Embossed fibrous structures that exhibit a Dry Burst of greater than 270 g as measured according to the Dry Burst Test Method and more particularly to embossed fibrous structures that exhibit a Dry Burst of greater than 270 g as measured according to the Dry Burst Test Method and a Total Dry Tensile of less than 2375 g/76.2 mm and/or a Geometric Mean Total Dry Tensile of less than 1130 g/76.2 mm as measured according to the Tensile Strength Test Method are provided.

A fiber structure for a fiber-reinforced composite material includes a section in which a width varies continuously along a central axis in a plan view. In a section in which the width increases continuously along the central axis, discontinuous fibers are aligned radially along the central axis, and both a thickness of the fiber structure and a density of the discontinuous fibers are uniform.

In a composite material structure, which is configured as a fiber-reinforced plastic composite material extending in one direction and having a plurality of holes defined at intervals in a row in the one direction and which is subjected to a tensile load and/or a compressive load in the one direction, a peripheral region around the holes comprises a first area obtained by bending composite material, which is reinforced using continuous fibers that have been made even in a longitudinal direction, so that a center line of a width of the composite material weaves between adjacent holes and zigzags in the one direction. A tensile rigidity and/or a compressive rigidity in the one direction of the peripheral region around the holes is lower than a tensile rigidity and/or a compressive rigidity in the one direction of other regions that surround the peripheral region.

A hybrid carbon/fiberglass structural component or beam for an aircraft is constructed with layers of strips of glass fibers interspersed with layers of strips of unidirectional carbon fibers where the carbon fibers are oriented only in alignment with or along the longitudinal direction of the length of the beam thereby adding strength and stiffness to the beam while reducing weight and manufacturing costs.

A hybrid carbon/fiberglass structural component or beam for an aircraft is constructed with layers of strips of glass fibers interspersed with layers of strips of unidirectional carbon fibers where the carbon fibers are oriented only in alignment with or along the longitudinal direction of the length of the beam thereby adding strength and stiffness to the beam while reducing weight and manufacturing costs.

A multilayer composite is disclosed comprising a heat shrinkable polymer layer and a nanofiber layer. Methods of forming the composite and uses thereof are also described.

Electromagnetic radiation scanning is used to monitor the integrity of a composite laminate structure. The composite laminate structure is optically resonant at a frequency of electromagnetic radiation, allowing inconsistencies in the laminate to be detected and mapped.

Fibrous structures that exhibit a Geometric Mean Modulus (GM Modulus) of less than 1402.4 g/cm at 15 g/cm as measured according to the Modulus Test Method described herein and a Geometric Mean Elongation (GM Elongation or GM Elong) of less than 10.2% measured according to the Elongation Test Method described herein are provided.

Woven fabrics are formed from high tenacity fibers or tapes that are loosely interwoven with adhesive coated filaments, to composite articles formed therefrom, and to a continuous process for forming the composite articles.

Multilayer material sheets containing unidirectional high performance fibers are obtained by a process which includes the steps of positioning the fibers in a parallel fashion, consolidation of the fibers to obtain a monolayer, stacking at least two monolayers such that the fiber direction in one monolayer is at an angle a to the direction of the fibers in an adjacent monolayer and fixation whereby the stack of at least two monolayers is subjected to a pressure and temperature treatment for a duration of a least 2 seconds, followed by cooling the stack under pressure to a temperature of 120 C. or lower. The multilayer material sheet has a reduced uptake of liquids.