Abstract: A diffused light control sheet includes: a louver layer on which light-transmitting zones and light-shielding zones are arranged alternately; a transparent protective layer disposed on a first face of the louver layer; and a light-diffusing layer disposed on a second face of the louver layer, in which the light-diffusing layer has a haze of 93% or more as measured in accordance with JIS K 7136 (2000).

Abstract: The disclosed method can manufacture a thick-walled cylindrical part of an excellent quality which is free from the interlayer separation, by using a fiber reinforced plastic composite material. The fiber reinforced plastic composite material having a small thermal expansion coefficient is laminated in the circumferential direction of a mandrel; the laminated fiber reinforced plastic composite material layer is heat-cured to form an auxiliary member of the mandrel; a plurality of sorts of fiber reinforced plastic composite materials having a different elastic modulus, respectively are laminated on the formed auxiliary member; and the laminated fiber reinforced plastic composite materials are all heat-cured.

Abstract: A wing of composite material has an upper skin, a lower skin and a plurality of intermediate spars arranged between the upper and the lower skin. The intermediate spars extend from roots to tips of the upper and the lower skins. The intermediate spars are integrally formed with the upper and the lower skins or are adhesively bonded to the upper and the lower skins. The wing has a small number of parts, needs greatly reduced time for fabrication and can be fabricated at a low cost.

Abstract: A wing of composite material has an upper skin, a lower skin and a plurality of intermediate spars arranged between the upper and the lower skin. The intermediate spars extend from roots to tips of the upper and the lower skins. The intermediate spars are integrally formed with the upper and the lower skins or are adhesively bonded to the upper and the lower skins. The wing has a small number of parts, needs greatly reduced time for fabrication and can be fabricated at a low cost.

Abstract: A wing of composite material has an upper skin, a lower skin and a plurality of intermediate spars arranged between the upper and the lower skin. The intermediate spars extend from roots to tips of the upper and the lower skins. The intermediate spars are integrally formed with the upper and the lower skins or are adhesively bonded to the upper and the lower skins. The wing has a small number of parts, needs greatly reduced time for fabrication and can be fabricated at a low cost.

Abstract: The disclosed method can manufacture a thick-walled cylindrical part of an excellent quality which is free from the interlayer separation, by using a fiber reinforced plastic composite material. The fiber reinforced plastic composite material having a small thermal expansion coefficient is laminated in the circumferential direction of a mandrel; the laminated fiber reinforced plastic composite material layer is heat-cured to form an auxiliary member of the mandrel; a plurality of sorts of fiber reinforced plastic composite materials having a different elastic modulus, respectively are laminated on the formed auxiliary member; and the laminated fiber reinforced plastic composite materials are all heat-cured.

Abstract: The disclosed method can manufacture a thick-walled cylindrical part of an excellent quality which is free from the interlayer separation, by using a fiber reinforced plastic composite material.

Abstract: A composite material wing structure is disclosed, comprising a plurality of composite material multi-spar structures, each including a plurality of spar extending in a span direction, placed in the span direction. A wing structure of an airplane is also disclosed, comprising wing structures divided into plural parts in a span direction, a rib connected to an end of the wing structure to assemble adjacent wing structures, and a coupling material for coupling spars of the adjacent wing structures.

Abstract: The disclosed method can manufacture a thick-walled cylindrical part of an excellent quality which is free from the interlayer separation, by using a fiber reinforced plastic composite material. The fiber reinforced plastic composite material having a small thermal expansion coefficient is laminated in the circumferential direction of a mandrel; the laminated fiber reinforced plastic composite material layer is heat-cured to form an auxiliary member of the mandrel; a plurality of sorts of fiber reinforced plastic composite materials having a different elastic modulus, respectively are laminated on the formed auxiliary member; and the laminated fiber reinforced plastic composite materials are all heat-cured.

Abstract: An aircraft fuselage structure is fabricated by the following steps. A plurality of ring-shaped members are first prepared, each member being provided around the outer peripheral surface thereof at positions spaced apart in the circumferential direction thereof with a plurality of recesses. Elongated plate members are provided which have respective convex parts corresponding to the recesses, to form stringers. The ring-shaped members are then arranged at a coaxially spaced-apart paralleled disposition, and thereafter a laminating jig is inserted into the coaxially arranged ring-shaped members with a silicone bag interposed therebetween, the silicone bag having an open opposite end. The ring-shaped members are placed in annular recesses provided in the laminating jig and in correspondingly formed annular recesses provided in the bag.

Abstract: An aircraft fuselage structure is fabricated by the following steps. A plurality of ring-shaped members are first prepared, each member being provided around the outer peripheral surface thereof at positions spaced apart in the circumferential direction thereof with a plurality of recesses. Elongated plate members are provided which have respective convex parts corresponding to the recesses, to form stringers. The ring-shaped members are then arranged at a coaxially spaced-apart paralleled disposition, and thereafter a laminating jig is inserted into the coaxially arranged ring-shaped members with a silicone bag interposed therebetween, the silicone bag having an open opposite end. The ring-shaped members are placed in annular recesses provided in the laminating jig and in correspondingly formed annular recesses provided in the bag.