Abstract: An antenna reflector for a spacecraft. The antenna reflector comprises one outer layer of an electrically conductive and electrically reflective material including a plurality of openings formed therein. The antenna reflector also comprises at least one inner layer of a fabric material bonded to the outer layer. The fabric material includes a plurality of openings formed therein. The combination of the openings in the outer layer and the openings in the inner layer allow acoustic noise to be transmitted and dissipated through the openings.

Abstract: An improved thermal harness or thermal heat strap that comprises carbon based (graphite) fiber heat conducting elements coupled to graphite, composite, polymer, or metal end attachment brackets. An outer casing comprising a tubular braided sleeve surrounds the heat conducting elements and eliminates possible contamination caused by the graphite fibers. The thermal harness may be advantageously used in electronic applications to dissipate heat from high temperature components.

Abstract: A method and apparatus for grounding multi-layer insulations (MLI) by electric contact, of either of each layer with the other or of all the layers with the underlying structure by means of one or more points of attachment of mechanical type. This makes it possible to simplify the construction procedure and increase the reliability.This method is essentially carried out in the following manner: The layers (FIG. 1) which form the multi-layer insulations (6), (7) (8) are metalized on both faces and have holes (9) which are also metalized. All layers are contacted with each other and with a part of the attachment system (3) which is also electrically conductive.The other part of the attachment system (2) is positioned on the structure (1) in such a manner as to permit the passage of electric charges. By contacting the two parts of the attachment system (2) (3), the multi-layer insulation is grounded with the structure.

Abstract: An antenna reflector structure of the offset-fed type which is suitable for use on spacecraft. The reflector structure includes a central boom, a number of spaced ribs on the boom, an RF reflective mesh layer adjacent to the outer, transverse peripheral edges of the ribs, and contoured angle members for securing the mesh layer to the ribs to provide a specific contour for the reflector surface defined by the mesh layer. The boom can be of one-piece construction or formed from telescoped segments. The reflector structure is deployable and furlable. Several embodiments of the reflector structure are disclosed.

Abstract: Described herein is a method for bonding a skin member such as metal, plastic, perforated acoustic skin, or fiberglass or graphite reinforced plastic, to a honeycomb core support structure such as lightweight hollow hexagonally shaped tubes. Such a method can be used in the construction industry for making panels and walls and similar structures, and in the aerospace industry for making airplane and satellite structures, etc. The adhesive employed is an adhesive-coated fabric material which is partially cured onto the honeycomb and cooled down, following which most of the adhesive material is removed when the coated fabric is peeled away. This leaves an optimum amount of adhesive in the most effective locations on the wall edges of the honeycomb cells where it is needed for bonding the core to the skin. The skin member is then bonded to the honeycomb by bringing the adhesive to its final cure.