Embodiments disclosed herein relate to polymer resins having a first thermoset and one or more additional components (e.g., a second thermoset and/or a thermoplastic), composite laminates including the same, methods of making and using the same, and composite laminate structures including the same.

A laminated composite airfoil assembly includes a first lamina formed of a material including metal fibers, and at least a second lamina formed of a material including at least one of metal fibers intermixed with carbon fibers, only metal fibers, only carbon fibers, a substrate including metal fibers, a substrate including carbon fibers, and combinations thereof.

A laminated composite airfoil assembly includes a first lamina formed of a material including metal fibers, and at least a second lamina formed of a material including at least one of metal fibers intermixed with carbon fibers, only metal fibers, only carbon fibers, a substrate including metal fibers, a substrate including carbon fibers, and combinations thereof.

Systems and methods are provided for enhancement of vacuum bagging processes for a composite part. One system includes dispensers configured to dispense materials onto a forming tool for a composite part, and a controller. The controller is able to identify a selected location for placing the composite part on the tool, to direct the dispensers to apply a mold release agent onto the tool based on the selected location, to apply a sealant onto the tool proximate to the selected location, to lay up a ply of constituent material for the composite part atop the mold release agent at the selected location, to apply a pressure pad material atop the constituent material, to apply a breather material atop the pressure pad, and to apply vacuum bag material atop the ply proximate to the selected location to cover the ply as well as the sealant.

The present invention provides: a surface-coated film which is for being integrally formed with a fiber impregnation resin; a surface-coated fiber-reinforced resin molded product; and a manufacturing method thereof. The surface-coated film has a base film B and an easily adhesive layer A provided on the base film B, wherein the base film B has a flat layer b2 and an easily molded layer b1 adjacent to the easily adhesive layer A, the thickness of the easily adhesive layer A is 30-250 nm, the thickness of the base film B is 50-500 μm, the easily molded layer b1 and the flat layer b2 satisfy both expression 1 of 3≤ratio (EHb2/EHb1) of storage elastic modulus EHb2 of flat layer b2 at 150° C. to storage elastic modulus EHb1 of easily molded layer b1 at 150° C., and expression 2 of 1,000 MPa≤storage elastic modulus ELb1 of easily molded layer b1 at 23° C.

A method for producing a Fiber Metal Laminate component of an airplane, using a manipulator system with an end effector and a control, wherein at least one metal layer and at least one unhardened fiber layer are being stacked onto each other in a mould in a stacking sequence, wherein each stacking cycle comprises picking up a metal layer or a fiber layer from a supply stack according to the stacking sequence, transporting the layer to the mould, placement of the layer at a deposition surface in the mould and depositing the so placed layer onto the deposition surface. After being picked up from the supply stack and before being deposited onto the deposition surface the layer to be stacked can be deformed by the end effector as to adapt the form of the layer to the form of the deposition surface.

A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.

A composite material body (10) includes a first material layer (20) and a second material layer (30) overlapping the first material layer (20). The first material layer (20) and the second material layer (30) are wound to form a flexible and circular rod. Impact absorption is effectively improved and impact resisting strength is enhanced because energy-absorber or damping material or its composition is attached into the composite material body (10). Technical characteristics, effects and objects of this invention are achieved thereby.

A shear web mould system for manufacturing a wind turbine component in form of an I-shaped shear web having a web body and a first web foot flange at a first end of the web body and a second web foot flange at a second end of the web body is described. The system comprises a central moulding portion for forming at least a part of the web body, a first moulding plate for forming at least a part of the first web foot flange, and a second moulding plate for forming at least a part of the second web foot flange. The angles of the first moulding plate and the second moulding plate relative to the central moulding portion are adjustable.

Rotor blade panels, along with methods of their formation, are provided. The rotor blade panel may include one or more fiber-reinforced outer skins having an inner surface; and, a plurality of reinforcement structures on the inner surface of the one or more fiber-reinforced outer skins, where the reinforcement structure bonds to the one or more fiber-reinforced outer skins as the reinforcement structure is being deposited. The reinforcement structure includes, at least, a first composition and a second composition, with the first composition being different than the second composition.