Harris Corporation

Eagle Technology, LLC

Richard I Harless

David S Albert

Dennis Calhoun

Robert T Fandrich, Jr

Andrew J Vajanyi

Therese Boyle

Michael Hoffman

Robert M Taylor

Ronald E Jackson

Ryan Whitney

Ronald Edward Jackson, Jr

Timothy L Fetterman

Keith Nugent

Rodney Sorrell

Christopher L Rose

Stephen J Kolvek

Bibb B Allen

Arthur H White

David Lopez

Miguel Ortega-Morales

Rodolfo V Valentin

Charles F Willer

John Carro

Joshuo Feys

Ryan N Whitney

A space antenna may include an extendible boom movable between stored and deployed positions. An extendible hoop may surround the extendible boom and is movable between the stored and deployed positions. A front cord arrangement may be coupled to the extendible hoop and defines a curved shape in the deployed position, and a reflective layer may be carried thereby. A rear cord arrangement may be behind the front cord arrangement and coupled between the extendible hoop and the extendible boom. The rear cord arrangement may include a rear plurality of interconnected cords defining rear polygons. Tie cords may extend between the front cord arrangement and the rear cord arrangement. A top cord arrangement may be above the reflective layer and coupled between the hoop and the extendible boom.

Space antenna having extendible hoop and interconnected cords defining polygons and related methods

Systems and methods for operating a deployable reflector system. The methods comprising: causing a proximal end of a first link element (LE) located at a first end of a scissoring rib assembly (SRA) to slidingly engage a hub; allowing a proximal end of a second LE of SRA to pivot relative to the hub so as to cause scissor motion of SRA while the first LE is slidingly engaging the hub; causing a distal end of a third LE located at a second end of SRA to pivot relative to the edge member during the scissor motion of SA; allowing the edge member to slidingly engage a fourth LE located at the second end of SRA during pivotal motion of the third LE; and using the edge member to cause vertical movement of a peripheral edge of a reflector relative to the hub while the edge member slidingly engages the fourth LE.

Scissors radial deployable antenna reflector structure

A foldable and expandable antenna reflector, and method of making and using the same are disclosed. The antenna reflector includes a reflector and a support structure where the support structure includes a hub assembly; a hub tower extending from the hub assembly; a plurality of drive strut assemblies that are connected to the hub assembly; and a plurality of rib assemblies connected to the hub tower and to the plurality of drive strut assemblies. Each rib assembly has a multi-piece rib hinge assembly so that each drive strut assembly is pivotably connected to one of the rib hinge assemblies and applies a force to expand the rib assembly in response to the hub assembly applying a force to at least one of the drive strut assemblies to thereby fold or expand the antenna reflector from a first folded configuration to a second expanded configuration.

Folded rib truss structure for reflector antenna with zero over stretch

Reflector antenna system includes a hoop assembly comprising a plurality of link elements which are rigid and extend between a plurality of hinge members, the hoop assembly expandable between a collapsed condition where the link elements are substantially parallel to one another and an expanded condition wherein the link elements define a circumferential hoop around a central axis. The hoop assembly defines a plurality of N rectangular sides, each comprised of an X-member including first and a second link element in a crossed configuration. A plurality of tension elements extend around the periphery of the side and apply tension between opposing ends of the first and second link elements in directions aligned with the top, bottom and two opposing sides.

Deployable reflector antenna system

A fluid pipeline assembly may include a plurality of pipe segments coupled together in end-to-end relation, and a length compensator coupled between an adjacent pair of the plurality of pipe segments to define a fluid passageway therewith. The length compensator may include a tubular body having a plurality of openings spaced apart around a periphery thereof to permit a longitudinal change of the tubular body, and a sealing sleeve extending around the tubular body and covering the plurality of openings.

Fluid pipe assembly including length compensator and related methods

An apparatus for hydrocarbon resource recovery from a subterranean formation includes a radio frequency (RF) source, an RF antenna to be positioned within the subterranean formation to deliver RF power to the hydrocarbon resource within the subterranean formation, and an RF transmission line extending between the RF source and the RF antenna. The RF transmission line may include RF transmission line sections coupled together in end-to-end relation. Each section may include an inner conductor, an outer conductor surrounding the inner conductor, and an outer load-carrying tubular member surrounding the outer conductor. A respective coupling assembly joins ends of adjacent sections together. Each coupling assembly may include an electrical coupler being fixedly connected to first ends of corresponding inner and outer conductors and being slidably connected to opposing second ends of adjacent inner and outer conductors, and a mechanical coupler connecting ends of adjacent load-bearing tubular members together.

Hydrocarbon resource recovery apparatus including RF transmission line and associated methods

A vibration isolation system () for a payload (). The vibration isolation system provides a level of vibration isolation for all vibration translational and rotational components, while minimizing the moment of the payload mass relative to the isolation system. The system includes a base () and a plurality of vibration isolators (). Each vibration isolator includes a semi-rigid first support member () having first portion () positioned below the base and an opposing second portion () positioned above the base, and a second support member () having a first portion () fixed to the base and an opposing second portion () extending above the base. An elastomeric coupling () couples the first support member to the second support member at a height that is approximately equal to a height of a center of gravity () of a combined mass of the base and the payload above the base.

Flexure elastomer antenna isolation system

A deployable reflector includes a support structure having a plurality of support members. The support members are movable from a compact stowed configuration to a deployed configuration. Selected portions of the support members define a prescribed surface when in the deployed configuration. A continuous reflector material is provided restrained against the support members defining the prescribed surface. The reflector material comprises a flexible solid reflector surface.

Solid surface implementation for deployable reflectors

A compactly stowable and deployable support architecture, such as may be used for supporting an energy directing surface, includes radial and hoop support members including upwardly and downwardly extending strut members for deploying a surface, such as a mesh-configured antenna reflector. In one aspect, at least one strut is formed as a telescoping tube member. A multi-sided foldable hoop structure has a plurality of foldable joints, and generally radial struts that extend from and are foldable about corner joints of the hoop structure. At least one drive mechanism is coupled to torque tubes that drive geared hinges of the multi-sided hoop structure. The hinges and drive linkages are geared to synchronously unfold the multi-sided foldable hoop structure and the radial struts, so that the antenna surface may be smoothly deployed from its stowed condition.

Lightweight, compactly deployable support structure with telescoping members

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.

Compactly stowable thin continuous surface-based antenna having radial and perimeter stiffeners that deploy and maintain antenna surface in prescribed surface geometry

A compactly stowable and deployable support architecture, such as may be used for supporting an energy directing surface, includes radial and hoop support members for deploying a surface, such as a mesh-configured antenna reflector. A multi-sided foldable hoop structure has a plurality of foldable joints, and generally radial struts that extend from and are foldable about corner joints of the hoop structure. At least one drive mechanism is coupled to torque tubes that drive geared hinges of the multi-sided hoop structure. The hinges and drive linkages are geared to synchronously unfold the multi-sided foldable hoop structure and the radial struts, so that the antenna surface may be smoothly deployed from its stowed condition.

Lightweight, compactly deployable support structure

An architecture deploying an energy-directing mesh so as to conform with a prescribed surface includes a plurality of radially extending support structures. Cords extend between the support structures in a generally circumferential fashion, and have attachment locations for the energy-directing material offset from the support structures. Each of a plurality of outermost intercostal cords is retained in tension between the support structures and is configured to substantially conform to the perimeter of the prescribed surface. Flexible intercostal compression reactor members are arranged to be placed in tension in a generally arcuate shape between adjacent support structures. Flexible radial compression members are placed in compression between the intercostal compression reactor members and the outermost intercostal cords, so that the outermost cords substantially conform with the perimeter of the prescribed surface. The outermost intercostal cord is supplemented by at least one, and preferably a plurality of, additional, auxiliary cords installed between each pair of support structures. These plural cords are attached to intercostal and radial compression members in a manner that fills in the scallop-shaped gaps of the conventional architecture with an auxiliary mesh attachment structure for conforming the perimeter of the mesh surface with its intended geometrical shape. The combination of these additional intercostal cord sets and their associated radial compression members provides for a more accurate mesh attachment geometry and improved stability.

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Melbourne, FL, United States of America

Richard I Harless