A method is described for manufacturing a molded product having a recessed/protruding part from a molded substrate (A) including reinforcing fibers and a matrix resin by press molding, the method comprising: a step (I) of placing the molded substrate (A) between molds including an upper mold and a lower mold and deforming the molded substrate (A) in an in-plane direction by heating and pressing the molds; and a step (II) of deforming the molded substrate (A) in an out-of-plane direction by depressurizing the molds subsequent to the step (I), wherein a deformation rate ratio T represented by the following formula (1) is within a range of 0.1 to 1:
T=X/Z   (1)
where X and Z are as defined.

A method is described for manufacturing a molded product having a recessed/protruding part from a molded substrate (A) including reinforcing fibers and a matrix resin by press molding, the method comprising: a step (I) of placing the molded substrate (A) between molds including an upper mold and a lower mold and deforming the molded substrate (A) in an in-plane direction by heating and pressing the molds; and a step (II) of deforming the molded substrate (A) in an out-of-plane direction by depressurizing the molds subsequent to the step (I), wherein a deformation rate ratio T represented by the following formula (1) is within a range of 0.1 to 1:
T=X/Z   (1)
where X and Z are as defined.

A composite part is provided and includes a component, a first set of first composite plies with finite lengths and a second set of second composite plies with finite lengths. A respective end of each of the first composite plies is wrapped around the component in a clockwise wrapping direction and includes first fibers. A respective end of each of the second composite plies is wrapped around the component in a counter-clockwise wrapping direction and includes second fibers.

A composite airfoil is disclosed. In various embodiments, a composite airfoil as disclosed herein includes an outer skin comprising one or more layers of carbon fiber composite material, the outer skin defining an aerodynamic surface having a leading edge; and a reinforcement material comprising a roll of fiberglass reinforced fabric positioned behind the outer skin along at least a portion of the leading edge.

A stitched multi-axial reinforcement and a method of producing a stitched multi-axial reinforcement. The stitched multi-axial reinforcement may be used in all such applications that reinforcements are generally needed and especially in such applications where either Vacuum Infusion technology or Resin Transfer Molding (RTM) technology for distributing the resin in the mold is used. The stitched multi-axial reinforcement is especially applicable in the manufacture of wind turbine blades, boats, sporting equipment, storage tanks, bus, trailer, train and truck panels, etc., and generally in all such structures that are subjected to stress in more than one direction

A non-woven carbon fiber reinforced thermoplastic (CFRTP) composite object is formed by the variable frequency microwave (VFM) irradiation of a mixed fiber sheet of thermoplastic fibers, carbon fibers and wavy carbon nanotubes (CNTs). The mixed fiber sheets are prepared from a slurry of the thermoplastic fibers, carbon fibers, and wavy CNTs such that the wavy CNTs contact the carbon fibers and thermoplastic fibers. Upon irradiation with VFM radiation, the wavy CNTs generate heat and transfer the heat to the thermoplastic fibers, causing melting of the thermoplastic to form the matrix of the CFRTP composite object. The mixed fiber sheets can be combined alone or with other sheets to form laminar composites that are molded into objects and heated by VFM irradiation.

Forming features in the surface of a bicycle component involves depositing a substance onto a substrate in a geometric pattern to form a transfer medium. Forming features may also involve positioning the transfer medium relative to an unformed bicycle component, and forming a negative of the geometric pattern in the bicycle component through the application of heat and/or pressure to the transfer medium and the unformed bicycle component. The transfer medium may be configured for use in the molding of carbon fiber reinforced plastic (“CFRP”) bicycle components and may include a substrate formed of a flexible material, and a geometric pattern formed of a hard material, the hard material different than the flexible material.

Forming features in the surface of a bicycle component involves depositing a substance onto a substrate in a geometric pattern to form a transfer medium. Forming features may also involve positioning the transfer medium relative to an unformed bicycle component, and forming a negative of the geometric pattern in the bicycle component through the application of heat and/or pressure to the transfer medium and the unformed bicycle component. The transfer medium may be configured for use in the molding of carbon fiber reinforced plastic (“CFRP”) bicycle components and may include a substrate formed of a flexible material, and a geometric pattern formed of a hard material, the hard material different than the flexible material.

A door for a thrust reversal system, an aircraft with such a door, and a method for manufacturing a door of a thrust reversal system. The door comprises a wall formed from long fibers embedded in a thermoplastic resin matrix and a network of ribs overmolded on one of the faces of the wall. A propulsion assembly of an aircraft comprises a thrust reversal system having a plurality of such doors.

A flexible, self-supporting hybrid veil that is permeable to liquid and gas. The hybrid veil includes: (a) intermingled, randomly arranged fibres in the form of a nonwoven structure; (b) particles dispersed throughout the nonwoven structure, wherein a majority of the particles are penetrating through the thickness of the nonwoven structure; and (c) a polymeric or resinous binder present throughout the veil. Such hybrid veil can be incorporated into composite laminates, prepregs, fabrics and fibrous preforms.