A method may comprise applying a first adhesive to a cavity of a bond panel, the cavity defined by a raised body portion of the bond panel, inserting an acoustic insert assembly in the cavity, the acoustic insert assembly being secured in the cavity by the first adhesive, and securing edges of the acoustic insert assembly to the raised body portion of the bond panel with a second adhesive to create a seamless interface between the edges and the raised body portion.

A construct for a hockey blade that includes a foam core. The foam core includes a first core face, a second core face, and a bottom core edge and a top core edge. Multiple pins are injected into the foam core, and one or more layers of resin preimpregnated tape are wrapped around the foam before forming a hockey blade structure in a heated mold.

Some embodiments are directed to a method for producing a part made of a composite material. The method can include arranging at least two reinforcing plies on a first molding face of a mold; impregnating the reinforcing plies with a hardenable resin. A preform is provided between the reinforcing plies, and the preform includes at least two components and a marker for defining or marking the position of the preform and the components in the part.

A tank manufacturing method includes the steps of (a) forming a reinforcing layer before hardening, (b) embedding at least a part of a label into the reinforcing layer before hardening, and (c) winding glass fiber with thermosetting resin before hardening impregnated so as to cover the label to form a surface layer before hardening. The step (a) includes (a1) forming an inner layer before hardening, and (a2) forming an outer layer before hardening having a cover rate lower than the inner layer before hardening and lower than 100%, the outer layer before hardening being arranged on the inner layer before hardening.

A high pressure container has enhanced pressure resistant strength, and a method for manufacturing such high pressure container. The high pressure container includes a sealable hollow liner and a reinforcement layer including a composite carbon fiber bundle covering an outer surface of the hollow liner, wherein the reinforcement layer is wound around the outer surface of the hollow liner and fixed with a cured product of thermosetting resin, and a stress relaxation portion including the cured product of thermosetting product and a plurality of carbon nanotubes between a carbon fiber contained in one composite carbon fiber bundle and a carbon fiber contained in the other composite carbon fiber bundle.

A method for manufacturing a composite material vane with a cavity, includes making a core with the shape of the cavity of the vane to be manufactured, the core including a reinforcing structure occupying only part of the volume of the core, the remaining volume of the core being occupied by a material of a fleeting nature, forming a composite material skin around the core, and eliminating the fleeting material to obtain a composite material vane with a cavity reinforced by the reinforcing structure.

A method for manufacturing a turbomachine vane made of composite material and having a cavity, the method includes producing a core having the shape of the cavity of the vane to be manufactured, the core including a reinforcing structure occupying only a portion of the volume of the core, the core further including a sealed envelope defining the outer surface of said core; and forming a composite material skin around the core.

A fiber-reinforced resin composite includes a honeycomb core, a fiber-reinforced resin layer, and a protection layer. The honeycomb core includes a plurality of cells that are defined by partition walls and extend in an axial direction. The fiber-reinforced resin layer is disposed around the honeycomb core. The fiber-reinforced resin layer includes continuous fibers wound around the honeycomb core. The protection layer is interposed between the honeycomb core and the fiber-reinforced resin layer. The protection layer is configured to prevent rupture of the continuous fibers.

A method for manufacturing a shell includes providing a mold of the shell. The method also includes forming one or more first skins on the mold. Further, the method includes securing at least one three-dimensional (3-D) grid structure onto an inner surface of the one or more first skins. Thus, the method also includes securing one or more reinforcing members to one or more locations of the grid structure so as to locally increase a stiffness of the shell at the one or more locations by creating one or more localized sandwich structures with the grid structure.

A composite structure that includes a plurality of components coupled together forming a joint, wherein the plurality of components are oriented such that a gap is defined at least partially therebetween. The composite structure also includes a filler structure positioned in the gap. The filler structure includes a honeycomb core including side walls that define a plurality of core cells, and an amount of resin within each of the plurality of core cells. The honeycomb core side walls facilitate restricting crack propagation in the resin from spreading between adjacent pairs of the plurality of core cells.