A bonded structure includes a first fiber part (12) and a second fiber part (14) arranged between a first member (10) and a second member (20). The first fiber part (12) and the second fiber part (14) are bonded so as to connect the first member (10) and the second member (20) to each other. The first fiber part (12) and the second fiber part (14) are arranged so that the fibers constituting the first fiber part (12) and the second fiber part (14) are oriented in a direction from the first member (10) toward the second member (20).

A method and system for forming a composite laminate. A layup plan is generated for laying up a plurality of plies having a plurality of merge zones, each ply of the plurality of plies having a corresponding merge zone at which ends of a first plurality of tows for each ply and ends of a second plurality of tows for each ply meet. The locations of the plurality of merge zones are offset relative to each other through a thickness of the composite laminate. The plurality of plies is then laid up according to the layup plan to form a composite laminate.

A method of producing a single assembled longitudinally extending fibre layer for use in a later resin infusion process for manufacturing a fibre-reinforced composite structure is described including steps: a) providing a first fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the first fibre mat, b) providing a second fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the second fibre mat, c) arranging the first fibre mat and the second fibre mat so that unidirectional fibres of one end of the first fibre mat adjoin one end of the second fibre mat in a single plane at a common boundary, and d) splicing unidirectional fibres of the first fibre mat at one end of the first fibre mat to unidirectional fibres of the second fibre mat at one end of the second fibre mat in order to form a splicing joint.

Layers of plies of composite material are laid on a convex tool surface. A first layer is placed with a first ply of a first section having a gap edge adjacent a gap edge of a first ply of a second section, the edges being parallel and a contraction distance from each other. A second layer is placed with a second ply of the first section having a gap edge adjacent a gap edge of a second ply of the second section, the edges being parallel and a contraction distance from each other, the second ply of the second section overlapping onto the first ply of the first section by a splice distance. Consolidation and curing cause contraction of the layers toward the tool, allowing the adjacent gap edges of each layer to be in close proximity or in contact after moving toward each other during the contraction.

The invention relates to a casing for an aircraft engine, in particular a bypass pipe or fan casing, consisting of a plurality of hardened prepreg plies in which the fibers are oriented differently, and to a method for producing a casing of said type. In order to improve the resistance properties of the casing, especially in fire resistance tests, and reduce the amount of wasted prepreg material, at least one reinforcement ply is provided that consists of a prepreg strip having several windings, and the prepreg strip of each reinforcement ply includes a lateral overlapping portion.

A wind turbine blade 2 for a rotor has a longitudinal direction extending from a root region 26 to a blade region. The wind turbine blade 2 is formed of a fibre-reinforced polymer material comprising a polymer matrix and a first and a second reinforcement fibre material being embedded in the polymer matrix. The wind turbine blade further comprises a first region being reinforced predominantly with the first reinforcement fibre material, a second region being reinforced predominantly with the second reinforcement fibre material, and a transition region between the first and the second region. The first region extends in the root region 26 and the first reinforcement fibre material is a metal.

Methods and devices of fabricating a stringer for a vehicle. The stringer can be constructed from two charges that are formed together into the stringer. During fabrication, the charges are placed over support members with the ends of each charge extending over a die cavity. The charges are secured and a punch die forces the first ends into the die cavity forming blades of the stringer. The charges are secured thus tensioning the charges during the punch process.

A composite blade is formed by laying up composite material layers in which reinforcement fibers are impregnated with resin in a thickness direction of the blade. The composite blade includes a blade root on a base end side, an airfoil on a tip side, a first lay-up in which some composite material layers are laid up in the blade root so as to space parts of the composite material layers to form spacing parts and to extend from the distal toward the base end side in the thickness direction, and second lay-ups in which some composite material layers are laid up in the spacing parts so as to be lined up in the thickness direction. Among the second lay-ups, a second lay-up closer to a center side than to an outer side in the thickness direction is a larger distance from a proximal position to a top position.

A method for fabricating a composite structure. A first section for the composite structure is formed in which the first section has a first end with a chevron shape, wherein first composite layers in the first section has a first step pattern at the first end. A second section for the composite structure is formed in which the second section has a second end with a counterpart shape to the chevron shape and in which second composite layers in the second section have a second step pattern at the second end. The first end the second end are positioned such that a first composite layer in the first composite layers in the first step pattern overlap the second composite layers in the second step pattern at a splice location.

A prepreg, including: a fiber layer containing unidirectionally arranged discontinuous carbon fibers and a thermosetting resin; and a resin layer existing on at least one side of said fiber layer and containing a thermosetting resin and a thermoplastic resin; in which said prepreg contains carbon fibers having an areal weight of fibers of 120 to 300 g/m.sup.2, and has a mass fraction of resin of 25 to 50% with respect to the whole mass of said prepreg; and in which a temperature at which a coefficient of interlayer friction is 0.05 or less is in a temperature range of from 40 to 80 C., the interlayer friction being caused at the contact interface between layers of said prepreg when the middle one of three layers that are each made of said prepreg and laid up is pulled out, said coefficient of interlayer friction being measured at 10 C. intervals in a temperature range of from 40 to 80 C. under conditions including a pulling speed of 0.2 mm/min, a perpendicular stress of 0.08 MPa, and a pulling length of 1 mm. There is provided a prepreg with which a wrinkle-free preform can be produced and which expresses excellent, mechanical property in carbon fiber reinforced plastics made thereof.