Abstract: A reflector support system is provided that includes a backing structure having a plurality of struts. The backing structure may have a plurality of hubs, each of the plurality of hubs may be configured to couple to two or more of the plurality of struts, each of the plurality of hubs may be configured to couple to another one of the plurality of hubs using one of the plurality of struts, each of the plurality of struts is configured to couple to at least two of the plurality of hubs. The backing structure may have a plurality of feet, each of the plurality of feet configured to couple to a corresponding one of the plurality of hubs, the plurality of feet are configured to couple to a reflector. In addition, a synthesis for mechanical adjustment of the reflector support system is provided.

Abstract: A reflector support system is provided that includes a backing structure having a plurality of struts. The backing structure may have a plurality of hubs, each of the plurality of hubs may be configured to couple to two or more of the plurality of struts, each of the plurality of hubs may be configured to couple to another one of the plurality of hubs using one of the plurality of struts, each of the plurality of struts is configured to couple to at least two of the plurality of hubs. The backing structure may have a plurality of feet, each of the plurality of feet configured to couple to a corresponding one of the plurality of hubs, the plurality of feet are configured to couple to a reflector. In addition, a synthesis for mechanical adjustment of the reflector support system is provided.

Abstract: A high power radiating antenna system is disclosed which includes a ground plane and an electrically conductive power radiating element. The power radiating element includes a first, power feed end proximal to the ground plane and a second end distal to the ground plane. The power radiating element further includes an integrally formed heat pipe adapted for dissipating thermal energy generated in the power radiating element during operation of the antenna system.

Abstract: A broadband mesh antenna and a phased array broadband mesh antenna are provided. The antenna of the present invention is a mesh antenna system that may be implemented with printed circuit board technology and wired technology that operates with increased bandwidth. The mesh antenna system provides for a single mesh antenna to operate at a wide range of frequencies. The antenna may be employed as a high efficient broadband antenna for rockets, space vehicles and ships when placed inside a metallic open box.

Abstract: A broadband mesh antenna and a phased array broadband mesh antenna are provided. The antenna of the present invention is a mesh antenna system that may be implemented with printed circuit board technology and wired technology that operates with increased bandwidth. The mesh antenna system provides for a single mesh antenna to operate at a wide range of frequencies. The antenna may be employed as a high efficient broadband antenna for rockets, space vehicles and ships when place inside a metallic open box.

Abstract: A deployable reflecting structure for use in space applications, preferably for RF antenna structures, includes at least one rigid section having a reflective surface and at least one bendable section having a reflective surface and being connected to the rigid section. The bendable section is movable between a first, stowed position in which the reflective surface of the bendable section is at least partially overlapping with the reflective surface of the rigid section, and a second, deployed position in which the reflective surfaces are continuous and non-overlapping.

Abstract: To reduce the time required to build spacecraft, and to reduce costs, the spacecraft are members of a set of spacecraft. Each member has the same structural members, such as panels, but different members of the set are elongated by multiples of an increment such as five inches. The structural panels of larger members of the set are elongated in the longitudinal direction, to provide more surface area for mounting payload, and to provide more heat rejection surface. The propellant tank(s), which may be fuel and oxidizer tanks, are spherical in the shortest members of the set, and are increased in length by addition of cylindrical sections, to provide greater volume in larger members to thereby provide longer operating life. Similarly, the solar panels, heat pipes and the like may be elongated.

Abstract: The invention lies in a support transition which is affixed to a spacecraft for supporting the spacecraft on a support ring of a booster or launch vehicle. The transition is in the general form of a ring defining a longitudinal axis parallel to the axis of the spacecraft and the booster. The transition has a circular end adapted to mate with the booster support ring, and a polygonal end adapted to mate with the spacecraft, and makes a smooth transition between ends. The circumference of the transition, at any cross-section transverse to the longitudinal axis, is constant. The transition is advantageously made of a composite material such as fiber-reinforced solidified liquid or carbon-fiber reinforced resin. In a particular embodiment, the polygonal end is a square rectangle, with four straight sides and rounded corners. In a set of spacecraft, the transition remains the same size.

Abstract: An apparatus and method for fastening together spacecraft panels includes the use of fastener pairs, one of which has preformed therein an aperture which is larger in diameter than the body of a tolerance takeup piece which is to pass therethrough. A washer which takes up the clearance is adhesively fastened to one of the fastener halves, and allowed to cure while the panels are in their desired position. Thus, a high-tolerance mating pair can be finalized in position at a late state in fabrication, without undesirable drilling or reaming. In a first particular embodiment, a flat washer, having an inside diameter which closely fits the corresponding bolt, is adhesively fastened over the preformed oversize aperture of a fitting.

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.