Abstract: Described herein are composites that are composed of a plurality of plies with a stiffening grid intimately embedded within the composite. The composite structures have the improved buckling performance characteristics of known isogrid and orthogrid composite structures and yet have a significantly higher damage tolerance that permits such structures to be used in the formation of aircraft and spacecraft designs. Also described herein are methods for making the composites.

Abstract: Embodiments in the present invention provide a system and method of joining structural members. This method involves aligning the first structural member to a metallic substrate when the first structural member has at least one tapered hole or cavity. A metallic or other like material suitable to cold spraying technology is deposited into the tapered cavity to form a shaped or tapered fastener bonded to the metallic substrate. The shape of the fastener secures the first structural member to the metallic substrate. Additionally, a protective insert may be placed within the shaped or tapered cavity to protect the first structural member during hoe cold spraying deposition when the first structural member is a composite material or other like material susceptible to erosion during the cold spraying technique.

Abstract: Described herein are composites that are composed of a plurality of plies with a stiffening grid intimately embedded within the composite. The composite structures have the improved buckling performance characteristics of known isogrid and orthogrid composite structures and yet have a significantly higher damage tolerance that permits such structures to be used in the formation of aircraft and spacecraft designs. Also described herein are methods for making the composites.

Abstract: A method for joining a first structural member and a metallic substrate is provided. This method involves drawing projections from a metallic substrate using a Co-Meld or other like process. Individual plies of composite materials may be laid upon the metallic substrate and projections. These projections penetrate the individual ply or layers of the composite material. A mechanical feature that serves as a retaining device may be located at the distal end of the projections in order to prevent separation of the composite materials from the metallic substrate. The composite materials may be infused with a resin or other material to complete the formation of the composite material. Additionally, other layers of composite material may be placed over the mechanical features located at the distal ends.