Method, device and program for generating three-dimensional modeling information

Abstract

To provide a method, device and program for generating three-dimensional modeling information that can easily perform (1) designing a mechanical requirement including a stiffness in a stacking direction, (2) designing a continuity of fibers in a continuous fiber composite material, and (3) without requiring a huge computational cost, in a three-dimensional modeling object manufactured by an additive manufacturing method.SOLUTION: A stacking parameter optimization process (S107) of a modeling information generation process is configured in that a combination of stacking parameters corresponding to stacking directions of edges constituting an outer shape and edges constituting an internal structure is optimized based on input information regarding mechanical requirements including a rigidity of a three-dimensional modeling object in the stacking direction. A fiber arrangement optimization process (S109) is configured in that an arrangement of a composite material for each layer that satisfies the optimized stacking parameters obtained in the stacking parameter optimization process (S107) is optimized based on input information regarding a continuity of carbon fibers constituting the composite material.SELECTED DRAWING: Figure 2

Description

Technical Field

[0001] The present invention relates to a method, an apparatus, and a program for generating three-dimensional modeling information used in manufacturing a three-dimensional molded object formed by laminating continuous fiber composite materials. Note that a method of forming a three-dimensional molded object by laminating continuous fiber composite materials (hereinafter sometimes simply referred to as "lamination molding method") is an example of 3D printing technology or AM (Additive Manufacturing) technology.

Background Art

[0002] Mechanical parts composed of continuous fiber composite materials such as carbon fiber reinforced plastics (hereinafter referred to as "CFRP") are typically manufactured by laminating a plurality of sheet-like materials called prepregs in which resin is impregnated in advance. Continuous fibers refer to fibers that are long and continuous without breaks (hereinafter the same in this specification).

[0003] And, for the design method related to this type of lamination, for example, there are those using design variables called lamination parameters disclosed in Non-Patent Document 1 below, those using the thickness of fiber bundles disclosed in Non-Patent Document 2 below as design variables, and the like. Further, as a lamination molding method using continuous fiber composite materials, for example, a method of optimizing the fiber arrangement in the same plane using an evolutionary calculation algorithm is disclosed in Non-Patent Document 3 below.

[0004] Note that a method of forming a three-dimensional molded object by laminating continuous fiber composite materials and the technology related thereto are disclosed in, for example, Patent Document 1 below. Further, the technology related to the lamination parameters of the laminate is disclosed in, for example, Non-Patent Document 4 below.

Prior Art Documents

Non-Patent Documents

[0005]

Non-Patent Document 1

Non-Patent Document 2

Non-Patent Document 3

Non-Patent Document 4

Patent Document

[0006]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0007] The fibers constituting the continuous fiber composite material have a very high tensile strength in their longitudinal direction, while they have a low strength in the thickness direction. Therefore, mechanical parts made of continuous fiber composite materials have significantly different mechanical properties depending on the arrangement and orientation of the fibers. For example, in 3D printing technology and AM technology for forming three-dimensional objects by laminating continuous fiber composite materials as disclosed in Patent Document 1 above, the arrangement and orientation of the fibers are extremely important. However, a lamination forming method including the arrangement of fibers that can achieve a desired function has not yet been established.

[0008] For example, Non-Patent Document 1 above discloses a technique related to a method of arranging fibers in a three-dimensional object manufactured by stacking thin sheet-like laminated materials such as prepregs, and targets only the arrangement of fibers within a limited range of the lamination plane in the lamination direction. Therefore, this technique is not targeted at 3D printing technology.

[0009] Also, the technique disclosed in Non-Patent Document 2 above targets thin plate-like three-dimensional objects such as aircraft wing plates, and is not a technique targeting complex three-dimensional objects that make use of the features of the lamination forming method. Furthermore, the technique disclosed in Non-Patent Document 3 above optimizes the arrangement of fibers within the same plane and cannot be directly applied to the height direction (the entire lamination direction) of a three-dimensional object.

[0010] Therefore, in the disclosed technologies of these Non-Patent Documents 1 to 3 and Patent Document 1, it is not easy to design a three-dimensional object manufactured by a lamination forming method with respect to (1) mechanical requirements including rigidity in the height direction (lamination direction), or (2) the continuity of the fibers included in the continuous fiber composite material. Even if it were possible, (3) there would be a problem that an enormous computational cost would be required and the calculation time would be too long.

[0011] The present invention has been made to solve the above-described problems, and in a three-dimensional object manufactured by a layered manufacturing method, (1) design related to mechanical requirements including rigidity in the lamination direction, and (2) design related to the continuity of fibers included in a continuous fiber composite material can be easily performed, and (3) a method, an apparatus, and a program for generating three-dimensional modeling information that can be performed without requiring enormous computational costs are provided.

Means for Solving the Problems

[0012] To achieve the above object, the technical means of claim 1 described in the claims is adopted. According to this means, a method for generating three-dimensional modeling information used in the manufacture of a three-dimensional object formed by laminating a continuous fiber composite material (hereinafter sometimes referred to as a "composite material") includes a first step and a second step. In the first step, a combination of lamination parameters corresponding to each lamination direction of a shell part constituting the outer shape of the three-dimensional object and an infill part constituting the internal structure of the three-dimensional object is optimized based on a first predetermined condition related to mechanical requirements including rigidity in the lamination direction of the three-dimensional object. In the second step, the arrangement of the composite material for each layer that satisfies the optimal combination of lamination parameters obtained in the first step is optimized based on a second predetermined condition related to the continuity of the fibers constituting the composite material.

[0013] Also, to achieve the above object, the technical means of claim 4 described in the claims is adopted. According to this means, a three-dimensional modeling information generation apparatus used in the manufacture of a three-dimensional object formed by laminating a continuous fiber composite material includes a first optimization means and a second optimization means. The first optimization means optimizes a combination of lamination parameters corresponding to each lamination direction of a shell part constituting the outer shape of the three-dimensional object and an infill part constituting the internal structure of the three-dimensional object based on a first predetermined condition related to mechanical requirements including rigidity in the lamination direction of the three-dimensional object. The second optimization means optimizes the arrangement of the composite material for each layer that satisfies the optimal combination of lamination parameters obtained by the first optimization means based on a second predetermined condition related to the continuity of the fibers constituting the composite material.

[0014] Note that the "shell part" refers to outer wall elements, outer structures, etc. that appear on the appearance of the three-dimensional object, and the "infill part" refers to inner wall elements, inner structures, etc. that do not appear on the appearance of the three-dimensional object. Also, the "continuity of fibers" is an expression representing the degree of the length of fibers (continuous fibers) that are continuous without breaks. The longer the length of this continuous fiber, the better the continuity, and the shorter the length, the lower the continuity.

[0015] By these technical means, by inputting or previously setting the first predetermined condition and the second predetermined condition from the outside as design information, for example, the combination of lamination parameters corresponding to the respective lamination directions of the shell part and the infill part constituting the three-dimensional object is optimized based on the design information. And the arrangement of the composite material for each layer that satisfies the optimal combination of lamination parameters in the shell part and the infill part is also optimized based on the design information. Note that the lamination parameter can be treated as an intermediate variable in the whole number of laminations and does not depend on the number of laminations as described in Non-Patent Document 1 or papers on composite material science. Therefore, for example, compared with the technology disclosed in Non-Patent Document 1 above, it is possible to significantly reduce the calculation cost required when designing the fiber arrangement of the composite material.

[0016] Also, adopt the technical means of claim 2 described in the claims. According to this means, the first predetermined condition is based on the outer shape of the three-dimensional object and the mechanical strength or mechanical function required for the three-dimensional object. Thereby, by providing, as design information, that which is based on the outer shape of the three-dimensional object and the mechanical strength or mechanical function as the first predetermined condition, the combination of lamination parameters corresponding to each of the shell part and the infill part is optimized based on these design information.

[0017] Also, the technical means of claim 3 described in the claims is adopted. According to this means, the second predetermined condition is based on the number and length of the paths for arranging the composite material when laminating each layer of the shell part and the infill part. Thereby, as the second predetermined condition, by providing, as design information, something based on the number and length of the paths for arranging the composite material when laminating each layer of the shell part and the infill part, the arrangement of the composite material for each layer that satisfies the optimal combination of lamination parameters in the shell part and the infill part is optimized based on this design information.

[0018] Also, the technical means of claim 5 described in the claims is adopted. According to this means, the generation program of the three-dimensional modeling information causes a computer to function as the three-dimensional modeling information generation device described in claim 4.

Advantages of the Invention

[0019] In the present invention, by providing the first predetermined condition and the second predetermined condition, for example, as design information, by inputting from the outside or setting in advance inside, the combination of the lamination parameters corresponding to the respective lamination directions of the shell part and the infill part constituting the three-dimensional object is optimized based on the design information. And the arrangement of the composite material for each layer that satisfies the optimal combination of lamination parameters in the shell part and the infill part is also optimized based on the design information. Therefore, in a three-dimensional object manufactured by the lamination modeling method, (1) the design related to the mechanical requirements including the rigidity in the lamination direction of the three-dimensional object and (2) the design related to the continuity of the fibers contained in the continuous fiber composite material can be easily performed, and (3) it can be performed without requiring enormous computational costs.

Brief Description of the Drawings

[0020]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

Embodiments for Carrying Out the Invention

[0021] Hereinafter, embodiments of the method, apparatus, and program for generating three-dimensional modeling information of the present invention will be described with reference to the drawings. First, a configuration example of a 3D modeling system to which the method, apparatus, and program for generating three-dimensional modeling information of the present invention are applied will be described based on Fig. 1. Fig. 1 shows a block diagram representing a configuration example of the 3D modeling system.

[0022] As shown in FIG. 1, the 3D modeling system of this embodiment (hereinafter sometimes referred to as "this system") is an aspect of AM technology for laminating a composite material 90 to model a three-dimensional structure M, and is mainly composed of a generation device 10 and a modeling device 20. The composite material 90 is typically exemplified by CFRP in which continuous carbon fibers are impregnated with a resin material for 3D printing, but in addition to this, those in which continuous fiber materials such as glass fibers, natural fibers, and metal fibers are impregnated with a plastic material for 3D printing may also be used. Resin materials for 3D printing, etc., are, for example, those disclosed in Patent Document 1 above, and biodegradable plastic materials, etc., are also used.

[0023] The generation device 10 is a device that generates three-dimensional modeling information necessary for three-dimensionally modeling the three-dimensional structure M based on input information 50 input from the outside and outputs it as output information 60 to the modeling device 20. Typically, a personal computer is used. The three-dimensional modeling information is what is called so-called 3D data and has a file format such as STL or OBJ, for example. The generation device 10 includes an MPU and a GPU as a control unit, a keyboard and a pointing device as an input unit, a semiconductor memory as a main storage unit, an HDD or an SSD as an auxiliary storage unit, and a LAN port and a USB port, etc., as an output unit.

[0024] The modeling device 20 is a so-called 3D printer and is configured as disclosed in Patent Document 1 above, for example. In FIG. 1, the configuration of the modeling device 20 is simply shown. Therefore, in the figure, the illustration of the bobbin, loader mechanism, heater, cutter, supply mechanism, moving mechanism, and controller, which will be described here, is omitted, and only the nozzle 25 is shown. It should also be noted that the three-dimensional structure M shown in the figure is an image of the state in which the composite material 90 is laminated and modeled by the modeling device 20, and does not represent the cantilever beam 110, etc., which will be described later.

[0025] The shaping device 20 includes, for example, a plurality of bobbins around which thermoplastic resin filaments and reinforcing fiber filaments necessary for forming the composite material 90 are wound, a loader mechanism for drawing out the resin filaments and fiber filaments from these bobbins, a heater for heating the resin filaments drawn out by the loader mechanism to a temperature equal to or higher than the melting temperature, a cutter for cutting the fiber filaments drawn out in the same manner, a supply mechanism for supplying these filaments as the composite material 90 to the nozzle 25, a moving mechanism for moving the nozzle 25, a nozzle 25 for discharging the composite material 90, and a controller for performing drive control of these based on 3D data input from the generation device 10 via a LAN port or the like, and so on.

[0026] In this system configured as described above, by executing, by the generation device 10, the shaping information generation process described below with reference to FIG. 2, (1) the design related to mechanical requirements including the rigidity in the stacking direction of the three-dimensional shaped object M, and (2) the design related to the continuity of the fibers contained in the composite material 90 are facilitated, and these can be carried out (3) without requiring an enormous computational cost. FIG. 2 shows a flowchart representing the flow of the shaping information generation process executed by the generation device 10.

[0027] This shaping information generation process is performed by a software program (generation program) that can be processed by the generation device 10 being executed by the MPU or GPU of the generation device 10. This generation program is stored in the HDD or SSD of the generation device 10. Note that these MPU and GPU may correspond to the "first optimization means" and "second optimization means" described in the claims.

[0028] As shown in FIG. 2, in the modeling information generation process, first, the external shape information input process is performed in step S101. In this process, external shape information such as the specific external shape, external dimensions, and constraint conditions regarding mechanical deformation (hereinafter simply referred to as "deformation") of the three-dimensional object M to be modeled by the modeling apparatus 20 is acquired from the outside. This external shape information is input, for example, by the user of the present system via an input unit such as a keyboard or a pointing device provided in the generation apparatus 10.

[0029] Instead of (or in addition to) such information on the specific external shape of the three-dimensional object M, for example, information that can specify the design area and non-design area of the entire three-dimensional object M (information that does not represent a specific external shape) may be acquired from the outside. That is, the external shape information may be any information that is necessary for generating the information on the internal structure of the three-dimensional object M in the subsequent internal structure information generation process (S103).

[0030] As a more specific example of the three-dimensional object M, a basic model 100 of a cantilever beam (a beam with one end fixed and the other end free) having a rectangular plate shape is shown in FIG. 3. Therefore, the description will be made with reference to FIG. 3 as well. In FIG. 3, as a diagram showing an example of the basic model 100 of the cantilever beam, a plan view of the same model is shown in FIG. 3(A), a side view of the same model is shown in FIG. 3(B), and a geometric graph-like schematic diagram showing the displacement state of the same model is shown in FIG. 3(C). Each reference numeral shown in FIG. 3(C) is related to the graph 120 shown in FIG. 5(A).

[0031] As shown in FIG. 3(A), when forming a cantilever beam as a three-dimensional object M, as information on the outer shape and outer dimensions of the basic model 100, for example, a length of 80 mm in the longitudinal direction (X-axis direction), a length of 40 mm in the short-side direction (Y-axis direction), and a length of 7.2 mm in the height direction (Z-axis direction) are input from the keyboard or the like of the generation device 10, respectively. Further, as shown in FIGS. 3(B) and 3(C), for the basic model 100 of this cantilever beam, as a constraint condition regarding deformation when a load F of 50 N (Newton) is applied in the Z-axis direction (lamination direction) on the free end side, information for setting the maximum value θmax of the displacement angle on the fixed end side to, for example, 5 degrees is also input.

[0032] In FIG. 3(C), the graph-shaped one represented by the broken line indicates a state where no load F is applied to the free end of the basic model 100, and the graph-shaped one represented by the solid line indicates a state where a load F is applied to the free end in the Z-axis direction (see FIG. 3(B)). Note that such information on the outer shape and outer dimensions of the basic model 100 and information on the maximum value θmax of the displacement angle on the fixed end side are an example of information regarding mechanical requirements including the rigidity of the entire lamination direction of the cantilever beam 110, which is a specific three-dimensional object M of the basic model 100, and can correspond to the "first predetermined condition" described in the claims.

[0033] In the next step S103, internal structure information generation processing is performed. This processing automatically designs the internal structure by mechanically arranging plate walls or the like in the internal space of the basic model 100 according to a predetermined rule. For example, general-purpose topology optimization analysis software is used. In the present embodiment, the predetermined rule is information such as the outer shape information input by the outer shape information input processing (S101) and making the internal structure a lattice-like infill structure. The lattice-like infill structure is an internal structure in which, without solidifying the inside, a space and a partition for partitioning the space in a lattice shape are provided inside.

[0034] Through this internal structure information generation process, the basic model 100 of the cantilever beam is generated as a cantilever beam 110 of a structural model as shown in, for example, FIG. 4. FIG. 4 shows, as an example of the structural model of the cantilever beam 110, a plan view of the same model in FIG. 4(A), a side view of the same model in FIG. 4(B), and a perspective view of the same model in FIG. 4(C).

[0035] In this embodiment, the cantilever beam 110 is composed of outer wall elements 111, 112, 113 provided along the longitudinal direction (X-axis direction), inner wall element 114 and outer wall element 117 provided along the short-side direction (Y-axis direction), and inner wall elements 115 and outer wall elements 116 provided obliquely in both these directions. The outer dimensions of this cantilever beam 110 are set to a longitudinal length of 80 mm, a short-side length of 40 mm, and a height-direction length of 7.2 mm, similar to the basic model 100 described above. Also, the plate thicknesses of the outer wall elements 111 to 113, 116, 117 and the inner wall elements 114, 115 are set to 1.6 mm.

[0036] No wall elements or the like are formed in the respective ranges of the triangular shapes surrounded by the outer wall elements 111, 117 and the inner wall element 115, the triangular shapes surrounded by the outer wall element 113 and the inner wall elements 114, 115, and the triangular shapes surrounded by the outer wall elements 112, 116 and the inner wall element 114. Therefore, spaces are formed in these triangular ranges. Here, as an example of partitioning the internal space in a lattice pattern, a triangular lattice structure is illustrated, but any shape that can partition the space, such as a lattice structure in the shape of a square, pentagon, hexagon, or other polygon, or a closed curve shape such as a circle or ellipse, may also be used.

[0037] In the subsequent step S105, a lamination parameter assignment process is performed. In this process, for each of the wall elements 111 to 116 that constitute the structural model of the cantilever beam 110, which will be the subject of the lamination parameter optimization process in the next step S107, a lamination parameter ξ9 representing the out-of-plane bending stiffness of the laminated material is assigned. Note that since the outer wall element 117 is fixed to the outside as a fixed end, the assignment of the lamination parameter ξ9 is not performed. The lamination parameter ξ9 and the like are described in detail in the above-mentioned Non-Patent Document 4. In the present embodiment, the case of symmetric lamination where the lamination configuration of each of the wall elements 111 to 116 is symmetric with respect to the center in the lamination direction will be exemplified and described. In the case of symmetric lamination, since the optimization result for one side of the symmetry can be applied to the other side, only the lamination parameter ξ9 corresponding to the out-of-plane bending stiffness is assigned and optimized.

[0038] Here, among the 12 types of lamination parameters ξ1 to ξ 12 , for the sake of convenience of explanation, the case of assigning and optimizing the lamination parameter ξ9 corresponding to the out-of-plane bending stiffness will be exemplified and described. However, in the case of asymmetric lamination where the lamination configuration is not symmetric with respect to the center in the lamination direction, the lamination parameters ξ1 corresponding to the in-plane bending stiffness and ξ5 which is the coupling term of the in-plane and out-of-plane bending stiffnesses are also assigned and optimized to satisfy the conditions. Also, when considering the coupling terms of out-of-plane bending and torsion, those lamination parameters ξ 11 , ξ 12 may be assigned and optimized. Furthermore, in addition, the lamination parameters ξ1, ξ2 corresponding to the in-plane bending stiffness and the lamination parameters ξ3, ξ4 corresponding to the coupling terms of in-plane bending and torsion may be assigned and optimized respectively. When there are multiple types of lamination parameters such as ξ9, ξ 10 assigned to each of the wall elements 111 to 116, they are optimized so that all the assigned multiple types of lamination parameters satisfy the conditions.

[0039] In the present embodiment, as will be described later, since the layer with "carbon fiber" has the fiber orientation angle θ(u) set to 0 degrees and the layer without "carbon fiber" has the fiber orientation angle θ(u) set to 90 degrees, the lamination parameters ξ3, ξ4, ξ11 , ξ 12 always has a value of 0, and the lamination parameters ξ2, ξ 10 always has a value of 1.0. Therefore, among the lamination parameters, the variables are ξ1, ξ9. Assuming a symmetric lamination case, only the lamination parameter ξ9 corresponding to the out-of-plane bending stiffness of one side (upper side) of the laminate is assigned and optimized. In the case of an asymmetric laminate, the lamination parameters ξ3, ξ4, ξ7, ξ8, ξ 11 , ξ 12 always has a value of 0, and the lamination parameters ξ2, ξ6, ξ 10 always has a value of 1.0, so the lamination parameters ξ1, ξ5, ξ9 become variables.

[0040] More specifically, for example, as shown in Fig. 5(A), for the edges 121 to 126 of the graph 120 when the cantilever beam 110 is represented in a geometric graph form, the lamination parameters ξ 9a , ξ 9b , ξ 9c , ξ 9d , ξ 9e , ξ 9f are respectively assigned. The lamination parameters for the entire structural model of the cantilever beam 110 are represented as [ξ 9a , ξ 9b , ξ 9c , ξ 9d , ξ 9e , ξ 9f . Note that the symbols 131 to 135 respectively indicate the nodes representing the intersections or endpoints of the edges 121 to 126.

[0041] The lamination parameters for the entire structural model of the cantilever beam 110 represented in this way are optimized by the lamination parameter optimization process according to the following step S107. The purpose of the optimization is, for example, when a load F of 50 N is applied in the Z-axis direction (lamination direction) to the free end of the basic model 100 of the cantilever beam 110, under the boundary conditions, the displacement angle at the tip of the free end of the cantilever beam 110 is below the specified value (θmax = 5 degrees), and the displacement amount at the tip is maximized, the lamination parameters [ξ 9a , ξ 9b , ξ 9c , ξ9d , ξ 9e , ξ 9f is to obtain the combination of

[0042] In the lamination parameter optimization process of step S107, the lamination parameters [ξ of the entire structural model of the cantilever beam 110 are explored and optimized using an evolutionary calculation algorithm. In this embodiment, as the evolutionary calculation algorithm, for example, a genetic algorithm (Genetic Algorithm, hereinafter sometimes referred to as "GA") is used. 9a , ξ 9b , ξ 9c , ξ 9d , ξ 9e , ξ 9f . In this embodiment, the optimization conditions by GA are set, for example, as follows: population size: 250, number of generations: 800, number of elite individuals saved: 1, crossover: Simulated Binary Crossover, mutation: Parameter-based mutation, crossover probability: 0.9, mutation probability: 0.1. Also, the material properties are set, for example, as follows: matrix elastic modulus: 1.25 GPa, matrix Poisson's ratio: 0.4, fiber elastic modulus: 135 GPa, fiber Poisson's ratio: 0.35. The optimization by this process is performed, for example, 20 times under the generation of random numbers generated software-wise, but it may be set to perform the maximum number of times within the allowable calculation cost range.

[0043] In addition, in order to appropriately evaluate the reliability of the optimization algorithm used in the lamination parameter optimization process, for the above-mentioned specified value of the tip displacement angle (θmax = 5 degrees), the lamination parameters [ξ

[0044] are fully explored and compared with the results. The full exploration is performed for ξ corresponding to each of the edges 121 to 126 9a , ξ 9b , ξ 9c , ξ 9d , ξ 9e , ξ 9f . 9a , ξ 9b , ξ 9c , ξ 9d , ξ 9e , ξ9f Since all six lamination parameters take continuous values in the range of -1.0 to 1.0, -1.0 to 1.0 was divided into 17 equal parts at intervals of 0.125.

[0045] That is, since the wall elements to be searched are six edges 121 to 126, the total number of searches is 17 6 = 24137569. As a result of such a full search, the lamination parameters (hereinafter referred to as "optimized lamination parameters") [ξ 9a_optim , ξ 9b_optim , ξ 9c_optim , ξ 9d_optim , ξ 9e_optim , ξ 9f_optim after optimization for the six edges 121 to 126 became [-1.0, 0.75, -0.875, -1.0, -0.375, 0.75], and the displacement amount at the tip of the cantilever beam 110 in this case was 5.33 mm. When this is represented by the shade of color, for example, it is represented as a map shown in Fig. 5(B).

[0046] The color of this map indicates that the darker (closer to black) the color, the closer the value of the lamination parameter is to 1.0 and the higher the rigidity, and the lighter (closer to white) the color, the closer the value of the lamination parameter is to -1.0 and the lower the rigidity. Therefore, in the optimized graph 120 where the lamination parameters are optimized, the colors of edges 122 and 126 are the darkest and the values of the lamination parameters ξ 9b_optim , ξ 9f_optim (0.75) are also the largest, and the colors of edges 121 and 124 are the lightest and the values of the lamination parameters ξ 9a_optim , ξ 9d_optim (-1.0) are also the smallest.

[0047] For the results of such a full search, the following results were obtained in the optimization performed 20 times by the lamination parameter optimization process. The number of times the parameters with the same numerical sequence as the optimized lamination parameters obtained by the full search were obtained was 2 times, the optimized fitness obtained by the full search was 0.188, the average fitness obtained by GA was 0.190, and the standard deviation of the search results obtained by GA was 5.84×10 -4It has become. Note that the displacement amount at the tip of the cantilever beam 110 in the average fitness by GA is 5.28 mm.

[0048] From these results, when the six lamination parameters [ξ 9a , ξ 9b , ξ 9c , ξ 9d , ξ 9e , ξ 9f for the edges 121 to 126 are optimized by the lamination parameter optimization process, the mechanical structure of the cantilever beam 110 that results in a displacement amount within an error of approximately -0.9% (= ((5.28 / 5.33) - 1) × 100) with respect to the displacement amount at the tip of the cantilever beam 110 composed of the edges 121 to 126 to which the optimal lamination parameter [ξ 9a_optim , ξ 9b_optim , ξ 9c_optim , ξ 9d_optim , ξ 9e_optim , ξ 9f_optim is applied is obtained on average.

[0049] Thus, the lamination parameter optimization process (S107) optimizes the rigidity of the cantilever beam 110, enables complex deformations to occur by combining members of different hardnesses, and can determine the hardness (lamination parameter) that can generate the function (rigidity) required for the cantilever beam 110 (a process for optimizing rigidity).

[0050] In the subsequent step S109, a fiber arrangement optimization process is performed. In this process, the continuous carbon fiber arrangement that can realize the optimal lamination parameter [ξ 9a_optim , ξ 9b_optim , ξ 9c_optim , ξ 9d_optim , ξ 9e_optim , ξ 9f_optim optimized by the lamination parameter optimization process (S107) is searched for and optimized using an evolutionary calculation algorithm. As the evolutionary calculation algorithm, for example, GA is used. The purpose of optimization in this embodiment is to reduce the number of cuts of continuous carbon fibers and improve the continuity of carbon fibers.

[0051] Incidentally, such a lamination parameter ξ9 represents the out-of-plane rigidity of the laminate, and in this embodiment, it represents the degree of hardness with respect to the lamination direction (Z-axis direction) obtained by laminating a layer containing carbon fibers as a continuous value of -1.0 (low rigidity) or more and 1.0 (high rigidity) or less. On the other hand, as disclosed in the above Non-Patent Document 1, the lamination parameter ξ9 is also a function composed of the fiber orientation angle θ(u) of the fibers to be laminated, and is determined by the distribution θ(u) of the fiber orientation angle. Therefore, in this embodiment, the lamination parameter ξ9 representing the out-of-plane rigidity of the laminate is expressed at intervals of 0.050 from -1.0 to 1.0 (see Fig. 6(B)), and the presence or absence of carbon fibers in each layer to be laminated is set using this fiber orientation angle θ(u).

[0052] For example, when running continuous carbon fibers along the longitudinal direction of each wall element 111 to 116 when laminating a layer containing carbon fibers, the layer with "carbon fibers present" has the fiber orientation angle θ(u) set to 0 degrees, and the layer with "no carbon fibers" has the fiber orientation angle θ(u) set to 90 degrees. Thereby, the presence or absence of carbon fibers in each layer is expressed, and as the gene information of the chromosome that is the search target by GA, "carbon fibers present" is represented by "1", and "no carbon fibers" of only resin is represented by "0". This gene information is stored as the gene of the chromosome provided for each layer.

[0053] For example, as shown in the enlarged view within the dashed-dotted line in Fig. 6(A), when the outer wall element 112 of the cantilever beam 110 is composed of 20 layers, by expressing the presence or absence of carbon fibers as "1" and "0" for each layer, it can be represented as [00011…10] in order from the upper layer 112a to the middle layer 112f of the outer wall element 112. In this embodiment, for example, as described above, it is configured by symmetric lamination that is symmetric with respect to the center in the lamination direction and is divided into upper and lower parts, and a chromosome is configured with 10 genes for the 10 upper layers (the tip side of the Z-axis arrow). Thereby, for the wall elements 111 to 116, it becomes possible to represent them as [0000000000], [1111010110], [0000010100], [0000000010], [1000010000], [1111010110].

[0054] By setting the presence or absence of carbon fibers for each layer in this way and combining a fiber layer with "carbon fibers" and a resin layer with "no carbon fibers", it becomes possible to obtain a wall element having rigidity corresponding to the intended value of the lamination parameter. Further, in the case of a symmetric lamination where the lamination structure is symmetric with respect to the center in the lamination direction, in each of the wall elements 111 to 116, by dividing the total number of laminations into two in the lamination direction, the number of genes constituting the chromosome is reduced, enabling reduction of the calculation cost.

[0055] As shown in FIG. 6(B), there may be a case where there are a plurality of combinations that result in the same value depending on the value of the lamination parameter for such a combination of a fiber layer and a resin layer. For example, in the range where the value of the lamination parameter is -0.45 or more and less than 0.70, there are 20 or more combinations of a fiber layer and a resin layer where the value of the lamination parameter is within the range of ±0.25, whereas in the ranges where the value of the lamination parameter is -1.0 or more and less than -0.55 or 0.90 or more and 1.0 or less, the number is 10 or less.

[0056] Therefore, for example, as shown in FIG. 6(C), for the edge 126 where the lamination parameter is around 0.1, it is possible to select from among nearly 50 (or types) of combinations of a fiber layer and a resin layer (inside the one-dot chain line in FIG. 6(B)), and for the edge 122 where the lamination parameter is close to 1.0, it is possible to select from among 9 (or types) of combinations of a fiber layer and a resin layer (inside the two-dot chain line in FIG. 6(B)).

[0057] Therefore, when the value of the lamination parameter is the same (for example, 0.75), an arrangement in which carbon fibers (composite material 90) can be continuously drawn by the shaping device 20, for example, carbon fibers are run so that adjacent wall elements such as the outer wall element 112 of the edge 122 and the outer wall element 116 of the edge 126 are continuously connected, reducing the number of cuts of the carbon fibers, thus making it possible to maintain the continuity of the fibers.

[0058] That is, when the shaping device 20 performs laminated shaping on the cantilever beam 110, a path for moving the nozzle 25 is set so that the composite material 90 containing carbon fibers discharged from the nozzle 25 is laminated in a "one-stroke" manner along the longitudinal direction of each wall element 111 to 116. As a result, unnecessary cutting of carbon fibers is eliminated, and it becomes possible to maintain the continuity of the fibers.

[0059] Therefore, in this embodiment, in the fiber arrangement optimization process (S109), the arrangement of continuous carbon fibers is searched for and optimized by GA using the objective function φ shown in the following formula (1).

[0060] φ = n path ×J + (l path / l all )×K …(1) However, n path is the number of paths and is obtained by the following formula (2). Also, l path is the length of the path, l all is the total length of all edges, and J and K are weighting coefficients given to balance the evaluation weights of the first term (number of paths) and the second term (length of the path).

[0061] n path = N ep / 2 …(2) However, N ep is the number of specific nodes among the nodes (end points) of each edge (side) containing carbon fibers, where the number of edges connected to each of them is odd. This formula (2) can obtain the minimum number of strokes required to continuously draw a graph that is not a closed loop composed of a plurality of connected edges containing carbon fibers. That is, for a graph that can be drawn in one stroke, n path = 1.

[0062] The first term [n path×J] represents the number of paths through which carbon fibers can be continuously connected in each of the wall elements 111 to 116 configured to include carbon fibers, and the value of the weighting coefficient J is set according to the importance of the evaluation weight. And the value of this first term, that is, the number of paths, is such that the smaller the value (the fewer the paths), the longer the length of one path, and the larger the number of paths, the shorter the length of one path.

[0063] Also, the second term [(l path / l all )×K] in formula (1) represents the ratio of the length of the path to the total length of all edges, that is, the longest path length, and the value of the weighting coefficient K is set according to the importance of the evaluation weight. The value of this second term, that is, the length of the path, is such that the smaller the value (the shorter the path), the larger the number of paths, and the larger the value (the longer the path), the smaller the number of paths.

[0064] The optimization algorithm for combinations such as GA used in this embodiment is optimized to select those with a smaller value of the objective function φ. Therefore, for example, when preferentially selecting those with a smaller number of paths than the path length, the evaluation weight of the first term n path is made heavier, and the evaluation weight of the second term (l path / l all ) is made lighter. That is, the coefficient J> coefficient K is set (for example, J = 10, K = 1). On the contrary, when preferentially selecting those with a shorter path length than the number of paths, the evaluation weight of the second term (l path / l all ) is made heavier, and the evaluation weight of the first term n path is made lighter. That is, the coefficient J < coefficient K is set (for example, J = 1, K = 10).

[0065] Thus, the number of paths according to the first term n path and the second term (l path / l allRegarding which of the path lengths according to ( ) to preferentially select by setting weights using coefficients J and K, it is determined based on performance aspects such as the shaping speed of the shaping device 20, cost aspects such as the composite material 90 to be used and the cost of carbon fibers included therein, and characteristic aspects specific to the object to be shaped such as the structure and size of the three-dimensional shaped object M.

[0066] For example, in terms of the performance of the shaping device 20, when the length of time to cut carbon fibers (the speed of the shaping speed) does not significantly affect the shaping speed regardless of the number of paths, or in terms of the structure of the three-dimensional shaped object M, when the presence of short carbon fiber lengths has little impact on mechanical strength, it is more advantageous in terms of cost for the carbon fiber length included in the composite material 90 to be shorter. This is because carbon fibers are more costly than general-purpose resin materials, and it is considered more cost-effective to reduce their usage amount. In such a case, the evaluation weight of the second item (path length) is increased, and the objective function φ is configured to preferably select a path with a short path length as much as possible.

[0067] Also, in terms of the structure of the three-dimensional shaped object M, when shaping a large-sized one or one with strict functional condition settings, it is more advantageous to reduce the number of cuts and increase the carbon fiber length. In such a case, the evaluation weight of the first item (number of paths) is increased, and the objective function φ is configured to preferably select a path with a small number of paths and approaching a one-stroke drawing as much as possible. Generally, it is more convenient in terms of cost for the carbon fibers to be used in a smaller (shorter) amount. When the number of paths is large, it takes time to cut the carbon fibers, and the mechanical strength also decreases. Therefore, a path configuration that can be drawn in one stroke is more desirable than a path configuration that requires three strokes.

[0068] Note that the weighting coefficients J and K that can control such evaluation weights are, for example, stored in advance in an auxiliary storage unit such as an HDD or SSD that constitutes the generation device 10 as predetermined default values such as J = 10 and K = 1, or are preset in the generation program. However, in this embodiment, it is also configured such that the user can input and change each value from the outside via an input unit such as the keyboard of the generation device 10.

[0069] The operation of changing the weighting coefficients J and K may be configured to be performed, for example, in the external shape information input process (S101) shown in FIG. 2. Further, in a task, thread, or process that is executed separately from the three-dimensional modeling information generation process shown in FIG. 2, a software program or control process executed by the generation device 10 may be configured to perform the operation of changing the weighting coefficients J and K. Note that the weighting coefficients J and K are an example of information regarding the continuity of the carbon fibers constituting the composite material 90 and may correspond to the "second predetermined condition" described in the claims.

[0070] The conditions for optimization by GA in the fiber arrangement optimization process (S109) of the present embodiment are set, for example, to population size: 100, number of generations: 200, number of elite individuals saved: 1, crossover: single-point crossover, mutation: substitution, crossover probability: 0.9, and mutation probability: 0.1. Note that the material properties, random numbers, and number of optimizations are the same as the conditions set in the above-described lamination parameter optimization process (S107).

[0071] Note that in order to appropriately evaluate the reliability of the optimization algorithm used in the fiber arrangement optimization process, a full search of the fiber arrangement was performed for the laminated structure of the optimal solution obtained with the optimal lamination parameters [ξ 9a_optim , ξ 9b_optim , ξ 9c_optim , ξ 9d_optim , ξ 9e_optim , ξ 9f_optim =[-1.0, 0.75, -0.875, -1.0, -0.375, 0.75], and the result was compared. The full search was performed by dividing 21 times at intervals of 0.05 for six lamination parameters that take continuous values in the range of -1.0 to 1.0, similar to the case of evaluating the reliability of the optimization algorithm in the above-described lamination parameter optimization process (S107).

[0072] As a result of this exhaustive search, the chromosomes corresponding to each of the wall elements 111 to 116 are [0000000000], [1111010110], [0000010100], [0000000010], [1000010000], [1111010110]. The number of paths is 7, and the length of the path is 869.1 mm.

[0073] For the results of such an exhaustive search, the following results were obtained in the optimization performed 20 times by the fiber placement optimization process. For the wall elements 111 to 116, the number of times the same chromosome configuration as the chromosome obtained by the exhaustive search was obtained was 4 times. The optimal fitness obtained by the exhaustive search was 50.3, and the average fitness obtained by the GA was 51.4. The standard deviation of the search results obtained by the GA was 3.06.

[0074] From these results, it was found that a highly reliable result can be obtained with a small computational cost of 100 individuals and 200 generations compared to the case of optimization by GA in the comparative example described below for supplementary explanation. Thus, the effect obtained by performing optimization by dividing the lamination parameters for each of the wall elements 111 to 116 could also be confirmed.

[0075] As a supplementary explanation, the case of optimization by GA in the comparative example is illustrated. In this comparative example, the fiber placement is optimized by GA as a chromosome of a one-dimensional array. Therefore, for example, when the fiber placement for the wall elements 111 to 116 is composed of [0000000000], [1111010110], [0000010100], …, [1111010110], the fiber placement in the state where all these wall elements are connected is configured as the chromosome [000000000011110101100000010100…1111010110]. For this chromosome, optimization was performed by GA for two patterns where the number of one-sided layers in the upper half of each of the wall elements 111 to 116 is 10 layers and 20 layers.

[0076] The optimization conditions for this comparative example were set, for example, as follows: population size: 250, number of generations: 800, number of elite individuals saved: 1, crossover: single-point crossover, mutation: substitution, crossover probability: 0.9, mutation probability: 0.1. Note that the material properties, random numbers, and number of optimizations are the same as the conditions set in the aforementioned fiber arrangement optimization process (S109).

[0077] Optimization was performed 20 times, and the following results were obtained for the minimum fitness, average fitness, standard deviation, and 1% average generation. Note that the 1% average generation is the average value of the generations at which the error with respect to all search results reaches 1% or less, and the smaller the value, the better. Note that "this embodiment" in the following results refers to the GA optimization method (fiber arrangement optimization process (S109)) in this embodiment.

[0078] This embodiment | Comparative example (number of layers 10) | Comparative example (number of layers 20) Minimum fitness: 0.1871 | 0.1871 | 0.1872 Average fitness: 0.1873 | 0.1876 | 0.1877 Standard deviation: 4.19×10 -4 | 3.24×10 -4 | 4.40×10 -4 1% average generation: 68.9 | 23.7 | 129.7

[0079] From the above results, when comparing the case of this embodiment with the cases of the two comparative examples, although no superiority can be confirmed regarding the minimum fitness and average fitness, the value of the 1% average generation increases with the increase in the number of layers in the two comparative examples compared to the case of this embodiment where it is independent of the number of layers. That is, it was confirmed that the convergence speed depends on the number of stacked layers.

[0080] In this way, the fiber arrangement optimization process (S109) enables the search for the optimal arrangement of continuous carbon fibers by simultaneously evaluating, as evaluation items within the same objective function, the number and length of the paths for moving the nozzle 25 of the modeling device 20, that is, the paths for laminating the composite material 90 containing carbon fibers. Also, by optimizing the arrangement of carbon fibers, it is possible to determine the most realistic and suitable arrangement of carbon fibers for manufacturing and using in order to achieve the hardness (rigidity) of the cantilever beam 110. In the present embodiment, the process of optimizing the carbon fiber arrangement by this fiber arrangement optimization process (S109) and the process of optimizing the rigidity by the above-described lamination parameter optimization process (S107) enable the rational manufacturing of the functions required for the three-dimensional shaped object M such as the cantilever beam 110.

[0081] In the last step S111, a modeling information output process is performed. In this process, layer configuration information of wall elements that combine a fiber layer with "carbon fibers" and a resin layer without "carbon fibers" is generated based on the information of each chromosome [0000000000], [1111010110], [0000010100], [0000000010], [1000010000], [1111010110] corresponding to each of the wall elements 111 to 116 optimized by the above-described fiber arrangement optimization process (S109). Also, for the outer wall element 117 that is not an optimization target, information constituting the entire layer with a resin layer, for example, is generated as the layer configuration information of the wall element.

[0082] The three-dimensional modeling information regarding each of the wall elements 111 to 117 of the cantilever beam 110 generated in this way is output to the modeling device 20 via the output unit (LAN port, USB port, etc.) of the generation device 10 after being converted into a file format such as STL or OBJ. As a result, since the three-dimensional modeling information necessary for laminating and modeling the three-dimensional shaped object M such as the cantilever beam 110 is output from the generation device 10 to the modeling device 20, the modeling device 20 can laminate and model the cantilever beam 110 with the composite material 90 containing carbon fibers.

[0083] As described above, in the generation device 10 that constitutes the 3D modeling system of the present embodiment, output information 60 (3D modeling information) used for manufacturing a three-dimensional model M of a cantilever beam 110, which is formed by laminating a composite material 90, is generated by a modeling information generation process and output to the modeling device 20. In the lamination parameter optimization process (S107) of this modeling information generation process, lamination parameters ξ 9a ~ξ 9f for each of the edges 121 to 123, 126 that constitute the outer shape of the three-dimensional model M and the edges 124, 125 that constitute the internal structure of the three-dimensional model M are optimized based on input information 50 (first predetermined condition) input to the generation device 10 regarding mechanical requirements including the rigidity in the entire lamination direction (Z-axis direction) of the three-dimensional model M. Further, in the fiber arrangement optimization process (S109) that constitutes the modeling information generation process, the optimized lamination parameters ξ 9a_optim ~ξ 9f_optim for each layer that satisfy the are optimized based on input information 50 (second predetermined condition) input to the generation device 10 regarding the continuity of the carbon fibers that constitute the composite material 90.

[0084] As a result, the combination of lamination parameters ξ 9a ~ξ 9f for each of the edges 121 to 126 that constitute the three-dimensional model M is optimized based on the input information 50 input to the generation device 10, and the optimized lamination parameters ξ 9a_optim ~ξ 9f_optim for the optimal combination at the edges 121 to 126 are also optimized based on the input information 50 and the like. Such lamination parameters ξ 9a ~ξ 9fBy using etc., it is possible to perform calculations without depending on the number of layers of the three-dimensional object M, and since the rigidity in the stacking direction (Z-axis direction) can be linearly calculated with respect to the stacking parameters, for example, compared to the technology disclosed in Non-Patent Document 1 above, it becomes possible to significantly reduce the calculation cost required when designing the carbon fiber arrangement of the composite material 90. Therefore, in the three-dimensional object M manufactured by the additive manufacturing method, (1) design related to mechanical requirements including the rigidity of the entire stacking direction (Z direction) of the three-dimensional object M and (2) design related to the continuity of the carbon fibers included in the composite material 90 can be easily performed, and (3) it can be performed without requiring enormous calculation costs.

[0085] Note that in the 3D modeling system of the present embodiment described above, in the stacking parameter optimization process (S107) and the fiber arrangement optimization process (S109) of the modeling information generation process executed by the generation device 10, the case of using a genetic algorithm as an example of an evolutionary calculation algorithm has been illustrated and described. However, it is not limited to this as long as it is a metaheuristic search method. For example, search methods using swarm intelligence such as the ant colony optimization method, artificial bee colony algorithm, particle swarm optimization method, firefly algorithm, bat algorithm, cuckoo search, harmony search, etc. may be used. Also, machine learning methods applied to combinatorial optimization problems such as probabilistic optimization methods represented by Bayesian optimization may be used.

[0086] Also, in the 3D modeling system of the present embodiment described above, the case where the information such as the outer shape of the modeling information generation process executed by the generation device 10 is input from an input unit such as a keyboard or a pointing device provided in the generation device 10 has been illustrated and described. However, for example, the generation device 10 may be configured such that an output unit such as a LAN port or a USB port provided in the generation device 10 functions as another input unit, and through this, information such as the outer shape can be input from another information processing device (a personal computer, a portable information terminal device such as a smartphone or a mobile phone, etc.) or a USB memory device.

[0087] Furthermore, in the 3D modeling system of the present embodiment described above, the case where the three-dimensional modeling information generated by the generation device 10 is directly output (input) to the modeling device 20 via an output unit such as a LAN port or a USB port has been exemplified and described. However, for example, such three-dimensional modeling information may be indirectly output (input) to the modeling device 20 via, for example, other information processing devices (such as personal computers, portable information terminal devices such as smartphones and mobile phones), USB memory devices, or a wide-area data communication network such as the Internet.

[0088] Also, in the 3D modeling system of the present embodiment described above, in the modeling information generation process executed by the generation device 10, the case where the lamination parameters regarding the out-of-plane rigidity of the three-dimensional object M are optimized by the lamination parameter optimization process (S107), and further the fiber arrangement regarding the arrangement of continuous carbon fibers is optimized by the fiber arrangement optimization process (S109) has been exemplified and described. However, the optimization of the lamination parameters and the optimization of the continuous carbon fiber arrangement by the three-dimensional modeling information generation method, generation device, and generation program of the present invention are not limited to those related to the out-of-plane rigidity. That is, in addition to the out-of-plane rigidity, the lamination parameters and the continuous carbon fiber arrangement regarding the in-plane rigidity of the three-dimensional object M can also be optimized by the same evolutionary calculation algorithm as described above.

[0089] As described above, specific examples of the present invention have been described in detail, but these are merely examples and do not limit the scope of the claims. The technology described in the claims includes various modifications or changes of the above-described specific examples. Also, the technical elements described in this specification or the drawings exhibit technical utility alone or in various combinations, and are not limited to the combinations described in the claims at the time of filing. Furthermore, the technology exemplified in this specification or the drawings achieves a plurality of purposes simultaneously, and achieving one of these purposes itself has technical utility. Note that the descriptions in parentheses in the [Description of Reference Numerals] column can clarify the correspondence between the terms used in the above-described embodiments and the terms described in the claims.

Description of Reference Numerals

[0090] 10… Generation device (device for generating three-dimensional modeling information) 20… Modeling device 25… Nozzle 50… Input information (first predetermined condition, second predetermined condition) 60… Output information (three-dimensional modeling information) 90… Composite material (continuous fiber composite material) 100, 200… Basic model 110… Cantilever beam (three-dimensional modeled object) 111, 112, 113, 116, 117… Outer wall element (shell part) 114, 115… Inner wall element (infill part) 120… Graph 121, 122, 123, 124, 125, 126… Edge 131, 132, 133, 134… Node J, K… Weighting coefficient (second predetermined condition) M… Three-dimensional modeled object S107… Lamination parameter optimization process (first step) S109… Fiber arrangement optimization process (second step) ξ1, ξ2, ξ3, ξ4, ξ5, ξ6, ξ7, ξ8, ξ9, ξ 10 , ξ 11 , ξ 12 … Lamination parameter ξ 9a , ξ 9b , ξ 9c , ξ 9d , ξ 9e , ξ 9f … Lamination parameter ξ 9a_optim , ξ 9b_optim , ξ 9c_optim , ξ 9d_optim , ξ 9e_optim , ξ 9f_optim … Optimized lamination parameter

Claims

1. A method for generating three-dimensional modeling information used in manufacturing a three-dimensional object formed by laminating a continuous fiber composite material (hereinafter referred to as "composite material"), a first step of optimizing a combination of lamination parameters corresponding to each lamination direction of a shell part constituting the outer shape of the three-dimensional object and an infill part constituting the internal structure of the three-dimensional object based on a first predetermined condition regarding mechanical requirements including the rigidity of the three-dimensional object in the lamination direction; a second step of optimizing the arrangement of the composite material for each layer that satisfies the optimal combination of lamination parameters obtained in the first step based on a second predetermined condition regarding the continuity of the fibers constituting the composite material; The method for generating three-dimensional modeling information, characterized by including the above.

2. The method for generating three-dimensional modeling information according to Claim 1, wherein the first predetermined condition is based on the outer shape and the mechanical strength or mechanical function required for the three-dimensional object.

3. The method for generating three-dimensional modeling information according to Claim 1 or 2, wherein the second predetermined condition is based on the number of paths for arranging the composite material when laminating each layer and the length of the paths.

4. A device for generating three-dimensional modeling information used in manufacturing a three-dimensional object formed by laminating a continuous fiber composite material (hereinafter referred to as "composite material"), a first optimization means for optimizing a combination of lamination parameters corresponding to each lamination direction of a shell part constituting the outer shape of the three-dimensional object and an infill part constituting the internal structure of the three-dimensional object based on a first predetermined condition regarding mechanical requirements including the rigidity of the three-dimensional object in the lamination direction; a second optimization means for optimizing the arrangement of the composite material for each layer that satisfies the optimal combination of lamination parameters obtained by the first optimization means based on a second predetermined condition regarding the continuity of the fibers constituting the composite material; The device for generating three-dimensional modeling information, characterized by comprising the above.

5. A program for generating three-dimensional modeling information for causing a computer to function as the device for generating three-dimensional modeling information according to Claim 4.

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