Honda Giken Kogyo Kabushiki Kaisha

Honda Motor Co., Ltd.

Daiya Yamashita

Hiroshi Kato

Keiichi Sato

Toshiaki Fujii

Keizo Matsumoto

Koji Shiraishi

Nobuo Matsui

Fumihiko Shikano

Jun Nakazawa

Haruo Nakayama

Shun Kawabe

Satoshi Miyazu

Akira Kaneko

Takumi Shibata

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 LEnds of the first and second composite members are melted over a second length Lfrom 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 Lis equal to or more than &#xbd; of the fiber length Lb, and the second length Lis equal to or more than the fiber length La.

Method for producing fiber-reinforced resin bonded body

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.

Resin composite structure and method for producing the same

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. Moreover, no step nor seam is generated on a surface of the blade member, and hence it is possible to prevent an increase in drag and the generation of corrosion.

Blade member for airplane

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.

Wing structure of airplane

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.

Skin/bulkhead structure

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.

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Wako, Japan

Daiya Yamashita