging) are removed by plasma cutting. Then, the cut surfaces are ground and deburred to finally obtain a rocket propellant tank section that meets the design dimensions and quality. Figure 2 As shown in (d).

[0057] Additionally, the stainless steel rocket tank cylinder segment forming method of the present embodiment can also be applied to a stainless steel rocket tank cone segment forming method, as shown in FIG. 6, wherein Figure 3 (a) is the material after blanking according to the cone blank diameter, Figure 3 (b) is the cone blank part after forming treatment of the material, Figure 3 (c) is the cone blank part after pre-cooling, low-temperature bulging and film pasting, Figure 3 (d) is the cone segment rocket tank after the process segment is cut off. Figure 3

[0058] Optionally, the obtaining of the martensite volume fraction and the dislocation density based on the obtained diffraction curve comprises: respectively obtaining the half-height width characteristics of the austenite phase and the martensite phase in the diffraction curve, and obtaining the first diffraction vector variation and the first diffraction vector of the austenite phase crystal face and the first diffraction vector variation and the first diffraction vector of the martensite phase crystal face according to the half-height width characteristics.

[0059] Specifically, the diffraction vector variation and the diffraction vector can be calculated by the following formula: , , wherein, △K represents the diffraction vector variation, β represents the half-height width characteristic of each mirror surface diffraction peak (obtained according to the diffraction curve), θ represents the Bragg reflection angle (obtained according to the diffraction curve), for example, γ(111), γ(200), γ(220) are 22°, 25°, 37° respectively, α'(110), α'(200), α'(211) are 22°, 32°, 41° respectively, and λ represents the incident wave wavelength of the X-ray diffraction test, which is 0.15406 nm.

[0060] The half-height width characteristics of the austenite phase are brought into the above formula, and the corresponding first diffraction vector variation and the first diffraction vector are obtained, and the half-height width characteristics of the martensite phase are brought into the above formula, and the corresponding second diffraction vector variation and the second diffraction vector are obtained.

[0061] Based on the relationship between the diffraction vector variation and the dislocation density, the austenite curve slope is obtained according to the first diffraction vector variation and the first diffraction vector, and the martensite curve slope is obtained according to the second diffraction vector variation and the second diffraction vector.

[0062] Specifically, the relationship between the diffraction vector variation and the dislocation density can be represented by the following formula: , ​Wherein, d represents the average grain size, b represents the Burgers vector, the martensite corresponds to 0.252 mm, the austenite corresponds to 0.254 mm, M represents the dislocation contribution constant, the value is 2, and C represents the average dislocation factor, the value for stainless steel is 0.266. The corresponding curve slope can be obtained by data fitting.

[0063] The first diffraction vector change and the first diffraction vector are brought into the above formula, and the austenite curve slope can be obtained by derivation. The second diffraction vector change and the second diffraction vector are brought into the above formula, and the martensite curve slope can be obtained by derivation.

[0064] The austenite dislocation density is obtained according to the austenite curve slope, and the martensite dislocation density is obtained according to the martensite curve slope.

[0065] Specifically, after obtaining the curve slope, the austenite dislocation density and the martensite dislocation density can be calculated respectively by using the dislocation density calculation formula.

[0066] In order to further understand the invention content, characteristics and effects of the present application, the following specific embodiments are given: Embodiment 1 In this embodiment, 304L stainless steel is used, and the specific material is a solid solution state 304L stainless steel cold rolled sheet with a thickness of 2 mm. The laser welding parameters of the cylinder segment are as follows: welding speed 1 m / min, input power 1700 W, and weld gap less than 0.1 mm; the cylinder blank diameter is 500 mm, containing 1 weld. The yield strength of the formed cylinder segment is required to be greater than 1200 MPa, the residual stress is required to be less than 0.1 MPa, and the forming precision is required to be less than 2 mm.

[0067] The specific steps are as follows: Step S1, X-ray diffraction test is performed on the pretreated deformed sample under different environmental parameters, and the martensite volume fraction and dislocation density are obtained based on the obtained diffraction curve.

[0068] Specifically, standard sample low temperature tensile test. The uniaxial tensile sample is taken on the stainless steel flat plate, and the size of the sample is processed according to the national standard GB / T228.1. Then the 304L stainless steel sample is subjected to uniaxial tensile deformation in a temperature control box, and the test temperature range is 25℃~-196℃ (cooling medium is liquid nitrogen) or 25℃~-185℃ (cooling medium is liquid oxygen) or 25℃~-269℃ (cooling medium is liquid helium), and the temperature interval is fixed. The strain range is 0~30%, and the interval is fixed. Each test is repeated multiple times. The sample is taken in the uniform deformation area, polished and polished, and the stress layer is removed; X-ray diffraction test, diffraction angle 30°~110°.

[0069] Step S2, a first function is constructed based on the martensite volume fraction, the corresponding environmental parameter and the deformation amount of the deformed sample: .

[0070] Step S3: Obtain the yield strength based on the dislocation density. The relationship between the austenite phase yield strength and temperature and deformation is as follows: The relationship between the yield strength of the martensite phase and temperature and deformation is as follows: .

[0071] A quantitative model is constructed based on the yield strength and the first function. .

[0072] Alternatively, the above relationship can also be written as Python code, and by inputting the yield strength, a variable model regarding temperature and deformation can be obtained.

[0073] Step S4: Obtain the actual operating parameters by inputting them into the quantitative model to obtain the corresponding optimal operating parameters.

[0074] Specifically, the diameter of the cylinder section is 500 mm, and the strength is 1200 MPa. Substituting the yield strength index of 1200 MPa and the actual temperature of -120℃ into the quantitative model, the optimal deformation amount of 15% is obtained.

[0075] Step S5: Manufacture the rocket propellant tank section according to the optimal operating parameters.

[0076] Specifically, based on the principle of cylinder bulging, the relationship between strain and diameter before and after bulging is obtained: ; Based on a cylinder section diameter of 500mm, the maximum diameter D0 of the cylinder section billet is: ; Therefore, for a cylindrical section with an outer diameter of 500m, the diameter of the cylindrical blank is 438mm, requiring a 1.378m long slab. This slab is then cut into a single piece of material, rolled into a circle, and laser-welded at the joints to obtain the cylindrical blank part. The initial yield stress of the cylindrical blank part is calculated as follows: ; Calculate the film application pressure for the cylindrical blank part: , Where t represents the slab thickness of 2mm, r represents the minimum fillet radius of the mold of 100mm, and σ i T This indicates that the slab strength at temperature T = -120℃ is 775 MPa, derived from... σ is calculated to be... s T This indicates that the yield strength of the slab at -120℃ is 350MPa, σ b TThe tensile strength of the slab at temperature T is 1200 MPa.

[0077] The cylinder blank part is placed into a low-temperature bulging mold, and a practical temperature of -120℃ is used as the processing temperature. The cylinder blank part is pre-cooled to an initial yield stress of 3.65 MPa and a film-attaching pressure of 15.5 MPa, and is low-temperature bulged to completely attach the film. Then, the cylinder blank part is taken out, and the process section is cut off, to obtain the super-high-strength stainless steel rocket tank cylinder section.

[0078] Embodiment 2 In this embodiment, 304L stainless steel is used, and the specific material is a cold-rolled thin plate of solution-treated 304L stainless steel with a thickness of 2 mm. The laser welding parameters of the cylinder section are as follows: a welding speed of 1 m / min, an input power of 1700 W, and a welding gap of less than 0.2 mm. The cylinder blank has a diameter of 10 m and contains 7 welds. The yield strength of the formed cylinder section is required to be greater than 1000 MPa, the residual stress is required to be less than 0.1 MPa, and the forming precision is required to be less than 2 mm.

[0079] The specific steps are as follows: Step S1, X-ray diffraction testing is performed on the pretreated deformed sample under different environmental parameters, and the martensite volume fraction and dislocation density are obtained based on the obtained diffraction curve.

[0080] Specifically, standard sample low-temperature tensile testing. A uniaxial tensile sample is taken from a stainless steel flat plate, and the size of the sample is processed according to the national standard GB / T228.1. Then, the 304L stainless steel sample is subjected to uniaxial tensile deformation in a temperature control box, and the test temperature range is 25℃~-196℃ (cooling medium is liquid nitrogen) or 25℃~-185℃ (cooling medium is liquid oxygen) or 25℃~-269℃ (cooling medium is liquid helium), and the temperature interval is fixed. The strain range is 0~30%, and the interval is fixed. Each test is repeated multiple times. The uniform deformation area is sampled, polished, and stress relieved; X-ray diffraction testing is performed at an angle of 30°~110°.

[0081] Step S2, a first function is constructed based on the martensite volume fraction, the corresponding environmental parameter, and the deformation amount of the deformed sample: .

[0082] Step S3, the yield strength is obtained according to the dislocation density, and the relationship between the yield strength of the austenite phase and the temperature and deformation amount is , and the relationship between the yield strength of the martensite phase and the temperature and deformation amount is .

[0083] A quantitative model is constructed according to the yield strength and the first function .

[0084] Additionally, the above relationship can also be written as python code, by inputting the yield strength, the variable model about temperature and deformation can be obtained.

[0085] Step S4, obtaining the actual operation parameter inputting the quantitative model, obtaining the corresponding optimal operation parameter.

[0086] Specifically, the diameter of the cylinder segment is 10 m, and the strength is 1000 MPa. The yield strength index 1000 MPa and the actual temperature-150℃ are substituted into the quantitative model to obtain the optimal deformation 13%.

[0087] Step S5, manufacturing the rocket tank cylinder segment according to the optimal operation parameter.

[0088] Specifically, the relationship between strain and diameter before and after bulging is obtained according to the bulging forming principle of the cylinder segment: ; According to the diameter of the cylinder segment 10000mm, the maximum diameter D0 of the cylinder blank is obtained: ; Therefore, for the cylinder segment with an outer diameter of 10 m, the diameter of the cylinder blank is 8.93 m, which requires a 28 m long plate blank, and 7 pieces of material are obtained after cutting, and then the plate blank is coiled and welded, and the joint is laser welded to obtain the cylinder blank part. The cylinder blank part can be coiled and welded by one plate, or spliced and welded by multiple plates.

[0089] The initial yield stress of the cylinder blank part is calculated: ; The film pressing pressure of the cylinder blank part is calculated: , Wherein, t represents the plate blank thickness 2mm, r represents the minimum fillet radius of the die 2000mm, σ i T represents the strength of the plate blank at temperature T=-150℃ 950MPa, σ calculated, σ s T represents the yield strength of the plate blank at temperature-150℃ 400MPa, σ b T represents the tensile strength of the plate blank at temperature T 1500MPa.

[0090] Put the cylinder blank part into the low temperature bulging die, apply the actual temperature-150℃ as the processing temperature, adopt the low temperature bulging process, precool the cylinder blank part according to the initial yield stress 0.18MPa and the film pressing pressure 0.95MPa, and low temperature bulging to completely adhere to the die. Then take out the cylinder blank part and cut off the process section to obtain the super high strength stainless steel rocket tank cylinder segment.

[0091] As Figure 4 shown in the figure, the embodiment of the present application provides a stainless steel rocket tank cylinder segment forming device 400, which comprises: a test module 410, configured to perform X-ray diffraction test on the pretreated deformed sample under different environmental parameters, and obtain martensite volume fraction and dislocation density based on the obtained diffraction curve; a generation module 420, configured to construct a first function based on the martensite volume fraction, the corresponding environmental parameter and the deformation amount of the deformed sample; a construction module 430, configured to obtain yield strength according to the dislocation density, and construct a quantitative model according to the yield strength and the first function; an execution module 440, configured to input the actual operation parameters into the quantitative model to obtain corresponding optimal operation parameters, wherein the actual operation parameters include actual temperature and actual deformation amount, and the optimal operation parameters include optimal deformation amount corresponding to the actual temperature and optimal temperature corresponding to the actual deformation amount; a manufacturing module 450, configured to manufacture a rocket tank cylinder segment according to the optimal operation parameters.

[0092] As Figure 5 shown in the figure, the embodiment of the present application provides an electronic device 500, comprising a memory 510 and a processor 520; the memory 510 is used to store a computer program; the processor 520 is used to realize the stainless steel rocket tank cylinder segment forming method as described above when executing the computer program.

[0093] Or, an electronic device 500 comprises a memory 510 and a processor 520 coupled to the memory 510; the memory 510 is configured to store a computer program; the processor 520 is configured to execute the following operations when executing the computer program: perform X-ray diffraction test on the pretreated deformed sample under different environmental parameters, and obtain martensite volume fraction and dislocation density based on the obtained diffraction curve; construct a first function based on the martensite volume fraction, the corresponding environmental parameter and the deformation amount of the deformed sample; obtain yield strength according to the dislocation density, and construct a quantitative model according to the yield strength and the first function; input the actual operation parameters into the quantitative model to obtain corresponding optimal operation parameters, wherein the actual operation parameters include actual temperature and actual deformation amount, and the optimal operation parameters include optimal deformation amount corresponding to the actual temperature and optimal temperature corresponding to the actual deformation amount; manufacture a rocket tank cylinder segment according to the optimal operation parameters.

[0094] The embodiment of the present application provides a computer readable storage medium, and the storage medium stores a computer program, and when the computer program is executed by a processor, the stainless steel rocket tank cylinder segment forming method is realized.

[0095] Alternatively, a non-volatile computer readable storage medium, the storage medium stores a computer program, and when the computer program is executed by a processor, the processor executes the following operations: X-ray diffraction tests are performed on the pretreated deformed sample under different environmental parameters, and the martensite volume fraction and the dislocation density are obtained based on the obtained diffraction curve; A first function is constructed based on the martensite volume fraction, the corresponding environmental parameter and the deformation amount of the deformed sample; The yield strength is obtained according to the dislocation density, and a quantitative model is constructed according to the yield strength and the first function; The actual operation parameters are input into the quantitative model to obtain corresponding optimal operation parameters, wherein the actual operation parameters include an actual temperature and an actual deformation amount, and the optimal operation parameters include an optimal deformation amount corresponding to the actual temperature and an optimal temperature corresponding to the actual deformation amount; The rocket tank cylinder segment is manufactured according to the optimal operation parameters.

[0096] An electronic device 500 that can be a server or a client of the present application will now be described, which is an example of a hardware device that can be applied to various aspects of the present application. The electronic device 500 is intended to represent various forms of digital electronic computer devices such as laptops, desktops, tablets, personal digital assistants, servers, blade servers, mainframes, and other appropriate computers. The electronic device 500 can also represent various forms of mobile devices such as personal digital assistants, cellular telephones, smart phones, wearable devices, and other similar computing devices. The components shown here, their connections and relationships, and their functions, are meant to be examples only, and are not meant to limit implementations of the present application described and / or claimed in this document.

[0097] The electronic device 500 includes a computing unit that can perform various appropriate actions and processes in accordance with a computer program stored in a read-only memory (ROM) or a computer program loaded into a random access memory (RAM) from a storage unit. In the RAM, various programs and data required for device operation can also be stored. The computing unit, the ROM, and the RAM are connected to each other through a bus. An input / output (I / O) interface is also connected to the bus.

[0098] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by a computer program instructing relevant hardware, and the program can be stored in a computer readable storage medium. When the program is executed, the program can include the processes of the above-mentioned embodiment methods. The storage medium can be a magnetic disc, an optical disc, a read-only memory (ROM), a random access memory (RAM), or the like. In this application, the units described as separate components can or can not be physically separated, and the components shown as units can or can not be physical units, that is, they can be located in one place, or they can be distributed on multiple network units. Part or all of the units can be selected according to actual needs to achieve the purpose of the embodiment of the present application. In addition, the functional units in each embodiment of the present application can be integrated in one processing unit, or each unit can exist physically independently, or two or more units can be integrated in one unit. The integrated unit can be realized in the form of hardware or in the form of a software functional unit.

[0099] Although the present application is disclosed as above, the protection scope of the present application is not limited to this. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present application, and these changes and modifications will fall within the protection scope of the present application.

Claims

1. A method for forming a stainless steel rocket propellant tank section, characterized in that, include: X-ray diffraction tests were performed on the pretreated deformed specimens under different environmental parameters, and the martensite volume fraction and dislocation density were obtained based on the diffraction curves. A first function is constructed based on the martensite volume fraction, the corresponding environmental parameters, and the deformation amount of the deformed specimen; The yield strength is obtained based on the dislocation density, and a quantitative model is constructed based on the yield strength and the first function. The actual operating parameters are input into the quantitative model to obtain the corresponding optimal operating parameters. The actual operating parameters include the actual temperature and the actual deformation. The optimal operating parameters include the optimal deformation corresponding to the actual temperature and the optimal temperature corresponding to the actual deformation. The rocket propellant tank section is manufactured according to the optimal operating parameters.

2. The method for forming stainless steel rocket propellant tank sections according to claim 1, characterized in that, The construction of the first function based on the martensite volume fraction, the corresponding environmental parameters, and the deformation amount of the deformed specimen includes: The first function is represented by a first formula, which includes: ， Among them, f α̍ T f represents the martensite volume fraction at the environmental parameter T. s T β represents the martensite cohesion volume fraction at the environmental parameter T. T ε represents the fitting parameter for the environmental parameter T, and ε represents the deformation amount.

3. The method for forming stainless steel rocket propellant tank sections according to claim 1, characterized in that, The yield strength includes austenitic yield strength and martensitic yield strength; The step of constructing a quantitative model based on the yield strength and the first function includes: Obtain the difference between the preset value and the martensite volume fraction, and obtain the first value by multiplying the difference by the austenite yield strength; The second value is obtained by multiplying the martensite yield strength by the martensite volume fraction. The quantitative model is obtained by summing the first value and the second value.

4. The method for forming stainless steel rocket propellant tank sections according to claim 3, characterized in that, The quantitative model is expressed using a second formula, which includes: = (1-f α̍ T )+ f α̍ T =f(T,ε), in, This represents the yield strength at the given environmental parameter T. The term represents the martensitic yield strength at the specified environmental parameter T. The austenitic yield strength is represented by the environmental parameter T, and f(T, ε) represents the relationship function between the yield strength and the environmental parameter T and the amount of deformation.

5. The method for forming stainless steel rocket propellant tank sections according to claim 1, characterized in that, The process of manufacturing the rocket propellant tank section according to the optimal operating parameters includes: The diameter of the cylindrical blank is obtained based on the actual deformation amount or the optimal deformation amount. The blank is cut to obtain material according to the diameter of the cylindrical blank, and the material is formed to obtain the cylindrical blank part; The initial yield stress and film-applying pressure of the cylindrical blank part are obtained. The cylindrical blank part is placed in a low-temperature bulging mold and pre-cooled according to the optimal temperature corresponding to the actual deformation amount or the actual temperature corresponding to the optimal deformation amount, the initial yield stress and the film-applying pressure. The part is then bulged at low temperature until it is fully molded. After removing the expanded cylindrical blank part, the process section is cut off to obtain the rocket storage tank section.

6. The method for forming stainless steel rocket propellant tank sections according to claim 1, characterized in that, The determination of martensite volume fraction and dislocation density based on the obtained diffraction curves includes: The volume fraction of martensite is obtained from the integrated intensity of the diffraction peaks of the martensitic phase crystal plane and the integrated intensity of the diffraction peaks of the austenitic phase crystal plane in the diffraction curve.

7. The method for forming stainless steel rocket propellant tank sections according to claim 1, characterized in that, The determination of martensite volume fraction and dislocation density based on the obtained diffraction curves includes: The full width at half maximum (FWHM) characteristics of the austenite and martensite phases in the diffraction curves are obtained respectively. Based on the FWHM characteristics, the first diffraction vector change and the first diffraction vector of the austenite phase crystal plane, as well as the second diffraction vector change and the second diffraction vector of the martensite phase crystal plane, are obtained. Based on the relationship between the change in diffraction vector and the change in dislocation density, the slope of the Auster curve is obtained according to the change in the first diffraction vector and the first diffraction vector, and the slope of the Martens curve is obtained according to the change in the second diffraction vector and the second diffraction vector. The austenitic dislocation density is obtained from the slope of the austenitic curve, and the Markov dislocation density is obtained from the slope of the Markov curve.

8. A stainless steel rocket propellant tank section forming device, characterized in that, include: The testing module is used to perform X-ray diffraction tests on pretreated deformed specimens under different environmental parameters, and to obtain the martensite volume fraction and dislocation density based on the obtained diffraction curves. A generation module is used to construct a first function based on the martensite volume fraction, the corresponding environmental parameters, and the deformation amount of the deformed specimen; The module is used to obtain the yield strength based on the dislocation density and to construct a quantitative model based on the yield strength and the first function. An execution module is used to obtain actual operating parameters input into the quantitative model and obtain corresponding optimal operating parameters. The actual operating parameters include actual temperature and actual deformation, and the optimal operating parameters include the optimal deformation corresponding to the actual temperature and the optimal temperature corresponding to the actual deformation. A manufacturing module for manufacturing rocket propellant tank sections according to the optimal operating parameters.

9. An electronic device, characterized in that, Including memory and processor; The memory is used to store computer programs; The processor is configured to implement the stainless steel rocket tank section forming method as described in any one of claims 1 to 7 when executing the computer program.

10. A computer-readable storage medium, characterized in that, The storage medium stores a computer program, which, when executed by a processor, implements the stainless steel rocket tank section forming method as described in any one of claims 1 to 7.

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