Abstract: A dimensionally stable honeycomb core and sandwich structure for use in spacecraft applications. The sandwich structure comprises inner and outer faceskins that sandwiches the dimensionally stable honeycomb core. The honeycomb core comprises a fiber and polymer laminate, oriented at a predetermined optimized angle relative to a ribbon direction of the core. Fiber is selected based on strength, modulus and thermal expansion coefficient properties. The polymer is selected based on inherent adhesive properties, coefficient of thermal expansion, moisture absorption, outgassing and its ability to perform in a space environment. The volumetric fraction of fiber and resin and the fiber angular orientation is determined based on the desired system performance, which includes achieving the lowest coefficient of thermal expansion in the plane of the sandwich (ribbon and anti ribbon), as well as through the thickness (z direction).

Abstract: An embedded heat pipe sandwich panel having components made using dissimilar materials is described. An exemplary embedded heat pipe sandwich panel comprises graphite faceskins secured to aluminum honeycomb core using traditional film adhesives. One or more aluminum heat pipes are embedded in the sandwich panel and thermally coupled to the faceskins using a high thermal conductivity gasket material disposed between the panel faceskins and the heat pipes.

Abstract: Thermal interface materials for use in space applications. The thermal interface materials comprise a plurality of graphitized thermally conductive (carbon based) fibers 6 that are contained, immersed, or embedded, in one or more substantially non-outgassing polymer matrix materials. Both relatively stiff and relatively stiff and compliant polymer matrix materials may be used to secure the thermally conductive fibers. The thermally conductive fibers and non-outgassing polymer matrix material may be additionally cured to improve their conductive properties. The polymer matrix materials contain volatile condensable material of less than 0.1 percent and exhibit a total mass loss of less than 1.0 percent per an ASTM E595 procedure.

Abstract: An unfurlable reflector antenna system having one or more unfurlable arms that are each shaped in the form of a parabolic right cylinder when it is unfurled. Each arm comprises an RF reflecting membrane or a thin shell as the reflector structure. Each arm is coupled by way of a line feed to a receiver. The system is specifically designed for use on a spacecraft. Each arm may be stowed by flattening the parabolic membrane or shell, and then rolling up the arm, which is accomplished without stretching. The sparse reflector antenna array system is thus stowable in a compact configuration, yet easily unfurls to provide a very large diameter lightweight reflector.