Abstract: A lightweight, high strength structure is described where a core material has a first and second metal matrix composite layer on surfaces of the core material. A sandwich type structure may be formed. The core material may be a solid material, a foam, a honeycomb structure, or may be a channeled material. The metal matrix composite layers may include fiber reinforced metal matrix composites.

Abstract: The present invention provides for assemblies comprising metal matrix composite bars where the bars only intermittently have mutual contact. Minimally two bars of metal matrix composite are joined, for example by lap joints, or by the use of incorporated tabs and slots or over-lapping slots, at areas of mutual contact to form the assemblies. The metal matrix composite assemblies of the present invention may be readily assembled to provide structures, supports, or sub-assemblies, and the like, that may exhibit high strength and stiffness coupled with relatively low mass. Additionally, such assemblies may withstand exposure to elevated temperatures higher than can be tolerated by polymeric composites. Such assemblies are expected to be particularly suitable for lightweight, stiff support structures for space booms, satellite structures, mirror backings, solar panel supports, wall reinforcement, and the like.

Abstract: A lightweight, high strength structure is described where a core material has a first and second metal matrix composite layer on surfaces of the core material. A sandwich type structure may be formed. The core material may be a solid material, a foam, a honeycomb structure, or may be a channeled material. The metal matrix composite layers may include fiber reinforced metal matrix composites.

Abstract: The present invention provides for assemblies comprising metal matrix composite bars where the bars only intermittently have mutual contact. Minimally two bars of metal matrix composite are joined, for example, by lap joints, or by the use of incorporated tabs and slots or over-lapping slots, at areas of mutual contact to form the assemblies. The metal matrix composite assemblies of the present invention may be readily assembled to provide structures, supports, or sub-assemblies, and the like, that may exhibit high strength and stiffness coupled with relatively low mass. Additionally, such assemblies may withstand exposure to elevated temperatures higher than can be tolerated by polymeric composites. Such assemblies are expected to be particularly suitable for lightweight, stiff support structures for space booms, satellite structures, mirror backings, solar panel supports, wall reinforcement, and the like.