CN108804835B - Manufacturing process of thrust structure - Google Patents
Manufacturing process of thrust structure Download PDFInfo
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Abstract
The manufacturing process of the thrust structure comprises a design process and a production process, wherein the production process is operated according to the result of the design process; in the design process, an initialized curved surface model is established, material properties and material thickness are preliminarily determined according to the curved surface model, then the curved surface model is dispersed by adopting a finite element method, boundary conditions of the curved surface model after dispersion are received to establish the finite element model, optimized design variables, optimized constraint conditions and optimized targets are received to obtain the topological model, the topological optimization model is solved, the model is modified according to topological optimization results, the optimized design variables, the optimized constraint conditions and the optimized targets are received to obtain a size optimization model, and finally the size optimization model is solved. The design can actively take the performance requirements of the thrust structure as optimization design variables and optimization constraint conditions, can set an optimization target for optimization, avoids passive optimization, and can shorten the design period and improve the design benefit.
Description
Technical Field
The invention relates to an anti-thrust structure, in particular to a manufacturing process of the anti-thrust structure, which is particularly suitable for shortening a design period and improving design benefits.
Background
The thrust structure is an important functional component of the test device structure, belongs to the field of experimental equipment, and plays a role in bearing and transmitting load. The thrust structure is designed to ensure the structural strength and stability and reduce the weight as much as possible. The existing common design method comprises the steps of firstly establishing an initialized geometric model of the thrust structure according to experience or a thrust structure with a similar analog structure, then carrying out simulation check on the structure performance, and then carrying out repeated adjustment and check on each plate thickness of the thrust structure on the basis of the simulation check to finally obtain a thrust structure scheme meeting the requirements.
Because the selection of the initialized geometric model and the selected plate thickness has certain blindness, and the optimization of the initialized geometric model can be realized only by repeated checking and adjustment, once the initialized geometric model is established, the plate thickness selects an incorrect thrust structure or a thrust structure without similar structure as a reference, the subsequent optimization period is very long, the performance optimization effect of the obtained model is not ideal, the more the performance requirements on the thrust structure are, the more the problems of the existing design method are.
The invention patent application with the application publication number of CN107101795A and the application publication date of 2017, 8.29 discloses a thrust structure, which comprises a bottom plate, a collision bearing plate, a rear wrapping plate, a pressure plate, at least one vertical plate and two side plates, wherein the two side plates are vertically fixed on the bottom plate, the two side plates are arranged in parallel relatively, the collision bearing plate and the rear wrapping plate are fixed on the bottom plate, the rear wrapping plate and the collision bearing plate are respectively and fixedly connected with the two side plates, the tops of the collision bearing plate and the rear wrapping plate are mutually connected, the bottom plate, the collision bearing plate, the rear wrapping plate and the two side plates define a cavity, the at least one vertical plate is arranged in the cavity, each vertical plate is arranged in parallel with the two side plates, each vertical plate is respectively connected with the bottom plate, the rear wrapping plate and the collision bearing plate, a first notch is arranged on one side edge of the vertical plate, which is connected with the collision bearing plate, the pressure plate is clamped in the first notch, one side wall of the pressure plate is fixedly connected with the vertical plate, the other side wall of the pressure plate is fixedly connected with the impact plate. Although the design discloses a specific structure of the thrust structure, the thrust structure belongs to a structural patent, the protection of the thrust structure is focused on a mechanical structure, and technical characteristics of the thrust structure are not designed, so that the defects existing in the prior art cannot be solved.
The information disclosed in this background section is only for enhancement of understanding of the general background of the patent application and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person skilled in the art.
Disclosure of Invention
The invention aims to overcome the defects and problems of longer design period and poorer design benefit in the prior art and provides a manufacturing process of a thrust structure with shorter design period and better design benefit.
In order to achieve the above purpose, the technical solution of the invention is as follows: the manufacturing process of the thrust structure comprises a design process and a production process which are sequentially carried out, wherein the production process is operated according to the result of the design process; the design process comprises the following steps of:
s11, constructing an initialization surface model: firstly, determining a design boundary range, namely a space range of the thrust structure, according to overall requirements, and then primarily determining a curved surface structure form according to a bearing condition to obtain an initialized curved surface model;
s12, preliminarily estimating the material property and thickness, and dispersing the curved surface model by adopting a finite element method: firstly, preliminarily estimating material properties and plate thickness, then preprocessing in finite element software, and dividing finite element grids to disperse the initialized surface model;
s13, setting boundary conditions to obtain a finite element model: receiving the boundary condition of the dispersed initialization surface model to construct a finite element model;
s14, receiving the optimization design variables, the optimization constraint conditions and the optimization target to obtain a topology optimization model: firstly, determining an optimization design variable, and then determining an optimization constraint condition and an optimization target to carry out topology optimization on the optimization design variable, so that the maximum structural rigidity is optimized, and a topology optimization model is obtained;
s15, solving a topological optimization model: obtaining the structural shape with the maximum rigidity through topological optimization;
s16, deriving a topological result model, and modifying the generated size-optimized surface model: deriving a result model of topology optimization, and modifying according to process conditions and actual conditions to obtain a size-optimized curved surface model;
s17, receiving material properties and plate thickness, and discretizing the model by adopting a finite element method: firstly, preliminarily determining material properties and plate thickness, preprocessing in finite element software, dividing finite element grids, and then dispersing the size-optimized curved surface model;
s18, setting boundary conditions to obtain a finite element model: determining boundary conditions of the dispersed curved surface model to construct and obtain a finite element model;
s19, receiving the optimization design variables, the optimization constraint conditions and the optimization target to obtain a size optimization model: the optimization design variables, the optimization constraint conditions and the optimization targets are manually set according to performance requirements, wherein the performance requirements comprise structural rigidity, structural strength, resonant frequency, stability and total weight;
s20, solving a size optimization model: and determining an optimized design variable through optimizing the constraint condition and the optimization target so as to obtain the size of the thrust structure and further obtain a size optimization model so as to finish the design process.
The design process further comprises the following steps which are sequentially carried out after S20 and the size optimization model are solved:
s21, checking a size optimization model: during checking, firstly receiving boundary conditions of a size optimization model, wherein the boundary conditions of the size optimization model are the same as those of the discrete curved surface model, and then simulating the stress condition of the thrust structure during actual work through the size optimization model to check the size optimization model, wherein the checking content comprises structural strength and structural stability;
s22, adjusting the local structure of the size optimization model according to the checking result: and adjusting the local structure of the size optimization model according to the checking result, and obtaining a final thrust structure model after the adjustment is finished, wherein the thrust structure model is used for production as a final result of the design process.
The finite element method is performed using ANSYS software.
The material properties include density, modulus of elasticity, and poisson's ratio; the boundary conditions include the maximum load and the degree of freedom to which the thrust structure is subjected.
And S14, receiving an optimized design variable, an optimized constraint condition and an optimized target to obtain a topological optimization model, wherein the optimized design variable is the design boundary range, namely the space range of the thrust structure, the optimized constraint condition is the volume fraction of the thrust structure, and the optimized target is the rigidity of the thrust structure.
And S19, receiving an optimization design variable, an optimization constraint condition and an optimization target to obtain a size optimization model, wherein the optimization design variable is the thickness of a material, the optimization constraint condition is the strength and the stability of the push-to-stop structure, and the optimization target is the total weight of the push-to-stop structure.
In S11: the space range of the thrust structure is 2000mm multiplied by 3040mm multiplied by 2400mm, the curved surface structure is preliminarily determined to be five vertical plates, a bottom plate and a pressure plate according to the bearing condition, and the pressure plate bears the impact load; the vertical plates are welded with the wall plates, the thickness of each wall plate is 20mm, the bottom plate is welded with five vertical plates, three vertical plates are abutted to the back of the pressure plate at even intervals, and the other two vertical plates are respectively arranged close to the edges of the wall plates;
in S12: preliminarily estimating the thickness of the vertical plate to be 20mm, the thickness of the bottom plate to be 30mm and the thickness of the pressure plate to be 40 mm;
in S13: determining the boundary condition that the lower plane of the bottom plate is fixed and the impact load acts on the local surface of the pressure plate;
in S14: setting the topological mode of the five vertical plates by taking the optimized design variable as the area of the five parallel vertical plates, so that each vertical plate is subjected to topological optimization according to the same shape; two optimized responses are determined: the first is the model volume fraction, the second is the structural rigidity, the volume fraction is taken as a constraint condition, the structural rigidity is taken as an optimization target, so that the structure is subjected to iterative computation according to a certain volume fraction, and the maximum structural rigidity is optimized;
in S16: deriving a topological result model, modifying according to process conditions and actual conditions, and adding sealing plates and rib plates to obtain a size-optimized curved surface model;
in S17: firstly, preliminarily determining the thicknesses of a vertical plate and a rib plate to be 20mm, a pressure plate to be 40mm, a bottom plate to be 30mm and a sealing plate to be 15mm, then preprocessing in finite element software, dividing finite element grids and dispersing a curved surface model;
in S18: determining the boundary condition of the structure that the lower plane of the bottom plate is fixed and the impact load acts on the local surface of the pressure plate;
in S19: performance requirements include structural strength, stability, total weight; the optimization design variable is the thickness of the material, the optimization constraint condition is the structural strength and stability of the thrust, the optimization target is the total weight of the thrust, and the total weight is minimized on the premise of meeting the structural strength and stability during optimization, so that the structural strength and stability of the thrust structure are ensured, the total weight of the thrust structure is reduced, and the lightweight design of the thrust structure is realized;
s20: after the solution, the optimization result is adjusted, the thicknesses of the vertical plates on the two sides are changed from 13mm to 15mm, the thickness of the middle vertical plate is changed from 29.5mm to 30mm, the thickness of the front sealing plate is changed from 5mm to 8mm, the thickness of the rear sealing plate is stored for 8mm, the thickness of the pressure plate is stored for 50mm, and structurally, a plate with the thickness of 30mm is pasted in a stress area behind the wallboard.
The step S20 is followed by the steps S21 and S22 which are carried out in sequence;
in S21: the method comprises the steps of checking the structural strength of a size optimization model, wherein the maximum stress of the thrust structure in the design in actual work is 267 MPa and is smaller than the allowable stress of a material 280MPa, the requirement on the structural strength is met, and the stability of a first-order buckling coefficient 7.94 meets the requirement;
in S22: and improving the shape and the size of the rib plate to increase the local structural strength and the structural rigidity of the size optimization model so as to enhance the stability of the size optimization model, and obtaining a final thrust structural model after the local structure of the size optimization model is adjusted to finish the design process.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention relates to a manufacturing process of a thrust structure, which comprises a design process and a production process which are sequentially carried out, wherein the production process carries out production operation according to the result of the design process, the design process sequentially comprises 10 steps from S11 to S20, firstly, an initialized geometric model of the thrust structure is built according to a design area, then, the attribute and the initial material thickness are preliminarily estimated, then, a finite element method is adopted to carry out dispersion on a curved surface model, then, the boundary condition of the dispersed curved surface model is received to build a finite element model, then, the optimized design variable, the optimized constraint condition and the optimized target are received to obtain a topological optimized model, then, the topological optimized model is solved, then, the model is modified according to the topological result to prepare for size optimization, then, the optimized design variable, the optimized constraint condition and the optimized target are received according to the modified model to obtain a size optimized model, finally, a size optimization model is obtained to finish the design process, parameters such as performance requirements of the thrust structure can be actively used as optimization design variables and optimization constraint conditions, and optimization targets can be set for optimization, so that passive optimization is avoided, the design cycle of the product is shortened, the design benefit is improved, in addition, the overall layout is clear, the front-back connectivity is strong, each step is strong in operability, and the design process is easy to realize. Therefore, the invention not only can shorten the design period and improve the design benefit, but also is easy to operate and has higher production efficiency.
2. In the manufacturing process of the thrust structure, the two steps of S21 checking the size optimization model and S22 adjusting the local structure of the size optimization model according to the checking result can be added after the size optimization model is solved at S20, the optimization effect of the model can be further improved through the two added steps, the thrust structure model with stronger structural strength, structural rigidity and stability is obtained, and the thrust structure with better quality can be produced. Therefore, the invention has stronger structural strength and rigidity and better product quality.
Drawings
FIG. 1 is a schematic flow chart of the design process of the present invention.
Fig. 2 is a schematic flow chart of a design process in the second embodiment of the present invention.
Fig. 3 is a schematic diagram of an initialization model in the third embodiment of the present invention.
FIG. 4 is a diagram of a finite element model after discretization in the third embodiment of the present invention.
FIG. 5 is a schematic diagram of a finite element model for topology optimization according to a third embodiment of the present invention.
Fig. 6 is a schematic diagram of a result of topology optimization in the third embodiment of the present invention.
Fig. 7 is a schematic diagram of a model modified according to a result of topology optimization in the third embodiment of the present invention.
FIG. 8 is a diagram of a finite element model after discretization in the third embodiment of the present invention.
FIG. 9 is a schematic diagram of a finite element model after dimensional optimization in a third embodiment of the present invention.
Fig. 10 is a schematic diagram of the size optimization result in the third embodiment of the present invention.
Detailed Description
The invention is described in further detail below with reference to the figures and the detailed description of the invention.
Referring to fig. 1 to 10, a manufacturing process of a thrust structure includes a design process and a production process performed in sequence, wherein the production process is operated according to a result of the design process; the design process comprises the following steps of:
s11, constructing an initialization surface model: firstly, determining a design boundary range, namely a space range of a thrust structure, according to overall requirements, and then primarily determining a curved surface structure form according to a bearing condition to obtain an initialized curved surface model;
s12, preliminarily estimating the material property and thickness, and dispersing the curved surface model by adopting a finite element method: firstly, preliminarily estimating material properties and plate thickness, preprocessing in finite element software, and dividing finite element grids to disperse an initialized curved surface model;
s13, setting boundary conditions to obtain a finite element model: receiving the boundary condition of the dispersed initialization surface model to construct a finite element model;
s14, receiving the optimization design variables, the optimization constraint conditions and the optimization target to obtain a topology optimization model: firstly, determining an optimization design variable, and then determining an optimization constraint condition and an optimization target to carry out topology optimization on the optimization design variable, so that the maximum structural rigidity is optimized, and a topology optimization model is obtained;
s15, solving a topological optimization model: obtaining the structural shape with the maximum rigidity through topological optimization;
s16, deriving a topological result model, and modifying the generated size-optimized surface model: deriving a result model of topology optimization, and modifying according to process conditions and actual conditions to obtain a size-optimized curved surface model;
s17, receiving material properties and plate thickness, and discretizing the model by adopting a finite element method: firstly, preliminarily determining material properties and plate thickness, then preprocessing in finite element software, dividing finite element grids, and then dispersing the size-optimized curved surface model;
s18, setting boundary conditions to obtain a finite element model: determining boundary conditions of the dispersed curved surface model to construct and obtain a finite element model;
s19, receiving the optimization design variables, the optimization constraint conditions and the optimization target to obtain a size optimization model: the optimization design variables, the optimization constraint conditions and the optimization targets are manually set according to performance requirements, wherein the performance requirements comprise structural rigidity, structural strength, resonant frequency, stability and total weight;
s20, solving a size optimization model: and determining an optimized design variable through optimizing the constraint condition and the optimization target so as to obtain the size of the thrust structure and further obtain a size optimization model so as to finish the design process.
The design process further comprises the following steps which are sequentially carried out after S20 and the size optimization model are solved:
s21, checking a size optimization model: during checking, firstly receiving boundary conditions of a size optimization model, wherein the boundary conditions of the size optimization model are the same as those of the discrete curved surface model, and then simulating the stress condition of the thrust structure during actual work through the size optimization model to check the size optimization model, wherein the checking content comprises structural strength and structural stability;
s22, adjusting the local structure of the size optimization model according to the checking result: and adjusting the local structure of the size optimization model according to the checking result, and obtaining a final thrust structure model after the adjustment is finished, wherein the thrust structure model is used as a final result of the design process for production.
The finite element method is performed using ANSYS software.
The material properties include density, modulus of elasticity, and poisson's ratio; the boundary conditions include maximum load and degrees of freedom to which the thrust structure is subjected.
And S14, receiving an optimized design variable, an optimized constraint condition and an optimized target to obtain a topological optimization model, wherein the optimized design variable is the design boundary range, namely the space range of the thrust structure, the optimized constraint condition is the volume fraction of the thrust structure, and the optimized target is the rigidity of the thrust structure.
And S19, receiving an optimized design variable, an optimized constraint condition and an optimized target to obtain the thickness of the material in the size optimization model, wherein the optimized design variable is the strength and the stability of the push structure under the optimized constraint condition, and the optimized target is the total weight of the push structure.
In S11: the space range of the thrust structure is 2000mm multiplied by 3040mm multiplied by 2400mm, the curved surface structure is preliminarily determined to be five vertical plates, a bottom plate and a pressure plate according to the bearing condition, and the pressure plate bears the impact load; the vertical plates are welded with the wall plates, the thickness of each wall plate is 20mm, the bottom plate is welded with five vertical plates, three vertical plates are abutted to the back of the pressure plate at even intervals, and the other two vertical plates are respectively arranged close to the edges of the wall plates;
in S12: preliminarily estimating the thickness of the vertical plate to be 20mm, the thickness of the bottom plate to be 30mm and the thickness of the pressure plate to be 40 mm;
in S13: determining the boundary condition that the lower plane of the bottom plate is fixed and the impact load acts on the local surface of the pressure plate;
in S14: setting the topological modes of the five vertical plates by taking the optimized design variables as the areas of the five parallel vertical plates, so that each vertical plate is subjected to topological optimization according to the same shape; two optimized responses are determined: the first is the model volume fraction, the second is the structural rigidity, the volume fraction is used as a constraint condition, the structural rigidity is used as an optimization target, the structure is subjected to iterative calculation according to a certain volume fraction, and the maximum structural rigidity is optimized;
in S16: exporting a topological result model, modifying according to process conditions and actual conditions, and adding sealing plates and rib plates to obtain a size-optimized curved surface model;
in S17: firstly, preliminarily determining the thicknesses of a vertical plate and a rib plate to be 20mm, a pressure plate to be 40mm, a bottom plate to be 30mm and a sealing plate to be 15mm, then preprocessing in finite element software, dividing finite element grids and dispersing a curved surface model;
in S18: determining the boundary condition of the structure that the lower plane of the bottom plate is fixed and the impact load acts on the local surface of the pressure plate;
in S19: performance requirements include structural strength, stability, total weight; the optimization design variable is the thickness of the material, the optimization constraint condition is the structural strength and stability of the thrust, the optimization target is the total weight of the thrust, and the total weight is minimized on the premise of meeting the structural strength and stability during optimization, so that the structural strength and stability of the thrust structure are ensured, the total weight of the thrust structure is reduced, and the lightweight design of the thrust structure is realized;
s20: after solving, the optimized result is adjusted, the thickness of the vertical plates on the two sides is changed into 15mm from 13mm, the thickness of the vertical plate in the middle is changed into 30mm from 29.5mm, the thickness of the front sealing plate is changed into 8mm from 5mm, the thickness of the rear sealing plate is stored for 8mm, the thickness of the pressure plate is stored for 50mm, and structurally, a plate with the thickness of 30mm is pasted in a rear stress area of the wallboard.
The step S20 is followed by the steps S21 and S22 which are sequentially carried out;
in S21: the method comprises the steps of checking the structural strength of a size optimization model, wherein the maximum stress of the thrust structure in the design in actual work is 267 MPa and is smaller than the allowable stress of 280MPa of a material, the requirement on the structural strength is met, and the stability of a first-order buckling coefficient 7.94 meets the requirement;
in S22: and improving the shape and the size of the rib plate to increase the local structural strength and the structural rigidity of the size optimization model, so that the stability of the size optimization model is enhanced, and after the local structure of the size optimization model is adjusted, a final thrust structure model can be obtained to finish the design process.
The principle of the invention is illustrated as follows:
the method comprises the steps of firstly constructing an initialized curved surface model of the thrust structure, receiving material attributes and initial material thickness, then dispersing the curved surface model by adopting a finite element method, receiving boundary conditions of the dispersed curved surface model to construct the finite element model, receiving optimization design variables, optimization constraint conditions and optimization targets to obtain a topology optimization model, solving the topology optimization model, deriving a topology optimization result to modify the curved surface model, receiving the material attributes and the initial material thickness, then dispersing the curved surface model by adopting the finite element method, receiving the boundary conditions of the dispersed curved surface model to construct the finite element model, receiving the optimization design variables, the optimization constraint conditions and the optimization targets to obtain a size optimization model, and solving the size optimization model. Because parameters such as performance requirements of the thrust structure can be actively used as optimization design variables and optimization constraint conditions, and an optimization target can be set for optimization, passive optimization is avoided, the design cycle of a product is shortened, and the design benefit is improved.
Example 1:
referring to fig. 1 to 10, a manufacturing process of a thrust structure includes a design process and a production process performed in sequence, wherein the production process is operated according to a result of the design process; the design process comprises the following steps of:
s11, constructing an initialization surface model: firstly, determining a design boundary range, namely a space range of a thrust structure, according to overall requirements, and then primarily determining a curved surface structure form according to a bearing condition to obtain an initialized curved surface model;
s12, preliminarily estimating the material property and thickness, and dispersing the curved surface model by adopting a finite element method: firstly, preliminarily estimating material properties and plate thickness, then preprocessing in finite element software, and dividing finite element grids to disperse the initialized surface model;
s13, setting boundary conditions to obtain a finite element model: receiving the boundary condition of the dispersed initialization surface model to construct a finite element model;
s14, receiving the optimization design variables, the optimization constraint conditions and the optimization target to obtain a topology optimization model: firstly, determining an optimization design variable, and then determining an optimization constraint condition and an optimization target to carry out topology optimization on the optimization design variable, so that the maximum structural rigidity is optimized, and a topology optimization model is obtained;
s15, solving a topological optimization model: obtaining the structural shape with the maximum rigidity through topological optimization;
s16, deriving a topological result model, and modifying the generated size-optimized surface model: deriving a result model of topology optimization, and modifying according to process conditions and actual conditions to obtain a size-optimized curved surface model;
s17, receiving material properties and plate thickness, and discretizing the model by adopting a finite element method: firstly, preliminarily determining material properties and plate thickness, preprocessing in finite element software, dividing finite element grids, and then dispersing the size-optimized curved surface model;
s18, setting boundary conditions to obtain a finite element model: determining boundary conditions of the dispersed curved surface model to construct and obtain a finite element model;
s19, receiving the optimization design variables, the optimization constraint conditions and the optimization target to obtain a size optimization model: the optimization design variables, the optimization constraint conditions and the optimization targets are manually set according to performance requirements, wherein the performance requirements comprise structural rigidity, structural strength, resonant frequency, stability and total weight;
s20, solving a size optimization model: and determining an optimized design variable through optimizing the constraint condition and the optimization target so as to obtain the size of the thrust structure and further obtain a size optimization model so as to finish the design process.
Example 2:
the basic contents are the same as example 1, except that:
the design process further comprises the following steps after S20 and the size optimization model are solved:
s21, checking a size optimization model: during checking, firstly receiving boundary conditions of a size optimization model, wherein the boundary conditions of the size optimization model are the same as those of the discrete curved surface model, and then simulating the stress condition of the thrust structure during actual work through the size optimization model to check the size optimization model, wherein the checking content comprises structural strength and structural stability;
s22, adjusting the local structure of the size optimization model according to the checking result: and adjusting the local structure of the size optimization model according to the checking result, and obtaining a final thrust structure model after the adjustment is finished, wherein the thrust structure model is used for production as a final result of the design process.
Example 3:
referring to fig. 1 to 10, a manufacturing process of a thrust structure includes a design process and a production process performed in sequence, wherein the production process is operated according to a result of the design process; the design process comprises the following steps of:
s11, constructing an initialization surface model: the shape and thickness of the wallboard are provided by the whole, the thickness of the wallboard is 20mm, the design boundary range is determined according to the general requirement, the space range of the thrust structure is 2000mm multiplied by 3040mm multiplied by 2400mm, the curved surface structure is preliminarily determined to be five vertical plates, a bottom plate and a pressure plate according to the load bearing condition and the load bearing pressure plate is used for bearing the impact load according to the load action of a component in the local area of the wall body; the vertical plates are welded with the wall plates, the bottom plate is welded with the five vertical plates, three vertical plates are evenly spaced after abutting against the pressure plate, and the other two vertical plates are respectively arranged close to the edges of the wall plates; the established initialized surface model is shown in FIG. 3;
s12, preliminarily estimating the material property and thickness, and dispersing the curved surface model by adopting a finite element method: determining the connection relation among the plates, preliminarily estimating the material property and the plate thickness, preliminarily estimating the vertical plate thickness to be 20mm, the bottom plate thickness to be 30mm and the pressure plate thickness to be 40mm, preprocessing in finite element software, dividing finite element grids, and dispersing the curved surface model; the number of units is determined by the unit size, the smaller the unit size is, the larger the number of units is, otherwise, the larger the unit size is, the smaller the number of units is; the discretized model is shown in FIG. 4;
s13, setting boundary conditions to obtain a finite element model: determining the boundary condition of the structure that the lower plane of the bottom plate is fixed and the impact load acts on the local surface of the pressure plate; the boundary load conditions are shown in FIG. 5;
s14, receiving the optimization design variables, the optimization constraint conditions and the optimization target to obtain a topology optimization model: setting the topological mode of the five vertical plates by taking design variables as areas of the five parallel vertical plates, so that each parallel vertical plate is subjected to topological optimization according to the same shape; two optimized responses are determined: the first is the model volume fraction, the second is the structural rigidity, the volume fraction is used as a constraint condition, the structural rigidity is used as an optimization target, the structure is subjected to iterative calculation according to a certain volume fraction, and the maximum structural rigidity is optimized;
s15, solving a topological optimization model: obtaining the structural shape with the maximum rigidity through topological optimization; the result of the topology optimization is shown in fig. 6;
s16, deriving a topological result model, and modifying the generated size-optimized surface model: exporting a topological result model in software, modifying according to process conditions and actual conditions, and adding sealing plates and rib plates; the modified model is shown in FIG. 7;
s17, receiving material properties and plate thickness, and discretizing the model by adopting a finite element method: determining the connection relation among the plates, preliminarily determining the material property and the plate thickness, the thicknesses of the vertical plate and the rib plate are 20mm, the pressure plate thickness is 40mm, the bottom plate thickness is 30mm and the sealing plate thickness is 15mm, preprocessing the plates in finite element software, dividing finite element grids and dispersing a curved surface model; the finite element model is shown in FIG. 8;
s18, setting boundary conditions to obtain a finite element model: determining the boundary condition of the structure that the lower plane of the bottom plate is fixed and the impact load acts on the local surface of the pressure plate;
s19, receiving the optimization design variables, the optimization constraint conditions and the optimization target to obtain a size optimization model: the optimization design variable is the thickness of a material, the structural strength and the stability of the thrust structure are optimized under constraint conditions, the total weight of the thrust structure is optimized, and the total weight is minimized on the premise of meeting the structural strength and the stability during optimization, so that the structural strength and the stability of the thrust structure can be ensured, the total weight can be reduced, and the lightweight design of the thrust structure is realized; the computational model is shown in FIG. 9;
s20, solving a size optimization model: determining an optimized design variable through an optimized constraint condition and an optimized target, thereby obtaining the size of the thrust structure; the optimization results are shown in fig. 10;
s21, checking a size optimization model: and during checking, receiving boundary conditions of the size optimization model, wherein the boundary conditions of the size optimization model are the same as those of the discrete geometric curved surface model, and simulating the stress condition of the thrust structure during actual work through the size optimization model to check the size optimization model, including checking the structural strength and the structural stability. In this embodiment, after the solution, the optimization result is adjusted according to the actual situation, the thickness of the vertical plates on the two sides is changed from 13mm to 15mm, the thickness of the vertical plate in the middle is changed from 29.5mm to 30mm, and the thickness of the front sealing plate is changed from 5mm to 8 mm. 8mm is preserved to back shrouding thickness, and 50mm is preserved to pressure plate thickness, structurally behind the wallboard atress regional paste 30 mm's board can. Further, checking the structural strength of the size optimization model, wherein the maximum stress of the thrust structure in actual work is 267 MPa and is smaller than the allowable stress of 280MPa of the material, so that the requirement on the structural strength is met, and the stability of the first-order buckling coefficient of 7.94 meets the requirement;
s22, adjusting the local structure of the size optimization model according to the checking result: and improving the shape and the size of the rib plate on the size optimization model to increase the local structural strength and the structural rigidity of the size optimization model to enhance the stability of the size optimization model so as to obtain a final thrust model, and producing according to the final thrust model.
The above description is only a preferred embodiment of the present invention, and the scope of the present invention is not limited to the above embodiment, but equivalent modifications or changes made by those skilled in the art according to the disclosure of the present invention should be included in the scope of the present invention as set forth in the appended claims.
Claims (7)
1. A manufacturing process of a thrust structure comprises a design process and a production process which are sequentially carried out, wherein the production process is operated according to the result of the design process, and the manufacturing process is characterized in that: the design process comprises the following steps of:
s11, constructing an initialization surface model: firstly, determining a design boundary range, namely a space range of the thrust structure, according to overall requirements, and then primarily determining a curved surface structure form according to a bearing condition to obtain an initialized curved surface model;
s12, preliminarily estimating the material property and thickness, and dispersing the curved surface model by adopting a finite element method: firstly, preliminarily estimating material properties and plate thickness, preprocessing in finite element software, and dividing finite element grids to disperse an initialized curved surface model;
s13, setting boundary conditions to obtain a finite element model: receiving the boundary condition of the dispersed initialization surface model to construct a finite element model;
s14, receiving the optimization design variables, the optimization constraint conditions and the optimization target to obtain a topology optimization model: firstly, determining an optimization design variable, and then determining an optimization constraint condition and an optimization target to carry out topology optimization on the optimization design variable, so that the maximum structural rigidity is optimized, and a topology optimization model is obtained; the step S14 of receiving an optimization design variable, an optimization constraint condition and an optimization target to obtain a topological optimization model, wherein the optimization design variable is the design boundary range, namely the space range of the thrust structure, the optimization constraint condition is the volume fraction of the thrust structure, and the optimization target is the rigidity of the thrust structure;
s15, solving a topological optimization model: obtaining the structural shape with the maximum rigidity through topological optimization;
s16, deriving a topological result model, and modifying the generated size-optimized surface model: deriving a result model of topology optimization, and modifying according to process conditions and actual conditions to obtain a size-optimized curved surface model;
s17, receiving material properties and plate thickness, and discretizing the model by adopting a finite element method: firstly, preliminarily determining material properties and plate thickness, preprocessing in finite element software, dividing finite element grids, and then dispersing the size-optimized curved surface model;
s18, setting boundary conditions to obtain a finite element model: determining boundary conditions of the discrete curved surface model to construct and obtain a finite element model;
s19, receiving the optimization design variables, the optimization constraint conditions and the optimization target to obtain a size optimization model: the optimization design variables, the optimization constraint conditions and the optimization targets are manually set according to performance requirements, wherein the performance requirements comprise structural rigidity, structural strength, resonant frequency, stability and total weight;
s20, solving a size optimization model: and determining an optimized design variable through optimizing the constraint condition and the optimization target so as to obtain the size of the thrust structure and further obtain a size optimization model so as to finish the design process.
2. The manufacturing process of the thrust structure according to claim 1, wherein: the design process further comprises the following steps which are sequentially carried out after S20 and the size optimization model are solved:
s21, checking a size optimization model: during checking, firstly receiving boundary conditions of a size optimization model, wherein the boundary conditions of the size optimization model are the same as those of the discrete curved surface model, and then simulating the stress condition of the thrust structure during actual work through the size optimization model to check the size optimization model, wherein the checking content comprises structural strength and structural stability;
s22, adjusting the local structure of the size optimization model according to the checking result: and adjusting the local structure of the size optimization model according to the checking result, and obtaining a final thrust structure model after the adjustment is finished, wherein the thrust structure model is used as a final result of the design process for production.
3. A process for the manufacture of a thrust structure according to claim 1 or claim 2, wherein: the finite element method is performed using ANSYS software.
4. A process for manufacturing a thrust structure according to claim 1 or 2, wherein: the material properties include density, modulus of elasticity, and poisson's ratio; the boundary conditions include the maximum load and the degree of freedom to which the thrust structure is subjected.
5. A process for the manufacture of a thrust structure according to claim 1 or claim 2, wherein: and S19, receiving an optimization design variable, an optimization constraint condition and an optimization target to obtain a size optimization model, wherein the optimization design variable is the thickness of a material, the optimization constraint condition is the strength and the stability of the push-to-stop structure, and the optimization target is the total weight of the push-to-stop structure.
6. A process for manufacturing a thrust structure according to claim 1 or 2, wherein:
in S11: the space range of the thrust structure is 2000mm multiplied by 3040mm multiplied by 2400mm, the curved surface structure is preliminarily determined to be five vertical plates, a bottom plate and a pressure plate according to the bearing condition, and the pressure plate bears the impact load; the vertical plates are welded with the wall plates, the thickness of each wall plate is 20mm, the bottom plate is welded with five vertical plates, three vertical plates are abutted against the back of the pressure plate at even intervals, and the other two vertical plates are respectively arranged close to the edges of the wall plates;
in S12: preliminarily estimating the thickness of the vertical plate to be 20mm, the thickness of the bottom plate to be 30mm and the thickness of the pressure plate to be 40 mm;
in S13: determining the boundary condition that the lower plane of the bottom plate is fixed and the impact load acts on the local surface of the pressure plate;
in S14: setting the topological modes of the five vertical plates by taking the optimized design variables as the areas of the five parallel vertical plates, so that each vertical plate is subjected to topological optimization according to the same shape; two optimized responses are determined: the first is the model volume fraction, the second is the structural rigidity, the volume fraction is taken as a constraint condition, the structural rigidity is taken as an optimization target, so that the structure is subjected to iterative computation according to a certain volume fraction, and the maximum structural rigidity is optimized;
in S16: deriving a topological result model, modifying according to process conditions and actual conditions, and adding sealing plates and rib plates to obtain a size-optimized curved surface model;
in S17: firstly, preliminarily determining the thicknesses of a vertical plate and a rib plate to be 20mm, a pressure plate to be 40mm, a bottom plate to be 30mm and a sealing plate to be 15mm, then performing pretreatment in finite element software, dividing finite element grids and dispersing a curved surface model;
in S18: determining the boundary condition of the structure that the lower plane of the bottom plate is fixed and the impact load acts on the local surface of the pressure plate;
in S19: performance requirements include structural strength, stability, total weight; the optimization design variable is the thickness of the material, the optimization constraint condition is the structural strength and stability of the thrust, the optimization target is the total weight of the thrust, and the total weight is minimized on the premise of meeting the structural strength and stability during optimization, so that the structural strength and stability of the thrust structure are ensured, the total weight of the thrust structure is reduced, and the lightweight design of the thrust structure is realized;
s20: after the solution, the optimization result is adjusted, the thicknesses of the vertical plates on the two sides are changed from 13mm to 15mm, the thickness of the middle vertical plate is changed from 29.5mm to 30mm, the thickness of the front sealing plate is changed from 5mm to 8mm, the thickness of the rear sealing plate is stored for 8mm, the thickness of the pressure plate is stored for 50mm, and structurally, a plate with the thickness of 30mm is pasted in a stress area behind the wallboard.
7. A process for manufacturing a thrust structure according to claim 6, wherein: the step S20 is followed by the steps S21 and S22 which are sequentially carried out;
in S21: the method comprises the steps of checking the structural strength of a size optimization model, wherein the maximum stress of the thrust structure in the design in actual work is 267 MPa and is smaller than the allowable stress of a material 280MPa, the requirement on the structural strength is met, and the stability of a first-order buckling coefficient 7.94 meets the requirement;
in S22: and improving the shape and the size of the rib plate to increase the local structural strength and the structural rigidity of the size optimization model, so that the stability of the size optimization model is enhanced, and after the local structure of the size optimization model is adjusted, a final thrust structure model can be obtained to finish the design process.
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