Abstract: Methods and compositions concerning an ultraviolet light curable formulation useful for repairing composite materials including the repair of a hole in the exterior of an airplane. The formulation may contain an acrylic oligomer, an acrylic monomer, an organic peroxide, a dialkylaniline promoter, a photoinitiator. The formulation can include a filler such as carbon fabric or Kevlar fabric.

Abstract: A process for coating a metallic surface of an aircraft. The process includes applying to the metallic surface a composition that polymerizes to form a polyurea having a tensile strength of more than 3500 psi and at least 700% elongation. The polyurea can be formed from an A-side and a B-side, where the weight percents of components for the A-side are: from about 30 to about 65 percent of polyisocyanate; from about 15 to about 70 percent of a polytetramethylene ether glycol; diluent, from 0 to about 20 percent; where the weight percents of components for the B-side are: from 35 to about 40 percent of one or more aromatic diamines; from about 20 to about 70 percent of one or more amine terminated polyether polyols.

Abstract: A polysilazane composition, formulated from a vinyl silazane and an organometallic accelerator, and associated methods thereof.

Abstract: A polysilazane composition, formulated from a vinyl silazane and an organometallic accelerator, and associated methods thereof.

Abstract: A composition and process for manufacturing a camouflaged aircraft component. The process includes providing an aircraft component; applying an uncured coating onto the aircraft component wherein the uncured coating comprises polysilazane resin, at least one pigment, at least one matting agent, and at least one diluent; allowing the diluent to evaporate; curing the coating to provided a cured coating that comprises cured polysilazane, at least one pigment, and at least one matting agent.

Abstract: A process for coating a metallic surface of an aircraft. The process includes applying to the metallic surface a composition that polymerizes to form a polyurea having a tensile strength of more than 3500 psi and at least 700% elongation. The polyurea can be formed from an A-side and a B-side, where the weight percents of components for the A-side are: from about 30 to about 65 percent of polyisocyanate; from about 15 to about 70 percent of a polytetramethylene ether glycol; diluent, from 0 to about 20 percent; where the weight percents of components for the B-side are: from 35 to about 40 percent of one or more aromatic diamines; from about 20 to about 70 percent of one or more amine terminated polyether polyols.

Abstract: A process for coating a metallic surface of an aircraft. The process includes applying to the metallic surface a composition that polymerizes to form a polyurea having a tensile strength of more than 3500 psi and at least 700% elongation. The polyurea can be formed from an A-side and a B-side, where the weight percents of components for the A-side are: from about 30 to about 65 percent of polyisocyanate; from about 15 to about 70 percent of a polytetramethylene ether glycol; diluent, from 0 to about 20 percent; where the weight percents of components for the B-side are: from 35 to about 40 percent of one or more aromatic diamines; from about 20 to about 70 percent of one or more amine terminated polyether polyols.

Abstract: A hydrogel composition and a method for protecting a surface from thermal injury is disclosed. The method comprises applying a hydrogel composition to the surface to protect the skin from exposure to a heat flux, wherein the hydrogel is of a type and applied in an amount effective to reduce heat flux by at least 40 percent when exposed to a heat flux of 40 kW/m2. Representative examples of such hydrogels include ionized carboxymethyl cellulose hydrogel, ionized polyacrylate hydrogel, and a polymer formed from acrylic acid and crosslinked with polyalkenyl ethers or divinyl glycol.

Abstract: Methods and compositions concerning an ultraviolet light curable formulation useful for repairing composite materials including the repair of a hole in the exterior of an airplane. The formulation may contain an acrylic oligomer, an acrylic monomer, an organic peroxide, a dialkylaniline promoter, a photoinitiator. The formulation can include a filler such as carbon fabric or Kevlar fabric.

Abstract: A composition and process for manufacturing a camouflaged aircraft component. The process includes providing an aircraft component; applying an uncured coating onto the aircraft component wherein the uncured coating comprises polysilazane resin, at least one pigment, at least one matting agent, and at least one diluent; allowing the diluent to evaporate; curing the coating to provided a cured coating that comprises cured polysilazane, at least one pigment, and at least one matting agent.

Abstract: A composition and process for manufacturing a camouflaged aircraft component. The process includes providing an aircraft component; applying an uncured coating onto the aircraft component wherein the uncured coating comprises polysilazane resin, at least one pigment, at least one matting agent, and at least one diluent; allowing the diluent to evaporate; curing the coating to provided a cured coating that comprises cured polysilazane, at least one pigment, and at least one matting agent.

Abstract: A process for coating a metallic surface of an aircraft. The process includes applying to the metallic surface a composition that polymerizes to form a polyurea having a tensile strength of more than 3500 psi and at least 700% elongation. The polyurea can be formed from an A-side and a B-side, where the weight percents of components for the A-side are: from about 30 to about 65 percent of polyisocyanate; from about 15 to about 70 percent of a polytetramethylene ether glycol; diluent, from 0 to about 20 percent; where the weight percents of components for the B-side are: from 35 to about 40 percent of one or more aromatic diamines; from about 20 to about 70 percent of one or more amine terminated polyether polyols.

Abstract: A composition and process for manufacturing a camouflaged aircraft component. The process includes providing an aircraft component; applying an uncured coating onto the aircraft component wherein the uncured coating comprises polysilazane resin, at least one pigment, at least one matting agent, and at least one diluent; allowing the diluent to evaporate; curing the coating to provided a cured coating that comprises cured polysilazane, at least one pigment, and at least one matting agent.

Abstract: This invention concerns an epoxy coating for use as a non-skid surface for applications such as the deck of an aircraft carrier. The epoxy coating can be formulated from (a) an amine curing agent, (b) an epoxide-containing toughening agent such as a polysulfide and/or a polythioether, (c) an epoxy resin, (d) a rubber toughening agent, and (e) an optional fire retardant, a glass fiber thixotrope and impact toughening agent, an optional pigment, an optional corrosion inhibitor, an optional moisture penetration inhibitor, an optional ultraviolet light stabilizer, an optional abrasive aggregate, or a combination thereof.

Abstract: This invention concerns an epoxy coating for use as a non-skid surface for applications such as the deck of an aircraft carrier. The epoxy coating can be formulated from (a) an amine curing agent, (b) an epoxide-containing toughening agent such as a polysulfide and/or a polythioether, (c) an epoxy resin, (d) a rubber toughening agent, and (e) an optional fire retardant, a glass fiber thixotrope and impact toughening agent, an optional pigment, an optional corrosion inhibitor, an optional moisture penetration inhibitor, an optional ultraviolet light stabilizer, an optional abrasive aggregate, or a combination thereof.

Abstract: This invention concerns an epoxy coating for use as a non-skid surface for applications such as the deck of an aircraft carrier. The epoxy coating can be formulated from (a) an amine curing agent, (b) an epoxide-containing toughening agent such as a polysulfide and/or a polythioether, (c) an epoxy resin, (d) a rubber toughening agent, and (e) an optional fire retardant, a glass fiber thixotrope and impact toughening agent, an optional pigment, an optional corrosion inhibitor, an optional moisture penetration inhibitor, an optional ultraviolet light stabilizer, an optional abrasive aggregate, or a combination thereof.

Abstract: An ultraviolet (UV) light curable formulation useful for repairing composite materials, comprising: an acrylic oligomer, an acrylic monomer, and a photoinitiator. This formulation may include fiberglass. The photoinitiator can be a combination of a bis-acylphosphine oxide and an alpha hydroxy ketone. The formulation can cure rapidly, such as in about 20 minutes. The cured formulation can have a Tg above 150° C.

Abstract: An ultraviolet (UV) light curable formulation useful for repairing composite materials, comprising: an acrylic oligomer, an acrylic monomer, and a photoinitiator. This formulation may include fiberglass. The photoinitiator can be a combination of a bis-acylphosphine oxide and an alpha hydroxy ketone. The formulation can cure rapidly, such as in about 20 minutes. The cured formulation can have a Tg above 150° C.

Abstract: An ultraviolet (UV) light curable formulation useful for repairing composite materials, comprising: an acrylic oligomer, an acrylic monomer, and a photoinitiator. This formulation may include fiberglass. The photoinitiator can be a combination of a bis-acylphosphine oxide and an alpha hydroxy ketone. The formulation can cure rapidly, such as in about 20 minutes. The cured formulation can have a Tg above 150° C.

Abstract: Syntactic foam, comprising a cured product obtained from a composition which comprises: at least one epoxy resin, a curing agent, and hollow microspheres, wherein the microspheres have a density less than 0.25 g/cc and wherein the cured syntactic epoxy foam has a density less than 0.7 g/cc. The foam may be used to repair composites in aircraft.