The invention concerns a method for producing a hybrid-structure part of a motor vehicle, comprising shaping of a sheet of metallic material, the provision of a sheet of composite material, application of a layer of connecting material on a face of said metallic material sheet or on a face of said composite material sheet, the shaping of a hybrid element by shaping said composite material sheet to the shape of said metallic material sheet and joining the composite material sheet to the metallic material sheet by means of said connecting material layer, and the production of ngidification elements by overmoulding using a polymer material.

A method of defining a rib structure within an iso-grid composite component according to an exemplary aspect of the present disclosure includes, among other things, defining a first rib at least partially with a uni-tape ply bundle at a first level, the uni-tape ply bundle including uni-tape plies and a first spacer ply, and defining a second rib transverse to the first rib at least partially with a spacer at the first level, the spacer including a second, different spacer ply, the spacer transverse to the uni-tape ply bundle such that the spacer is interrupted by the uni-tape ply bundle.

A composite stiffener for a stiffener reinforced panel is disclosed. The stiffener has a longitudinal direction and a run-out region which terminates at an end of the stiffener. The stiffener also has a constant section region inboard of the run-out region in the longitudinal direction and having a constant cross section transverse to the longitudinal direction with a crown between adjacent foot portions. The run-out region has a changing cross section transverse to the longitudinal direction with a crown between adjacent foot portions and the crown reduces in height towards the end of the stiffener forming a ramp. The composite stiffener includes a number of blankets of non-crimp fabric layers.

A FRP tubular body includes a tubular fiber structure formed by winding a reinforced fiber sheet made of fabric. The reinforced fiber sheet includes first reinforced fiber bundles arranged such that a yarn main axis direction extends in a circumferential direction of the fiber structure and second reinforced fiber bundles arranged such that a yarn main axis direction extends in an axial direction of the fiber structure. The reinforced fiber sheet includes a starting end, a finishing end, and a general portion located between the starting end and the finishing end. The general portion includes the first reinforced fiber bundles and the second reinforced fiber bundles. At least one of the starting end or the finishing end is a decreased portion that is smaller than the general portion in an amount of reinforced fibers per unit length in the circumferential direction of the fiber structure.

A composite stiffener for a stiffener reinforced panel is disclosed. The stiffener has a longitudinal direction and a run-out region which terminates at an end of the stiffener. The stiffener also has a constant section region inboard of the run-out region in the longitudinal direction and having a constant cross section transverse to the longitudinal direction with a crown between adjacent foot portions. The run-out region has a changing cross section transverse to the longitudinal direction with a crown between adjacent foot portions and the crown reduces in height towards the end of the stiffener forming a ramp. The composite stiffener comprises a number of blankets of non-crimp fabric layers.

A method produces a fiber composite component for a motor vehicle. The method provides a semifinished fiber composite blank, wherein the semifinished fiber composite blank includes reinforcing fibers and a matrix material. The semifinished fiber composite blank is arranged between a first membrane and a second membrane. The semifinished fiber composite blank is shaped into a fiber composite molding by pressing the semifinished fiber composite blank together with the first membrane and the second membrane via a pressing device, and the fiber composite molding is consolidated.

A method for manufacturing a blade made of composite material for a turbine engine, in particular of an aircraft, the steps of injecting a resin in order to impregnate a fibrous preform woven in three dimensions and polymerizing the resin so as to form the blade that includes an airfoil, one longitudinal end of which is connected to a platform. The platform includes pressure and suction portions connected to the airfoil by a fillet, wherein a separation is formed in the fibrous preform between the pressure and suction portions. The method further includes reinforcing a leading edge of the airfoil; and reinforcing the fillets by integration of a metal reinforcement on at least one part of the pressure and suction portions of the platform and in the separation.

A racquet including a frame including a head portion, a handle portion, and a throat portion. The head portion is a tubular structure including inner and outer peripheral walls, each having inner and outer surfaces. The head portion of the racquet being formed of a fiber composite material. The fiber composite material includes a plurality of ply arrangements. Each includes a pair of plies defining first and second angles with respect to a composite axis. A section of the outer peripheral wall from the inner surface to the outer surface includes at least three ply arrangements overlaying each other, and the first and second angles of at least two of the at least three ply arrangements being at least 35 degrees. When the racquet is tested under a racquet torsional stability test, the racquet has an angular deflection of less than 5.5 degrees about a longitudinal axis.

A racquet including a frame including a head portion, a handle portion, and a throat portion. The head portion forms a hoop that defines a string bed plane. The head portion of the racquet being formed of a fiber composite material. When the racquet is tested under a racquet forward/rearward bending test, the racquet has a forward/rearward deflection with respect to the longitudinal axis of at least 8.5 mm when measured in a direction that is perpendicular to the string bed plane and perpendicular to the longitudinal axis. When the racquet is tested under a racquet torsional stability test, the racquet has an angular deflection of less than 5.5 degrees about a longitudinal axis.

A racquet extending along a longitudinal axis and including a frame including a head portion, a handle portion, and a throat portion. The head portion forms a hoop that defines a string bed plane. At least the head portion and the throat portion of the frame are formed at least in part of a fiber composite material. When the racquet is tested under the racquet lateral bending test, the racquet has a lateral deflection of at least 6.0 mm when measured in a direction that is parallel to the string bed plane and perpendicular to the longitudinal axis.