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.

The object is to provide a resin composition for a printed circuit board capable of realizing a printed circuit board that not only has heat resistance and flame retardancy but also is excellent in heat resistance after moisture absorption. The resin composition is a resin composition for a printed circuit board containing a cyanate ester compound (A) obtained by cyanation of a naphthol-dihydroxynaphthalene aralkyl resin or a dihydroxynaphthalene aralkyl resin, and an epoxy resin (B).

A composite foam article is disclosed herein. The composite foam article comprises a polyurethane foam core presenting a first surface and a second surface facing opposite the first surface. A first skin is disposed on the first surface and a second skin is disposed on the second surface. The polyurethane foam core has a density of 15-80 kg/m.sup.3. The first and second skins comprise a plurality of fibers and a polymeric binder. The composite foam article has a weight per unit area of 500-1000 g/m.sup.2 and a strength of greater than 17 N at a post-compression thickness of greater than 2 mm when tested in according with SAE J949 at 23° C.

Embodiments disclosed herein relate to composite laminate structures having high bending stiffness and low heat release properties and methods of making the same.

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.

An impregnation system and a method for impregnating a textile fabric for composite components are described. A matrix 2 can be applied to a textile fabric 1 in such a way that the matrix 2 penetrates it at least partially and/or at least on one side. A first and a second endless belt 1 each designed as a belt loop are provided for the impregnation system. Between the first 4 and the second belt loop 5, the textile fabric 1 can guided on the mutually facing surfaces 6 of the belt loops and can be impregnated there. The deflection rollers 7 are provided in the respective belt loop 4, 5 of the respective endless belts at the deflection areas, with at least one roller being adjustable in the direction of the mutually facing surfaces 6 of the belt loops 4, 5. By adjusting the rollers 8 in the y direction, the wrap angle and thus the pressure exerted on the textile fabric during impregnation is controlled.

Provided is a laminate that is excellent in flexibility and has a high bending strength. Also provided is a reinforcing sheet including such laminate. The laminate of the present invention is a laminate including an adhesive layer and a constraining layer, wherein the constraining layer includes an impregnated layer obtained by impregnating a multilayer base material, which is obtained by laminating a plurality of reinforcing fiber sheet-shaped products in each of which reinforcing fiber yarns are arranged in parallel and knitting the products with a stitching thread to integrate the products, with a thermosetting resin composition. The reinforcing sheet of the present invention includes the laminate of the present invention.

A fiber-reinforced member includes: a base member having a tubular region with an outer circumferential surface extending along and substantially in parallel with an axial direction; and a fiber-reinforced resin layer constituted of a tow prepreg wound in an overlapping manner to cover the outer circumferential surface of the base member along a predetermined direction crossing the axial direction when viewed in a radial direction of the base member, the tow prepreg serving as a widened tape-like member. The tape-like member constituting the fiber-reinforced resin layer has a portion having a fiber line extending along a direction crossing the predetermined direction. A size of a width of the tape-like member constituting the fiber-reinforced resin layer is not less than 100 times and not more than 400 times as large as a size of a thickness of the tape-like member constituting the fiber-reinforced resin layer in the radial direction.

A molding material comprising a fibrous reinforcement layer and a curable resin matrix. The fibrous reinforcement layer comprises a non-woven fabric comprising a single layer of unidirectional tows arranged at an angle greater than 0° in relation to the lengthwise direction of the fabric and a support structure for maintaining the arrangement of the tows.

Methods and apparatuses for making laminated objects from composite materials are shown and described. An adhesion reducing material is applied with a moving printhead to the interfaces between object sections and waste sections of the layers of the objects to facilitate damage-free removal of the waste sections from the object sections. A rotating build platform allows the objects to be formed with the fibers of adjacent layers oriented at non parallel rotational orientations relative to one another. In certain examples, the adhesion reducing material is applied between opposing surfaces of layers wherein one surface is an object surface and the opposing surface is a waste surface. An infrared preheater preheats the side of a current layer being applied to a previous layer to a temperature sufficient to cause the composite adhesive to bond layers together. The infrared preheater and a pressure roller define a lamination assembly that traverses along a travel axis during a lamination operation.