A fibrous material or composite including a plurality of layers joined to one another, for example, by needlepunching, is disclosed. The fibrous composite generally has an asymmetrical stretch profile, such that the fibrous composite is more extensible in the cross-machine direction than in the machine direction. The fibrous composite may find particular use in forming a cure-in-place pipe liner.

A stretch laminate is disclosed. The stretch laminate may include a layer of nonwoven material that includes an accumulation of filaments and has an inner surface and an outer surface, the outer surface having an ordered arrangement of zones, each zone having an attenuated region adjacent to a build-up region wherein the attenuated region has a first basis weight and the build-up region has a second basis weight greater than the first basis weight, the difference in basis weights corresponding to disposition of the filaments according to the ordered arrangement. The stretch laminate may include a plurality of elastic strands space apart from each other in a crotch-stretch direction. In some examples the elastic strands may have an Average Strand Spacing no greater than 3 mm and/or an Average Decitex no greater than 300, and/or an Average Pre-Strain no greater than 250 percent.

The application relates to a fire-resistant textile composite having an upper surface and a lower surface. The composite contains a nonwoven layer and a knit layer. The nonwoven layer has a first and second side and contains a nonwoven textile. The nonwoven textile contains a plurality of first fire-resistant fibers, where the first fire-resistant fibers are non-thermoplastic. The nonwoven layer forms the lower surface of the textile composite. The knit layer contains a knit textile having a first and second side and the second side of the knit layer is adjacent to the first side of the nonwoven layer. The knit textile contains a plurality of second fire-resistant yarns, where the second fire-resistant yarns are non-thermoplastic. At least a portion of the first fire-resistant fibers from the nonwoven layer extend through the first side of the knit layer and form the upper surface of the textile composite.

A method and apparatus for producing elastic laminates, wherein a first continuous elastic film is stretched in a transverse direction by a spreader device and is applied on a transfer wheel on which it is cut longitudinally to form at least two parallel continuous elastic films which are transferred on a non-woven web held on the an outer cylindrical surface of an anvil wheel.

A composite laminate structure includes one or more layers of prepreg and a thermoplastic polyurethane film layer on the surface of the one or more prepregs. A method of making a composite laminate structure including a thermoplastic polyurethane film is also provided.

A stretch laminate is disclosed. The stretch laminate may include a layer of nonwoven material that includes an accumulation of filaments and has an inner surface and an outer surface, the outer surface having an ordered arrangement of zones, each zone having an attenuated region adjacent to a build-up region wherein the attenuated region has a first basis weight and the build-up region has a second basis weight greater than the first basis weight, the difference in basis weights corresponding to disposition of the filaments according to the ordered arrangement. The stretch laminate may include a plurality of elastic strands space apart from each other in a crotch-stretch direction. In some examples the elastic strands may have an Average Strand Spacing no greater than 3 mm and/or an Average Decitex no greater than 300, and/or an Average Pre-Strain no greater than 250 percent.

A panel (1000) for a cabin of an aircraft, the panel (1000) including a laminate (150) with a first layer formed of lithiated carbon fibers (100), a second layer form of carbon fibers with a cathode lithium coating (200), and an electrolyte-containing separator (300) interposed between the first and the second layers and a pressure sensor (50a, 50b) on an outer surface of the laminate (150), and a switch (40) to regulate a voltage to the laminate (150) based on an output of the pressure sensor (50a, 50b) so that the panel (1000) expands.

A panel (1000) for a cabin of an aircraft, the panel (1000) including a laminate (150) with a first layer formed of lithiated carbon fibers (100), a second layer form of carbon fibers with a cathode lithium coating (200), and an electrolyte-containing separator (300) interposed between the first and the second layers and a pressure sensor (50a, 50b) on an outer surface of the laminate (150), and a switch (40) to regulate a voltage to the laminate (150) based on an output of the pressure sensor (50a, 50b) so that the panel (1000) expands.

Methods and (articles of manufacture therefrom) including forming an elastic film from a polymer composition; tensioning the elastic film to a stretch ratio of between 2 and 6 in the MD; laminating the elastic film to an extensible facing to provide an elastomeric laminate having a CD hysteresis loss of 70% or less and an MD hysteresis loss of 50% or less.

Methods and (articles of manufacture therefrom) including forming an elastic film from a polymer composition; tensioning the elastic film to a stretch ratio of between 2 and 6 in the MD; laminating the elastic film to an extensible facing to provide an elastomeric laminate having a CD hysteresis loss of 70% or less and an MD hysteresis loss of 50% or less.