Provided are a method and an apparatus for manufacturing a fiber-reinforced resin molding material by which, when the fiber-reinforced resin molding material is manufactured, separated fiber bundles can be supplied to a cutting machine in stable condition while avoiding the influence of meandering of the fiber bundles or slanting or meandering of filaments occurring in the fiber bundles. A method for manufacturing a sheet-shaped fiber-reinforced resin molding material in which spaces between filaments of cut-out fiber bundles (CF) are impregnated with resin includes, so that a condition of the following expression (1) is satisfied, intermittently separating fibers of the continuous fiber bundles (CF) in a longitudinal direction by a rotational blade (18) serving as a fiber separating part and cutting out the fiber bundles with an interval therebetween in a longitudinal direction of a cutting machine (13A) to obtain the cut-out fiber bundles (CF). Expression (1): 1≤a/L (where a represents a length of a separated part of the continuous fiber bundles (CF) and L represents an interval when the fiber bundles (CF) are cut out in the longitudinal direction.)

Disclosed herein are methods for isolating a composite material from the environment, as well as the isolated composite material. Also disclosed herein are methods for shaping a composite material that include the use of isolated composite materials. For example, disclosed is a method for mechanical thermoforming of a composite material to form a shaped composite material.

According to one implementation, a composite material structure includes a corrugated stringer and a panel. The corrugated stringer has a corrugated structure including portions each having hat-shaped cross section. The corrugated stringer is made of a composite material. The panel is integrated with the corrugated stringer. The panel is made of a composite material. Further, according to one implementation, a manufacturing method of a composite material structure includes: setting a textile on a laminated body of prepregs; and producing the composite material structure by covering the laminated body with a bagging film, forming a vacuum state in a space covered with the bagging film, impregnating the textile with the resin, and thermal curing of the laminated body of the prepregs. The laminated body is a panel before curing. The textile has a structure corresponding to a corrugated stringer.

A polymer composite composition for use in high temperature applications such as furnaces, heat shields and aeronautical jet and rocket motors. In a particular application, the disclosed composition is applied to the manufacture of rocket motor cases, or parts thereof, to provide rigid thermal protection (RTP). The polymer composite composition comprises cyanate ester resin, fine lengths of carbon fibre and refractory filler material.

A joining method for connecting at least two thermoplastic workpieces is provided to permit the joining even of non-transparent carbon fiber reinforced plastics parts by means of laser welding, in which a splice is produced at the edge regions of the workpieces and the workpieces are subsequently positioned relative to one another in such a manner that the opposite splice regions bound a seam region. Connecting bodies are then inserted into the seam region and heated by means of local heat input by laser beam such that a fixed integrally bonded connection forms between the workpieces and the connecting bodies.

A joining method for connecting at least two thermoplastic workpieces is provided to permit the joining even of non-transparent carbon fiber reinforced plastics parts by means of laser welding, in which a splice is produced at the edge regions of the workpieces and the workpieces are subsequently positioned relative to one another in such a manner that the opposite splice regions bound a seam region. Connecting bodies are then inserted into the seam region and heated by means of local heat input by laser beam such that a fixed integrally bonded connection forms between the workpieces and the connecting bodies.

A method for forming fiber composite preforms, the preform (1) include a web (2), a flange (3) and a bent part (2.1), and the method includes: laying-up a laminate (4) onto a tooling (5), the laminate (4) comprising lateral and transverse edges (4.1, 4.2) and the tooling (5) comprising a male part (7) comprising a surface (7.1) and a lateral wall (7.2), the web (2) being configured to be located over the surface (7.1) of the male part (7) and the flange (3) being configured to be located over the lateral wall (7.2) of the male part (7); forming the preform (1) over the male part (7); clamping the lateral edges (4.2) of the laminate (4) to the tooling (5) such that the web (2) and the flange (3) of the laid-up laminate (4) are kept under tensional loads, and bending a longitudinal portion of the male part (7).

A composite laminate stiffener is formed to contour with reduced ply wrinkling using constrained creep forming. The tooling apparatus is provided with flexible cauls which constrain the stiffener during the contour forming process. The creep forming is carried out at a slow enough rate so that friction or shear resistance between the resin and fibers of the plies remains low enough that slippage can occur and significant compression stresses are not generated rate, allowing relaxation of residual stresses in the stiffener.

A carbon fiber tape material is favorable in followability to molds and impregnation with matrix resins, and capable of enhancing the productivity in producing a reinforcing fiber laminate by a method of fiber placement and capable of providing a molded body with high mechanical strength when the material is impregnated with a resin and molded. The carbon fiber tape material has a carbon fiber bundle group including a plurality of carbon fiber bundles arranged in parallel with the fiber orientation direction and a fabric are integrated, and satisfies (a) to (c): (a) the fabric includes one or more thermoplastic resins; (b) the carbon fiber tape material excluding the fabric is between 120 g/m.sup.2 and 400 g/m.sup.2 in basis weight; and (c) the fabric elongation rate with a load of 80 mN/50 mm applied to the fabric is 5% to 100% in at least one direction of the fabric.

Provided is a tube body intermediate including: a carbon fiber disposed with respect to an outer circumferential surface of a mandrel so as to extend in an axial direction of the mandrel; and a fixing member having a tubular shape and disposed with respect to the outer circumferential surface of the mandrel so as to cover the carbon fiber. Also provided is a tube body production method including: disposing a fiber body with respect to an outer circumferential surface of a mandrel so that the fiber body extends in an axial direction of the mandrel; disposing a fixing member with a tubular shape with respect to the outer circumferential surface of the mandrel so that the fixing member covers the fiber body; and impregnating the fiber body with a resin on the outer circumferential surface of the mandrel and then heating the resin to mold the resin.