Abstract: First and second composite members each containing first discontinuous fibers of fiber length La, are placed such that end surfaces thereof face each other at an interval of first length L1. Ends of the first and second composite members are melted over a second length L2 from the end surfaces. A connecting member containing second discontinuous fibers of fiber length Lb, is melted and placed to bridge a space between the ends, to form a stack. The stack is pressed, whereby the melted connecting member and the melted end portions flow into the space between the end surfaces to form a mixture portion. The mixture portion is cooled and solidified to produce a fiber-reinforced resin bonded body. The first length L1 is equal to or more than ½ of the fiber length Lb, and the second length L2 is equal to or more than the fiber length La.

Abstract: Linking parts are formed on one end of a first resin composite member and on one end of a second resin composite member in order to bond the ends together. For example, the linking parts may be wavy parts containing concave portions and convex portions. In this case, the wavy parts initially are heated and softened. Then, in a molding unit, respective pairs of confronting convex portions are overlapped with each other, and respective pairs of confronting concave portions are utilized to form a non-overlapping space. The overlapped convex portions are pressed and crushed, such that a base thermoplastic resin and fibers contained therein flow toward the non-overlapping space. Thereafter, the thermoplastic resin is cooled and hardened, whereby the first resin composite member and the second resin composite member are bonded integrally to obtain a resin composite structure.

Abstract: First and second composite members each containing first discontinuous fibers of fiber length La, are placed such that end surfaces thereof face each other at an interval of first length L1. Ends of the first and second composite members are melted over a second length L2 from the end surfaces. A connecting member containing second discontinuous fibers of fiber length Lb, is melted and placed to bridge a space between the ends, to form a stack. The stack is pressed, whereby the melted connecting member and the melted end portions flow into the space between the end surfaces to form a mixture portion. The mixture portion is cooled and solidified to produce a fiber-reinforced resin bonded body. The first length L1 is equal to or more than ½ of the fiber length Lb, and the second length L2 is equal to or more than the fiber length La.

Abstract: In a computer-aided die design apparatus having a computer, a display adapted to be connected to the computer, and a simulator adapted to be loaded in the computer to analyze and display on the display flow behavior of resin when the resin charged into a die cavity is die-clamped by a press at a compression force, the simulator comprises an analyzer that analyzes the resin flow behavior by increasing the compression force for die-clamping the resin at a predetermined time interval until the increased compression force reaches an upper limit value, and a substitutive value calculator that calculates a substitutive value of the compression force based on a stress-relaxation time of the resin when the compression force has reached the upper limit value.

Abstract: Linking parts are formed on one end of a first resin composite member and on one end of a second resin composite member in order to bond the ends together. For example, the linking parts may be wavy parts containing concave portions and convex portions. In this case, the wavy parts initially are heated and softened. Then, in a molding unit, respective pairs of confronting convex portions are overlapped with each other, and respective pairs of confronting concave portions are utilized to form a non-overlapping space. The overlapped convex portions are pressed and crushed, such that a base thermoplastic resin and fibers contained therein flow toward the non-overlapping space. Thereafter, the thermoplastic resin is cooled and hardened, whereby the first resin composite member and the second resin composite member are bonded integrally to obtain a resin composite structure.

Abstract: In a molding method and an apparatus for the method, a base material is placed on mounting portions of bottom support pins, which protrude from a first inner surface of a lower mold in an open state. Pressing portions of top support pins, which protrude from a second inner surface of an upper mold, are brought into contact with the base material. Consequently, the base material is sandwiched between the mounting portions and the pressing portions. Thereafter, pre-forming preferably is carried out. For example, the bottom support pins and the top support pins are lowered toward the lower mold, such that the base material is brought into contact with the first inner surface. Then, the lower mold and the upper mold are closed, and the base material is molded into a molded article.

Abstract: It is an object to provide a blade member for an airplane which is simple in structure, and moreover is excellent with respects to weight, aerodynamic performance, cost, strength and durability. A vane of a double-slotted flap includes: an outer skin area surrounded by a first outer skin, a second outer skin, a leading edge and a trailing edge each having a predetermined wall thickness. Front and rear reinforcing areas are provided that extend in a span direction within the outer skin area and are connected to the first outer skin and the second outer skin. The outer skin area and the reinforcing areas are integrally formed by wire electrical discharge-machining. The first outer skin and the second outer skin respectively have thickened portions thicker than the other portions, and the trailing edge is formed to have a thickness which is approximately zero. This blade member can be simplified in structure, leading to reductions in the number of parts, number of assembling steps and weight.

Abstract: In a wing of an airplane, a front spar having a C-shape in section includes a web, flanges, and a reinforcing partition wall. An intermediate spar having an I-shape in section includes a web, flanges, and a reinforcing partition wall. Ribs can be positioned in a span direction by coupling front and rear portions of the ribs to the reinforcing partition wall of the front spar and the reinforcing partition wall of the intermediate spar, without the provision of an assembling jig having a positioning function and without the use of a special positioning member. In addition, the ribs can be positioned in a cord direction by bringing rear ends of the ribs into abutment against a front surface of the web of the intermediate spar. Thus, it is possible to assemble the wing of the airplane using an inexpensive assembling jig having no rib-positioning function.

Abstract: It is an object to provide a blade member for an airplane which is simple in structure, and moreover is excellent with respects to weight, aerodynamic performance, cost, strength and durability. A vane of a double-slotted flap includes: an outer skin area surrounded by a first outer skin, a second outer skin, a leading edge and a trailing edge each having a predetermined wall thickness. Front and rear reinforcing areas are provided that extend in a span direction within the outer skin area and are connected to the first outer skin and the second outer skin. The outer skin area and the reinforcing areas are integrally formed by wire electrical discharge-machining. The first outer skin and the second outer skin respectively have thickened portions thicker than the other portions, and the trailing edge is formed to have a thickness which is approximately zero. This blade member can be simplified in structure, leading to reductions in the number of parts, number of assembling steps and weight.

Abstract: In a wing of an airplane, a front spar having a C-shape in section includes a web, flanges, and a reinforcing partition wall. An intermediate spar having an I-shape in section includes a web, flanges, and a reinforcing partition wall. Ribs can be positioned in a span direction by coupling front and rear portions of the ribs to the reinforcing partition wall of the front spar and the reinforcing partition wall of the intermediate spar, without the provision of an assembling jig having a positioning function and without the use of a special positioning member. In addition, the ribs can be positioned in a cord direction by bringing rear ends of the ribs into abutment against a front surface of the web of the intermediate spar. Thus, it is possible to assemble the wing of the airplane using an inexpensive assembling jig having no rib-positioning function.

Abstract: A skin/bulkhead structure comprising a barrel-shaped skin and a pressure bulkhead composed of a stiffening member and a bulkhead skin, wherein an end of the stiffening member is mechanically connected to an opening of the barrel-shaped skin through a first connecting member and marginal portion of the bulkhead skin is adhesive-connected to the opening through a second connecting member, the barrel-shaped skin, the stiffening member, the bulkhead skin, the first connecting member and the second connecting member being each made of a fiber-reinforced composite.

Abstract: A skin/bulkhead structure comprising a barrel-shaped skin and a pressure bulkhead composed of a stiffening member and a bulkhead skin, wherein an end of the stiffening member is mechanically connected to an opening of the barrel-shaped skin through a first connecting member and marginal portion of the bulkhead skin is adhesive-connected to the opening through a second connecting member, the barrel-shaped skin, the stiffening member, the bulkhead skin, the first connecting member and the second connecting member being each made of a fiber-reinforced composite.

Abstract: A leading edge structure for an aircraft has an outer wall, an inner wall disposed within the outer wall and including a partition with, the outer wall, the inner wall and the partition jointly defining a hot-air chamber, and a plurality of flow-rectifying fins or disposed in the hot-air chamber and compartmentalizing the hot-air chamber into a plurality of hot-air passages. The outer wall and the flow-rectifying fins are made of a fiber-reinforced synthetic resin and joined to each other by curing. The inner wall and the partition comprise a single component which is made of a fiber-reinforced synthetic resin, and being bonded to the outer wall. Alternatively, the inner wall and the partition are separate from each other and are joined to each other.