Abstract: An antenna reflector comprising a face skin of graphite fiber reinforced epoxy (GFRE) material is coated with a layer of chromium. The chromium is then coated with aluminum and a protective coating of silicon dioxide is then deposited over the aluminum. The chromium has a thickness sufficiently thin to provide good coverage of the pores of the GFRE material and to minimize distortion causing poor bond due to differences in the coefficient of thermal expansion of the different materials in the presence of temperature cycles. The aluminum is sufficiently thick to provide good reflecting characteristics to minimize the polarizing effects of the graphite face skins.

Abstract: A tubular circular cylindrical member, an attached frustro-conical member, and attached annular stiffening rings are formed of a metal matrix composite (MMC) material such as SiC/Al. The combined cylindrical and conical structure has a tapered wall thickness which reaches a maximum value at the point nearest the attachment of the structure to its launch vehicle. The entire structure and rings are quasi-isotropic, have a homogeneous microstructure, are low in weight, high in strength and stiffness, and are thermally stable with minimum distortion due to exposure to thermal cycling.

Abstract: A deployable spacecraft borne circular reflector structure comprises a plurality of plies of graphite fiber reinforced epoxy (GFRE) fibers, each ply comprising at least two layers of graphite epoxy reinforced fibers having quasi-isotropic properties. A circular ring of multiple layer plies of like construction as the reflector and having a U-shaped cross-section is bonded to the reflector rear surface adjacent the reflector peripheral edge. Each layer of each structure is formed from prepreg graphite fiber epoxy reinforced material.

Abstract: A compact frequency reuse communications antenna includes two superimposed structures, each including Kevlar honeycomb, fabric face skins on the honeycomb, and a reflector over one of the face skins, the two structures being spaced from one another by Kevlar ribs formed of honeycomb material. The directions in which the ribbons of the honeycomb cores of the superimposed structures extend, and the directions of the elements making up the reflector of the fabric warps are chosen to minimize thermal distortions and RF losses while providing high natural frequency and low weight.

Abstract: Imide-amides having the structure ##STR1## wherein ##STR2## are certain cycloaliphatic or aromatic groups and R and R individually are hydrogen, halogen, an alkyl group having from 1 to 4 carbon atoms, hydroxy, carboxyl, and amine and when taken together represent ##STR3## wherein R.sup.2 is the same as R and R.sup.1, have been found to provide cured epoxy resin systems characterized by high temperature stability and excellent mechanical and physical properties.

Abstract: A panel comprising an aluminum honeycomb core and outer face skins of Kevlar, a bi-directional epoxy-reinforced polyparabenzamide fabric which is a thermal and electrical insulator adhering to the core and forming the opposite flat surfaces of the panel. Solar cells are glued directly to one face skin while a set of epoxy-reinforced carbon fiber stiffeners are glued to the other face skin. The composite structure has a coefficient of thermal expansion closely matching that of the solar cells providing a very lightweight and stiff structure.

Abstract: Imide-anhydrides having the structure ##STR1## wherein 1 and 2 are certain cycloaliphatic or aromatic groups and Z is selected from certain imide-anhydride and other substituents have been found to provide cured epoxy resin systems characterized by high temperature stability and excellent mechanical and physical properties.

Abstract: Imide-amines having the structure ##STR1## wherein ##STR2## are certain cycloaliphatic or aromatic groups and R and R individually are hydrogen, halogen, an alkyl group having from 1 to 4 carbon atoms, hydroxy, carboxyl, and amine and when taken together represent ##STR3## wherein R.sup.2 is the same as R and R.sup.1, have been found to provide cured epoxy resin systems characterized by high temperature stability and excellent mechanical and physical properties.