A staple cartridge assembly for use with a surgical stapling instrument includes a staple cartridge including a plurality of staples and a cartridge deck. The staple cartridge assembly also includes a compressible adjunct positionable against the cartridge deck, wherein the staples are deployable into tissue captured against the compressible adjunct, and wherein the compressible adjunct comprises a first biocompatible layer comprising a first portion, a second biocompatible layer comprising a second portion, and crossed spacer fibers extending between the first portion and the second portion.

A structural insulation sheathing (SIS) comprises: a first upper facial member, a second lower facial member and an insulation member in intimate, planar contact with both the first upper member and second lower members. The first and second facial members are made from the same reinforcing fiber material less than about 3/16 inch thick. The insulation member comprises a foam layer, said structural insulation sheathing having at least 10×, preferably 15 to 20 times greater strength than its individual components.

A shear band and a non-pneumatic tire is described which includes a ground contacting annular tread portion; a shear band, and a connecting web positioned between a hub and the shear band. The shear band is preferably comprised of a three-dimensional spacer fabric having a first and second layer connected by connecting members. The three-dimensional spacer fabric has a defined depth. The three-dimensional spacer structure further includes a plurality of cells formed between the connecting members, and wherein one or more of the cells are filled with a filler material. The filler material may be foam or a thermoplastic elastomer.

A shear band and a non-pneumatic tire is described which includes a ground contacting annular tread portion; a shear band, and a connecting web positioned between a hub and the shear band. The shear band is preferably comprised of a three-dimensional spacer fabric having a first and second layer connected by connecting members. The three-dimensional spacer fabric has a defined depth. The three-dimensional spacer structure further includes a plurality of cells formed between the connecting members, and wherein one or more of the cells are filled with a filler material. The filler material may be foam or a thermoplastic elastomer.

A joined member assembly method includes: a step in which a substrate is inserted in a gap between a superposed first component and a second component, said substrate being configured from a multilayer fabric that is capable of expanding as a result of heating and that is flexible after expansion and a reinforcing material woven into the multilayer fabric; a step in which the substrate is heated and made to expand in the thickness direction; a step in which the gap is filled with a resin and the substrate is impregnated with the resin; and a step in which the resin is cured. A step in which a seam is created by machining in accordance with a measured gap shape is omitted.

A hybrid metal composite (HMC) structure comprises a first tier comprising a first fiber composite material structure, a second tier longitudinally adjacent the first tier and comprising a first metallic structure and a second fiber composite material structure laterally adjacent the first metallic structure, a third tier longitudinally adjacent the second tier and comprising a third fiber composite material structure, and a fourth tier longitudinally adjacent the third tier and comprising a second metallic structure and a fourth fiber composite material structure laterally adjacent the second metallic structure. At least one lateral end of the second metallic structure is laterally offset from at least one lateral end of the first metallic structure most proximate thereto. 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 a first tier comprising a first fiber composite material structure, a second tier longitudinally adjacent the first tier and comprising a first metallic structure and a second fiber composite material structure laterally adjacent the first metallic structure, a third tier longitudinally adjacent the second tier and comprising a third fiber composite material structure, and a fourth tier longitudinally adjacent the third tier and comprising a second metallic structure and a fourth fiber composite material structure laterally adjacent the second metallic structure. At least one lateral end of the second metallic structure is laterally offset from at least one lateral end of the first metallic structure most proximate thereto. Methods of forming an HMC structure, and related rocket motors and multi-stage rocket motor assemblies are also disclosed.

The present invention provides compositions and methods related to aerogel materials, including polyimide-based aerogels. In particular, aerogel materials optimized to have certain physical and chemical properties such as flexural and compressive strength are provided. In some embodiments, the aerogel materials can be at least partially carbonized.

The present invention provides compositions and methods related to aerogel materials, including polyimide-based aerogels. In particular, aerogel materials optimized to have certain physical and chemical properties such as flexural and compressive strength are provided. In some embodiments, the aerogel materials can be at least partially carbonized.

Fibrous structures containing filaments and solid additives, and more particularly to fibrous structures containing filaments and solid additives wherein the fibrous structure has three or more regions that exhibit different characteristics and/or properties and methods for making same, are provided.