An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.

In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.

A composite hat stringer for stiffening a panel includes a plurality of composite fabric plies arranged to form a cap, a pair of flanges and a pair of webs respectively connecting the cap with the pair of flanges. The cap includes at least one 0° composite tape ply interleafed in the composite fabric plies within the cap.

A guidance and maintenance machine (100) includes a guide roller (102) and an application roller (104), each having a plurality of respective grooves (102a, 104a) defined on a respective circumferential surface (102b, 104b). The guidance and maintenance machine includes at least one preparation comb (200) having a support (202) with an upper surface (202d) from which a plurality of teeth (204) extend. The teeth, with a predetermined uniform height, are aligned in parallel along a length of the support and are positioned at a pitch between them in correspondence with corresponding grooves (102a) of the guide roller (102) so that the comb (200) feeds filaments (50) from a supply creel (304), where the filaments are stored, to the guide roller (102) at a predetermined pitch positioning outside the guide roller.

A guidance and maintenance machine (100) includes a guide roller (102) and an application roller (104), each having a plurality of respective grooves (102a, 104a) defined on a respective circumferential surface (102b, 104b). The guidance and maintenance machine includes at least one preparation comb (200) having a support (202) with an upper surface (202d) from which a plurality of teeth (204) extend. The teeth, with a predetermined uniform height, are aligned in parallel along a length of the support and are positioned at a pitch between them in correspondence with corresponding grooves (102a) of the guide roller (102) so that the comb (200) feeds filaments (50) from a supply creel (304), where the filaments are stored, to the guide roller (102) at a predetermined pitch positioning outside the guide roller.

To provide a method for manufacturing a novel molded article using a commingled yarn and a composite material using a commingled yarn. The method for manufacturing a molded article, includes disposing a commingled yarn containing a continuous reinforcing fiber and a continuous thermoplastic resin fiber on a part of a surface of a prepreg, the prepreg containing continuous reinforcing fibers paralleling at least unidirectionally, and a thermosetting resin impregnated between the continuous reinforcing fibers, and heat-processing the prepreg with the commingled yarn.

An object of the present invention is to provide a golf club shaft having excellent strength. The present invention provides a golf club shaft made of a fiber-reinforced epoxy resin material comprising a cured product of an epoxy resin composition and a reinforcing fiber, wherein the epoxy resin composition comprises at least one selected from the group consisting of a bisphenol A type epoxy resin, a bisphenol F type epoxy resin and a novolac type epoxy resin, and a tetraglycidyl type epoxy resin as an epoxy resin component, and the cured product of the epoxy resin composition has a swelling ratio in a range from 20 mass % to 44 mass % in methyl ethyl ketone.

A fiber-reinforced member includes: a base member having a tubular region with an outer circumferential surface extending along and substantially in parallel with an axial direction; and a fiber-reinforced resin layer constituted of a tow prepreg wound in an overlapping manner to cover the outer circumferential surface of the base member along a predetermined direction crossing the axial direction when viewed in a radial direction of the base member, the tow prepreg serving as a widened tape-like member. The tape-like member constituting the fiber-reinforced resin layer has a portion having a fiber line extending along a direction crossing the predetermined direction. A size of a width of the tape-like member constituting the fiber-reinforced resin layer is not less than 100 times and not more than 400 times as large as a size of a thickness of the tape-like member constituting the fiber-reinforced resin layer in the radial direction.

Methods for fabricating fiber-composite truss structures comprise a) individually molding multiple unit cells of a given size, and subsequently fusing them together in a repeating pattern, b) cross members are consolidated with longerons while maintaining continuity of fiber in the longerons, and c) compression-molded truss components are unioned to continuous fiber beams by means of mechanically interlocking joints.

The present invention concerns a multilayer element comprising a reinforcing material suitable for producing composite parts combined on at least one of the faces of same with a support layer characterized in that the reinforcing material and the support layer are combined by means of electrostatic forces, and a method for preparing such a material and a method for producing a composite part produced from at least one reinforcing material obtained from such an element, after having removed the support layer.