Abstract: An antenna reflector (100, 700) comprising a centrally located hub (120), inner ribs (108) rotatably secured at a proximal end to the hub, outer ribs (110) extendible from the inner ribs, and a guideline truss structure (132, 160) configured to support a flexible antenna reflector surface (122). The inner ribs are rotatable from a stowed position in which they are generally aligned with a central axis of the hub, to a rotated position in which they extend in a radial direction relative to the central axis. The guideline truss structure is secured to each outer rib using standoff cords attached at intermediate locations along a length of the outer rib between opposing ends (116, 118) thereof. The outer ribs are configured to be linearly displaced respectively along an elongated length of the inner ribs from a proximal position adjacent to the hub, to an extended position distal from the hub.

Abstract: An antenna reflector (100, 700) comprising a centrally located hub (120), inner ribs (108) rotatably secured at a proximal end to the hub, outer ribs (110) extendible from the inner ribs, and a guideline truss structure (132, 160) configured to support a flexible antenna reflector surface (122). The inner ribs are rotatable from a stowed position in which they are generally aligned with a central axis of the hub, to a rotated position in which they extend in a radial direction relative to the central axis. The guideline truss structure is secured to each outer rib using standoff cords attached at intermediate locations along a length of the outer rib between opposing ends (116, 118) thereof. The outer ribs are configured to be linearly displaced respectively along an elongated length of the inner ribs from a proximal position adjacent to the hub, to an extended position distal from the hub.

Abstract: A space deployable antenna reflector surface is formed as a continuous laminate that is shaped to conform with a prescribed energy-focusing surface geometry. The laminate is formed of very thin layers of flexible material, such as very thin sheets of graphite epoxy, containing collapsible radial and perimeter stiffening regions or stiffeners. Due to its thinness, the reflector laminate is collapsible into a folded shape, that facilitates stowage in a restricted volume, such as aboard the space shuttle. The stiffening elements of the laminate antenna structure of the invention facilitate deploying and maintaining the reflector in its intended geometric shape, and collapsing the reflector laminate into a compact serpentine stowed configuration.

Abstract: A collapsible conductive material includes a generally mesh-configured, collapsible surface, that defines the intended reflective geometry of an antenna, and a distribution of tensionable cords and ties, which attach the reflective mesh to an inflatable support structure. The antenna is fully deployed once the inflatable support structure is inflated to at least a minimum pressure necessary to place the attachment tie/cord arrangement in a tension that causes the reflective surface to acquire a prescribed (e.g., parabolic) geometry. Preferably, the inflation pressure is above the minimum value, so as to allow for pressure variations (drops) within the support structure.

Abstract: A splined radial panel solar collector structure approximates compound curvature surfaces by a three-dimensional arrangement of compactly stowable flat reflective panel segments mounted on a collapsible, space-deployable support structure of linear components. The support framework is formed of an umbrella-like framework of radially-extending ribs, struts and cords which deploy away from a central hub to form a system of radial trusses. A semirigid reflective surface structure is divided into sections of radial panels which are supported and shaped by an arrangement of radially tensioned flexible tape members aligned with the ribs. Connecting ties between the tapes and the ribs cause the tapes to assume a catenary curve. The ribs and flexible tape members are bridged circumferentially by sets of cords and ties to which the panels are joined. These cord and tie pairs place the panels in bending to effect a "splined" approximation of a parabola in the radial direction.