Method for designing composite material and composite material

Patent metadata

Field	Value
Publication number	US-11065831-B2
Application number	US-201816057099-A
Country	US
Kind code	B2
Filing date	Aug 7, 2018
Priority date	Aug 9, 2017
Publication date	Jul 20, 2021
Grant date	Jul 20, 2021

Abstract

A computer-implemented method is for designing a composite material in which reinforcement fiber base materials are laminated. The composite material includes a hole extending in a lamination direction of the reinforcement fiber base materials and a reinforcement part provided around the hole. The method includes calculating a strain value generated in the composite material based on design factors and a predetermined load condition, the design factors including a shape of the hole, a shape of the reinforcement part, and an orientation angle of each of the reinforcement fiber base materials in respective layers of the reinforcement part; and optimizing the design factors based on a genetic algorithm such that the calculated strain value tends to decrease.

First claim

The invention claimed is:

1. A computer-implemented method for designing a composite material in which reinforcement fiber base materials are laminated, the composite material including a hole extending in a lamination direction of the reinforcement fiber base materials and a reinforcement part provided around the hole, the method comprising:
calculating a strain value generated in the composite material based on design factors and a predetermined load condition, the design factors including a shape of the hole, a shape of the reinforcement part, and an orientation angle of each of the reinforcement fiber base materials in respective layers of the reinforcement part;
optimizing the design factors based on a genetic algorithm such that the calculated strain value at a rim of the hole and the reinforcement part tends to decrease;
the genetic algorithm including:
generating a piece of genetic information on the shape of the hole, a piece of genetic information on the shape of the reinforcement part, and a piece of genetic information on the orientation angle according to a predetermined limiting condition to generate a plurality of individuals having the different pieces of genetic information;
calculating the strain value generated in the composite material under the predetermined load condition based on an outer peripheral shape of the outermost layer of the reinforcement part in one quadrant for each of the individuals, wherein the outer peripheral shape of the outermost layer of the reinforcement part in the one quadrant is determined by interpolating a first reinforcement part defining point, a second reinforcement part defining point, and a third reinforcement part defining point according to the predetermined limiting condition that is an allowable range;
sequentially selecting at least two individuals, one of the at least two individuals having smallest strain values relative to other individuals;
genetically manipulating the pieces of genetic information using the selected individuals to newly generate individuals having the different genetic information; and
calculating, when a predetermined condition is met while repeatedly performing the calculating of the strain value and the genetically manipulating on the individuals generated at the genetically manipulating, an individual having the smallest strain value among the individuals as an optimal solution;

and manufacturing the composite material based on the optimized design factors,
wherein the outer peripheral shape of an outermost layer of the reinforcement part includes the first reinforcement part defining point, the second reinforcement part defining point, and the third reinforcement part defining point in one quadrant in an X-Y coordinate system orthogonal to the lamination direction,
the first reinforcement part defining point is a preset coordinate point on a Y-axis,
the second reinforcement part defining point is a coordinate point neither on an X-axis nor on the Y-axis,
the third reinforcement part defining point is a coordinate point on the X-axis, and
the piece of genetic information on the shape of the reinforcement part is information on an X-coordinate of the second reinforcement part defining point, a Y-coordinate of the second reinforcement part defining point, and an X-coordinate of the third reinforcement part defining point.

2. The computer-implemented method according to claim 1 , wherein
each of the individuals includes the piece of genetic information on the shape of the hole, the piece of genetic information on the shape of the reinforcement part, and the piece of genetic information on the orientation angle, and
the method further comprises calculating optimal solutions for the shape of the hole, the shape of the reinforcement part, and the orientation angle en masse.

3. The computer-implemented method according to claim 1 , wherein
each of the individuals is one of an individual for the piece of genetic information on the shape of the hole, an individual for the piece of genetic information on the shape of the reinforcement part, and an individual for the piece of genetic information on the orientation angle, and
the method further comprises calculating optimal solutions in the order of the shape of the hole, the shape of the reinforcement part, and the orientation angle.

4. The computer-implemented method according to claim 1 , wherein
the shape of the hole includes a first hole defining point, a second hole defining point, and a third hole defining point in one quadrant in an X-Y coordinate system orthogonal to the lamination direction,
the first hole defining point is a preset coordinate point on a Y-axis,
the second hole defining point is a coordinate point neither on an X-axis nor on the Y-axis,
the third hole defining point is a coordinate point on the X-axis,
the piece of genetic information on the shape of the hole is information on an X-coordinate of the second hole defining point, a Y-coordinate of the second hole defining point, and an X-coordinate of the third hole defining point, and
the calculating the strain value generated in the composite material under the predetermined load condition further includes
interpolating the first hole defining point, the second hole defining point, and the third hole defining point to calculate the shape of the hole in the one quadrant for each of the individuals, and
calculating the strain value generated in the composite material based on the calculated shape of the hole.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Kamo Sota
• Takagi Kiyoka
• Shitani Tooru
• Abe Toshio
• Honda Shinya

Classifications

• G06F30/17 Primary

  Mechanical parametric or variational design · CPC title

• G06F30/00

  Computer-aided design [CAD] · CPC title

• G06F2113/26

  Composites · CPC title

• B29C70/54 Primary

  Component parts, details or accessories; Auxiliary operations {, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing} · CPC title