Mitsubishi Heavy Industries Limited

Tooru Shitani

Toshio Abe

Kiyoka Takagi

Sota Kamo

Takayuki Nomura

Satoshi Kodama

Masahiro Kashiwagi

Yoshinori Nonaka

Takaaki Yumitori

Kosuke Takahashi

Shinya Honda

Sae Obata

A wing used for an aircraft includes a configuration member formed of a composite material. The configuration member is divided into a plurality of regions along a surface thereof. The plurality of regions include a first region formed of the composite material of a high strength type, and a second region formed of the composite material of a high elasticity type having higher rigidity than the high strength type. The first region includes any region closest to a wing end side out of the plurality of regions, and the second region includes a region closest to the wing end side and a trailing edge side out of the plurality of regions.

Wing and wing design method

A composite material includes stacked reinforced fiber substrates and has a thickness-varying part whose thickness in a stacking direction changes from a large thickness to a small thickness. The reinforced fiber substrate that has the drop-off portion and is positioned between a base substrate and a cover substrate in the stacking direction is set as a cut substrate. Stress analysis is performed on the base substrate, the cut substrate, and the cover substrate to calculate an evaluation value concerning stress on the cut substrate. A reinforced fiber substrate in the thickness-varying part is set at the cut substrate, based on the calculated evaluation value.

Method of designing composite material, method of evaluating composite material, and composite material

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.

Method for designing composite material and composite material

A composite structure includes a stepped portion formed by laminating a plurality of plies with end surfaces thereof being shifted from each other. The composite structure includes a body portion which includes a first structure portion where a first ply is laminated on a top layer of the first structure portion, a second structure portion where a second ply is laminated on a top layer of the second structure portion, and the stepped portion disposed between the first structure portion and the second structure portion, the second ply being positioned at a distance from the first ply in a lamination direction, and a first cover ply which includes a covering portion covering the stepped portion, one end portion, and the other end portion and is formed so as to cover only a part of a surface of the first ply or a part of a surface of the second ply.

Composite structure

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Tokyo, Japan

Tooru Shitani