A display device includes a panel, a backlight, and an adhesive tape. The backlight is placed under the panel. The adhesive tape has a light blocking property and is bonded to an end face of the panel and the backlight.

A display device includes a panel, a backlight, and an adhesive tape. The backlight is placed under the panel. The adhesive tape has a light blocking property and is bonded to an end face of the panel and the backlight.

A hybrid metal composite (HMC) structure comprises tiers comprising fiber composite material structures, and additional tiers longitudinally adjacent one or more of the tiers and comprising perforated metallic structures and additional fiber composite material structures laterally adjacent the perforated metallic structures. Methods of forming an HMC structure, and related rocket motors and multi-stage rocket motor assemblies are also disclosed.

A hybrid metal composite (HMC) structure comprises tiers comprising fiber composite material structures, and additional tiers longitudinally adjacent one or more of the tiers and comprising perforated metallic structures and additional fiber composite material structures laterally adjacent the perforated metallic structures. Methods of forming an HMC structure, and related rocket motors and multi-stage rocket motor assemblies are also disclosed.

Sterilizable multilayer material (1), in particular for packaging at least one device for medical use, comprising a non-thermofusible sheet (2) sandwiched between two lower and upper thicknesses (3, 4) of thermofusible material of at least one thermofusible sheet (F), these thicknesses of thermofusible material being welded together across the non-thermofusible sheet.

Sterilizable multilayer material (1), in particular for packaging at least one device for medical use, comprising a non-thermofusible sheet (2) sandwiched between two lower and upper thicknesses (3, 4) of thermofusible material of at least one thermofusible sheet (F), these thicknesses of thermofusible material being welded together across the non-thermofusible sheet.

A system and method for direct and/or active detection and monitoring of civil engineering or other infrastructural structures, and in a preferred embodiment, for hydrocarbon leakage in oil and gas pipelines, storage structures, and/or transportation structures. Particularly, the system and method relate to various nanocomposite sensor coating and data gathering systems. In one embodiment, the apparatus includes a single measurement sensor coating (thin film) sensor. Other embodiments relate to multiple measurement sensor coating systems. The sensor is comprised of either a discrete conductive filament layer, or a single or multiple mesh of interwoven filaments of conductive material in one direction and nonconductive material in a perpendicular direction, as a substrate coated with sensitive coating materials to form a sensor grid. Various embodiments of the sensor coating and their applications are also disclosed.

The invention relates to polyvinylidene fluoride (PVDF) copolymer compositions that have improved crosslinking efficiency and performance. The PVDF copolymer contains a high level (>14 and preferably greater than 16 wt %) of a fluorinated comonomer, and has a high molecular weight as measured by the melt viscosity at 230° C. and 100 sec−1 of 18 to 40 kpoise. The composition can be effectively cross-linked with a low level radiation (high cross-linking efficiency). The cross-linked composition is useful in high-temperature applications, such as automotive wire and cable, and heat shrink tubing.

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.