Abstract: A bonding system includes a supporting jig having a mounting surface on bonding substrates which are mounted, a bonding device that sandwiches and welds the bonding substrates between itself and the mounting surface, an articulated robot to which the bonding device is attached, and a control unit that controls the articulated robot and the bonding device.

Abstract: A protrusion on a first member made of synthetic resin wherein a laser beam is applied to a side surface of the protrusion in a state in which a top surface of the protrusion of the first member is abutted against a second member made of synthetic resin, so as to melt at least the entire top surface of the protrusion and melt a portion of the second member in contact with the protrusion by heat of the melted top surface of the protrusion, followed by solidification of the melted portions, whereby the first member and the second member are welded together.

Abstract: A method of producing thermoplastic resin composite material in which a main base material containing thermoplastic resin and a sheet-like shaped auxiliary base material are integrally molded and are made into composite material. The production method includes the steps of: heating the auxiliary base material (step S1); disposing the heated auxiliary base material in a mold (step S2); disposing the main base material in the mold via the auxiliary base material (step S3); closing the mold, and pressing together and integrally molding the auxiliary base material and the main base material (step S4); and taking out the integrally-molded thermoplastic resin composite material from the mold.

Abstract: A molding method and a molding system for improving a molding speed of a resin molded member. In the method, firstly a thermoplastic resin composite material is filled in a metal mold (i.e., at time T0), and subsequently a mold-clamping process gets started. As the mold-clamping process progresses, a first decompression circuit starts to decompress an inside of a cavity when the cavity is closed by a sealing member provided on the metal mold. Then, as the mold-clamping process further progresses, the thermoplastic resin composite material thus filled in the metal mold contacts an upper mold of the metal mold (i.e., at time T2). After that, a second decompression circuit starts to decompress the inside of the cavity, thereby to complete the mold-clamping process (i.e., at time T3).

Abstract: A protrusion on a first member made of synthetic resin wherein a laser beam is applied to a side surface of the protrusion in a state in which a top surface of the protrusion of the first member is abutted against a second member made of synthetic resin, so as to melt at least the entire top surface of the protrusion and melt a portion of the second member in contact with the protrusion by heat of the melted top surface of the protrusion, followed by solidification of the melted portions, whereby the first member and the second member are welded together.

Abstract: A bonding system includes a supporting jig having a mounting surface on bonding substrates which are mounted, a bonding device that sandwiches and welds the bonding substrates between itself and the mounting surface, an articulated robot to which the bonding device is attached, and a control unit that controls the articulated robot and the bonding device.

Abstract: To provide a vehicle floor panel having a certain rigidity and being less prone to deformation during manufacturing and deformation when the vehicle floor panel installed in a vehicle is subjected to loads in various directions from outside the vehicle. A vehicle floor panel includes a floor panel main body made of a fiber-reinforced resin, a plurality of recesses 23-1 to 23-7 protruding on one of a lower surface 22 and upper surface of the floor panel main body and depressed on the other of the surfaces and arranged by being spaced apart from one another, and ribs 24-1 to 24-12 connecting two adjacent ones of the recesses on the one of the surfaces of the floor panel main body.

Abstract: A molding method and a molding system for improving a molding speed of a resin molded member. In the method, firstly a thermoplastic resin composite material is filled in a metal mold (i.e., at time T0), and subsequently a mold-clamping process gets started. As the mold-clamping process progresses, a first decompression circuit starts to decompress an inside of a cavity when the cavity is closed by a sealing member provided on the metal mold. Then, as the mold-clamping process further progresses, the thermoplastic resin composite material thus filled in the metal mold contacts an upper mold of the metal mold (i.e., at time T2). After that, a second decompression circuit starts to decompress the inside of the cavity, thereby to complete the mold-clamping process (i.e., at time T3).

Abstract: A method of producing thermoplastic resin composite material in which a main base material containing thermoplastic resin and a sheet-like shaped auxiliary base material are integrally molded and are made into composite material. The production method includes the steps of: heating the auxiliary base material (step S1); disposing the heated auxiliary base material in a mold (step S2); disposing the main base material in the mold via the auxiliary base material (step S3); closing the mold, and pressing together and integrally molding the auxiliary base material and the main base material (step S4); and taking out the integrally-molded thermoplastic resin composite material from the mold.

Abstract: To provide a vehicle floor panel having a certain rigidity and being less prone to deformation during manufacturing and deformation when the vehicle floor panel installed in a vehicle is subjected to loads in various directions from outside the vehicle. A vehicle floor panel includes a floor panel main body made of a fiber-reinforced resin, a plurality of recesses 23-1 to 23-7 protruding on one of a lower surface 22 and upper surface of the floor panel main body and depressed on the other of the surfaces and arranged by being spaced apart from one another, and ribs 24-1 to 24-12 connecting two adjacent ones of the recesses on the one of the surfaces of the floor panel main body.

Abstract: A method of fabricating a panel of composite material. The panel includes two outside skins and stringers attached inside of the two outside skins for reinforcing the two outside skins. A plurality of stringers for reinforcing outside skins is formed from dry preformed fibers and are disposed at a predetermined interval.

Abstract: A box-structure airfoil is constructed of a composite material uppers skin, a composite material lower a skin 12 and a spar. Ribs and an elongate projection are formed integrally on the inner surface of each of the two skins. The upper and lower skins and the spar are simultaneously bonded by an adhesive to form a single structure. Since the ribs and the elongate projection are one-piece formed with each skin, it is possible to reduce the number of principal constituent components. Furthermore, since assembly operation is made by using the adhesive, there is no need for fasteners or the like for assembling. Moreover, the flanges on both sides of the spar can also be bonded to the respective skins. According to the invention, it is possible to reduce the number of principal constituent components and that of assembling components of an airfoil, thereby achieving its cost reduction.

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: This invention is a method of fabricating a panel of composite material. The panel includes two outside skins and stringers attached inside of the two outside skins for reinforcing the two outside skins. A plurality of stringers for reinforcing outside skins is formed from dry preformed fibers. The plurality of stringers are disposed at a predetermined interval. Adjacent two stringers is connected with each other via a connecting member made from dry preformed fibers. The connected stringers and the connecting members are set into a forming mold. Resin is introduced into the forming mold to impregnate the dry preformed fibers of the stringers and the connecting members. The resin-impregnated stringers and the resin-impregnated connecting members are cured to unite the resin-impregnated stringers and the resin-impregnated connecting member into one body of “Rudder Shape” stringer. A prepreg is laminated onto an outside-skin shaping mold.

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 panel of composite material including two outside skin parts, a plurality of stringers, connecting members for connecting the plurality of stringers, and a reinforcing member connecting the two outside skin parts with each other. Each of the two outside skin parts is formed into one body. A portion protruding upward from the plurality of stringers is provided on the connecting members, and is connected to the reinforcing member by a fastener.

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: This invention is a method of fabricating a panel of composite material. The panel includes two outside skins and stringers attached inside of the two outside skins for reinforcing the two outside skins. A plurality of stringers for reinforcing outside skins is formed from dry preformed fibers. The plurality of stringers are disposed at a predetermined interval. Adjacent two stringers is connected with each other via a connecting member made from dry preformed fibers The connected stringers and the connecting members are set into a forming mold. Resin is introduced into the forming mold to impregnate the dry preformed fibers of the stringers and the connecting members. The resin-impregnated stringers and the resin-impregnated connecting members are cured to unite the resin-impregnated stringers and the resin-impregnated connecting member into one body of “Rudder Shape” stringer. A prepreg is laminated onto an outside-skin shaping mold.

Abstract: A box-structure airfoil is constructed of a composite material upper skin, a composite material lower skin 12 and a spar. Ribs and an elongate projection are formed integrally on the inner surface of each of the two skins. The upper and lower skins and the spar are simultaneously bonded by an adhesive to form a single structure. Since the ribs and the elongate projection are one-piece formed with each skin, it is possible to reduce the number of principal constituent components. Furthermore, since assembly operation is made by using the adhesive, there is no need for fasteners or the like for assembling. Moreover, the spar is bonded not only to Moreover, because not only a web but also flanges on both sides of the spar are bonded to the respective skins, it is possible to obtain a large strength. According to the invention, it is possible to reduce the number of principal constituent components and that of assembling components of an airfoil, thereby achieving its cost reduction.

Abstract: A leading edge structure of an aircraft airfoil comprises an outer skin, a front wall extended in the spanwise direction of the leading edge structure in a front section of the space defined by the outer skin so as to form an anti-icing duct together with a front part of the outer skin, and a plurality of ribs disposed in the space defined by the outer skin so as to form hot air passages. A laminar structure is formed by superposing upper and lower sheets of a superplastic titanium alloy, inserting a pair of core sheets of a superplastic titanium alloy between the upper and the lower sheet, and forming release agent layers in predetermined regions between the sheets.