The present invention generally relates to cementitious material that is a precursor of a magnesium oxychloride cement (MOC) and comprises treated carbon fibers comprising a dispersing agent at least partially coating the carbon fibers and processes for the preparation thereof. The present invention is also related to cementitious material that is a precursor of a magnesium oxychloride cement (MOC) and comprises siliconate and processes for the preparation thereof. The present invention further relates to cementitious material (e.g., pourable, extrudable, moldable and formable cementitious material) and cementitious construction material (e.g., boards, structural laminates, etc.) formed from curing the cementitious material.

A vehicle cargo construct includes a floor, a plurality of side wall panels extending from the floor, and an end wall panel extending from the floor between the plurality of side wall panels. The floor has an upper surface and an oppositely opposed lower surface. Each of the plurality of side wall panels has an exterior surface and an oppositely opposed interior surface. The end wall panel has an exterior surface and an oppositely opposed interior surface. Each of the floor, the plurality of side wall panels, and the end wall panel being formed of a composite sandwich panel material formed of an open area core defining a plurality of pores, a surface sheet adhered to a first face of the open area core by a first adhesive layer, and a structural skin adhered to a second face of the open area core by a second adhesive layer.

It is provided an airbag multilayer complex excellent in flexibility and durability by controlling adhesion between an adhesive layer and a base fabric to a predetermined range, and an airbag using it. This disclosure is an airbag multilayer complex comprising a base fabric and a multilayer film including an outer layer and an adhesive layer that is bonded to one surface of the base fabric. The adhesive strength of the interface between the multilayer film and the base fabric is 5 N/cm or more, the difference in loop stiffness between the airbag multilayer complex and the base fabric is 130 mN/cm or less, the adhesive layer contains a first resin having a hydrogen-bonding capacity, and the difference in Hansen solubility parameter (ΔHSP) between the base fabric and the first resin is 5 MPa.sup.0.5 or less.

An acoustic structure presenting a front surface and a back surface is provided. The acoustic structure includes a support layer comprising the back surface, a honeycomb core comprising a thickness defined between a back and a front, and a plurality of walls that define a plurality of honeycomb cells, wherein the plurality of honeycomb cells extend through the thickness of the honeycomb core opening out toward at least the front, and wherein the back of the honeycomb core is affixed to the support layer, a mesh layer affixed to the front of the honeycomb core, and a knit fabric layer affixed to the mesh layer and conforming to the front surface of the acoustic structure.

Processes for forming fiber reinforced composite aircraft components, i.e., aircraft components formed of a cured fiber-reinforced resin, are provided. According to specific embodiments, a finished surface of the composite aircraft component can be achieved by providing in-mold coating of the cured fiber-reinforced resin by a dried and cured film layer of a water-based primer paint material to thereby achieve a composite aircraft component having an exterior surface that does not necessarily require further finishing.

An ultra-stable structural laminate with fire resistance and a lateral nail pull strength from 44 to 300 pounds of force and an insulation R value from 1 to 40, the ultra-stable structural laminate of a cementious material with a nano-molecular veneer and a foam component catalytically reacted into an expanded closed cell foam having a thickness from ⅛.sup.th inch to 8 inches, a density from 1.5 pounds/cubic foot to 3 pounds/cubic foot that self-adheres to the cementitious material forming an ultra-stable structural laminate with fire resistance and a lateral nail pull strength from 44 pounds to 300 pounds of force, an insulation R value from 1 to 40, a resistance to seismic impact for earthquakes over 3.1 on the Richter Scale, a break point from 7 lbs/inch to 100 lbs/inch; and a resistance to wind shear equivalent to a 15 mph downburst.

The invention relates to a pre-impregnated fibre-reinforced composite material in laminar form, obtained impregnating a fibrous mass with a polymeric binder composition and intended to be subjected to successive forming and complete curing operations to produce a fibre-reinforced composite material. The polymeric binder composition comprises one or more resins chosen in the group consisting of siloxane resins and silsesquioxane resins, and can optionally comprise one or more organic resins. The polymeric binder composition appears as a liquid with viscosity between 55000 and 10000 mPas at temperatures between 50° C. and 70° C. The polymeric binder composition forms a polymeric binder matrix, not cross-linked or only partially cross-linked, that fills the interstices of the fibrous mass. The invention also relates to a method for making said pre-impregnated fibre-reinforced composite material in laminar form. The invention also relates to a manufactured article obtained by hot forming and complete curing of the aforesaid pre-impregnated fibre-reinforced composite material, as well as a method for making said manufactured article.

A soft physiotherapy instrument includes a flexible sheet and a controller. The flexible sheet includes a first flexible layer, a second flexible layer, a plurality of functional layers located between the first flexible layer and the second flexible layer, and a plurality of electrodes electrically connected with the plurality of functional layers. The functional layer includes a carbon nanotube layer including a plurality of carbon nanotubes uniformly distributed. The flexible sheet is electrically coupled with the controller via the plurality of electrodes.

A hole plug that can be used during rework or repair of a composite fiber assembly includes various features that allow placement of a vacuum force to the surface being reworked or repaired. In some implementations, the hole plug can include a plurality of nubs positioned around a shank. The nubs can secure the hole plug to the composite fiber assembly until a cure of an adhesive. The hole plug can further include a plurality of longitudinally oriented grooves extending along the shank and positioned between the plurality of nubs, and can include a notch positioned circumferentially around the shank. The grooves and notch can be used as adhesive carriers that assist with dispersal of a sufficient volume of the adhesive onto other portions of the shank and the composite fiber assembly during insertion of the hole plug into a hole in the composite fiber assembly.

A composite structure of a cargo body and a method of making the same are disclosed. The composite structure includes at least one electrical grid embedded within fiber-reinforced polymer (FRP) layers. The embedded electrical grid includes a plurality of conductive fibers and a plurality of insulating fibers integrated into a polymer matrix of the FRP layers. The embedded electrical grid may be used for power distribution, structural strengthening and stiffness, and/or puncture detection.