Abstract: The apparatus for detecting electromagnetic radiation (300), in particular for radio astronomic applications, comprises a receiving element (10), and a plurality of reflecting elements (20) forming a surface (30), capable of receiving the electro-magnetic radiation (300) and to direct it at the receiving element (10) The apparatus (1) further comprises a plurality of actuators (40) used to vary the position of the reflecting elements (20) and a plurality of smart circuit blocks (60), each designed to receive as input a control signal (loo) from a processing unit (50) and to generate as output a corresponding displacement parameter (101) used by an actuator (40) to position the reflecting elements (20) connected to it.

Abstract: An antenna directivity enhancer to enhance the directivity of an antenna is disclosed. The enhancer has a 3-dimensional structure in a predefined 3-dimensional shape when operating to enhance the directivity of an antenna. The 3-dimensional structure can be flexibly collapsible into 2-dimensional flat surfaces, with at least two of the surfaces not required to have any space between them when the structure is collapsed. The direction where the directivity is enhanced can be changed as desired. The enhancer can include just one reflecting surface, or at least two reflecting surfaces. In yet another embodiment, the enhancer includes a curved surface when the enhancer is in its predefined 3-dimensional shape.

Abstract: An integrated reflector and boom (1) for a deployable space based reflector antenna includes a facesheet (9) of stiff reflective material and a stiff lattice or grid structure bonded to the facesheet in a reflector portion of the assembly and defines a boom to the assembly. The grid structure is formed of ribs (13, 15, 17 & 19) that interlock through slots formed in the ribs, arranged in a symmetric pattern that defines an isogrid structure in the reflector portion and in at least a part of the boom assembly. At least some of the ribs extend in one piece from the reflector portion and into the boom. One of those ribs (13) is located along an axis of symmetry of the grid structure.

Abstract: A boom structure is deployable from a collapsed, stowable configuration to an elongated truss configuration. The boom structure contains a plurality of truss-forming multi-sided bays. A bay contains a pair of battens joined together at corner regions by foldable longerons. A side of a bay has a plurality of diagonal cord members crossing one another and connected to diagonally opposed corner regions of the side. When the longerons are in their folded positions, the battens are nested together against one another in a stacked arrangement and the diagonal cord members flex into a compact stowed configuration between adjacent battens. The stowed battens are compressed to each other at their corners to form a stowed structure capable of reacting loads.

Abstract: The invention is an inflatable antenna system. The antenna system includes an inflatable lenticular dish. The dish is enclosed in an inflatable radome. The inflatable radome stabilizes the orientation of the dish and protects it from environment conditions such as wind.

Abstract: A deployable antenna reflector comprising a central dish and a plurality of deployable sheet-like panels arranged around the central dish. The reflector further comprises a central supporting body, whereon the central dish is fixedly mounted and whereto the deployable sheet-like panels are hinged. The rotation axes of the individual deployable sheet-like panels are tilted with respect to the center point of the central dish. In the stowed configuration of the reflector, the deployable sheet-like panels are at least partially deflected in order to minimize the envelope of the reflector and that the panels relax upon deployment.

Abstract: An integral reflector-boom assembly (1) for a deployable antenna includes a facesheet (9) of stiff reflective material and a stiff lattice or grid structure bonded to the facesheet to form a reflector (3) portion of the assembly and a boom (5). Interlocked ribs (13, 15, 17 & 19) are arranged in a pattern that defines an isogrid structure in the reflector portion and at least a part of the boom assembly. Some of the ribs (13) extend in one piece from the reflector portion through the boom portion.

Abstract: A system for shaping a single curvature parabolic membrane. The system includes a shaping rail and a bending rail. At least two rollers operably connect the shaping rail and the bending rail. The rollers are operable to alter a position of the shaping rail relative to the bending rail. A compression adjustment bar is operably connected to ends of the shaping rail to apply a load to the shaping rail. A bending adjustment bar is operably connected to ends of the bending rail to apply a moment to the shaping rail through the at least two rollers.

Abstract: Tensegrity units may be used to form a tensegrity structure. Each tensegrity unit may include n face tension members, n continuous tension members, and n compression members. A bracket for the tensegrity unit may allow for adjustment of position of portions of the tension members when the tensegrity unit is not in a deployed state. The tension members may be coupled to the tensegrity unit so that there are no loose tension member ends. The unit may be deployed from a collapsed state by positioning the compression members and tension members in a proper orientation and adjusting the length of at least one compression member. Adjusting the length of at least the one compression member may allow tension to be applied to each tension member. A tensegrity structure may be formed from tensegrity units by joining a number of tensegrity units together.

Abstract: An inflatable, multifunction, multipurpose, parabolic reflector apparatus 10 having a plurality of manufactured parabolic mirrors 14, 16 made from a pressure-deformable reflective covering of an inflatable ring 12 for focusing electromagnetic energy from radio frequency radiation (RF) through the ultraviolet radiation (UV) and solar energy for (1) heating and cooking, for (2) electrical power generation, for (3) enhancing the transmission and reception of radio signals, for (4) enhancing vision in low-light environments, and for (5) projection of optical signals or images. The device also has non-electromagnetic uses, such as the collection of water. A first main embodiment utilizes two reflective membranes. A second main embodiment utilizes a reflective membrane and a transparent membrane. Portability is enhanced by complete collapsing of the inflatable device.

Abstract: An adaptive reflector antenna includes an adaptive reflector and a mechanism for simultaneously effecting feed rotation and shape change for the adaptive reflector so as to maintain antenna performance with large scan angles while simultaneously reducing weight, complexity, and cost.

Abstract: The present invention provides an electromagnetic reflector comprising a deployable support frame carrying at least one sheet element designed to form a reflective surface when in the deployed state, wherein the support frame comprises a band that is suitable for being packaged in a folded state and that is suitable for returning to a deployed state in the absence of external constraint, the band being in the form of three rings that are orthogonal in pairs, and the reflector further comprising eight generally triangular panels of sheet material.

Abstract: Radar reflective rescue and safety devices comprise radar permeable coverings around a plurality of reflectors. The radar reflective material may be incorporated into inflatable life vests or foam filled life vests. Additionally, inflatable life rafts with radar reflective cells are able to help personnel lost at sea to be found by radar. The radar reflective cells may also be incorporated into an inflatable cylindrical tube as radar cross-section enhancer separate from other flotation devices. The reflectors are flexible metallic material that forms reflective cavities once the shell is inflated. The reflective cavities may appear as flat surfaces, tilted surfaces, corner reflectors or some combination thereof depending upon the orientation of the cavities to an incident radar wave.

Abstract: A hybrid parabolic reflector phased array antenna system which is stowable in a space vehicle and is deployable in space. The antenna includes a large torus which acts as a support structure for a plurality of small reflector cells called super elements, each including its own reflector and an array of feed elements. The torus supports a stretched reflector mesh and matching back-up catanary wires that provide a mechanism for pulling the reflector surface of the cells down to an exact paraboloid. A set of rigid corner posts for stretching the mesh fabric for forming multiple reflectors is also provided. The torus is also used to support individual super element feed arrays for each reflector. The super elements incrementally scan the beam by group selection of feed elements in each feed array with time delay phase control being used to steer the array factor so as to achieve fine steering.

Abstract: 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.

Abstract: A terrestrially deployed flexible antenna is disclosed. The antenna includes a planar, flexible dielectric material having a first side and a second side. A flexible conductive ground plane is secured to the first side of the dielectric material. At least one flexible, planar conductive element is secured to the second side of the flexible dielectric material. The flexible dielectric material is bonded to form a collapsible enclosed volume with the ground plane forming an inner surface of the enclosed volume. A propellant is disposed within tie enclosed volume. The propellant releases a predetermined volume of gas when ignited. An igniter ignites the propellant to release the predetermined volume of gas, to thereby temporarily expand the enclosed volume to a predetermined shape such that the ground plane, the dielectric material, and the at least one conductive element cooperate to form a resonant antenna circuit.

Abstract: In an inflatable structure provided with an array antenna or the like, a membrane of a multi-layer inflatable structure is provided with an airtight layer for forming an airtight space inside and a rigidizing layer provided outside the airtight layer, and the rigidizing layer is composed of a triaxial woven fabrics of reinforcing fibers, to thereby achieve a light mass and a high level of precision, and enable adaptation to a demand for increased size.

Abstract: In one aspect, the present invention provides an apparatus 10 for imaging. At least one source 12 (or 12/14) of composite radiation illuminates a field of view 16. The radiation includes a set of multiple phase-independent partials that are independently controllable and exhibit distinct physical features. A quasi-optical element 21 is disposed between the field of view 16 and a multi-element receiver 18. The multi-element receiver 18 is disposed to receive image radiation 28 from the quasi-optical element 21. Particular ones of the receiver elements transform the image radiation 28 into a set of electrical signals that include information relating to features of the partials.

Abstract: Reconfigurable radiant energy reflectors (3) of very low areal densities are formed of a laminate of a thin layer of a shape memory alloy (17) and a thin film or membrane material (15). The outer surface of the membrane provides the energy reflecting surface (16) and a support member (11) is attached to the laminate for application in a system. In a preferred embodiment, the shape memory alloy (17) is compositionally graded (18, 19, 29, 21) and exhibits a two-way shape memory effect and a heater (5) serves as the actuator to the reflector.

Abstract: An inflatable antenna has a plurality of inflatable tori including a first toroidal member and a second toroidal member arranged one radially inward of the other. A front membrane having a reflective coating is attached to the plurality of tori to form a front reflective surface. A rear membrane is attached to the plurality of tori and provides a rear support surface. The inflatable reflector is lightweight and compact and can be easily inflated to a desired shape.

Abstract: The present invention relates to reflective antennas. With previous antennas, the beamwidth of a reflected signal decreases linearly as the frequency of a transmitted signal increases. This is because the beamwidth for a normal antenna is a function of several parameters, including the frequency of the signal and the diameter of the reflective antenna. A beamwidth that decreases with frequency is undesirable because a decreased beamwidth results in a smaller user area on the ground. The present invention provides an antenna that maintains a constant beamwidth by using a mesh whose spacing increases with the distance from a central point.

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: A deployable antenna reflector comprising a central dish and a plurality of deployable sheet-like panels arranged around the central dish. The reflector further comprises a central supporting body, whereon the central dish is fixedly mounted and whereto the deployable sheet-like panels are hinged. The rotation axes of the individual deployable sheet-like panels are tilted with respect to the center point of the central dish. In the stowed configuration of the reflector, the deployable sheet-like panels are at least partially deflected in order to minimize the envelope of the reflector and that the panels relax upon deployment.

Abstract: An inflatable antenna has a plurality of inflatable tori including a first toroidal member and a second toroidal member arranged one radially inward of the other. A front membrane having a reflective coating is attached to the plurality of tori to form a front reflective surface. A rear membrane is attached to the plurality of tori and provides a rear support surface. The inflatable reflector is lightweight and compact and can be easily inflated to a desired shape.

Abstract: A mounting (1) comprises a transparent spherical shell (2), which holds a reflective mirror (4) for collection and concentration of radiation flux. A second membrane (7) is affixed to maintain a pressure differential across the two approximate hemi-spheres separate by the mirror (4). A quantity of water (13) is contained within the shell (2) acting as ballast. The lower portion of the shell (2) rests on a toroid (9), which is affixed to a base (10). Both the toroid and the vessel created by the inside surface of the toroid (9) and base (10) is filled with water (11,12). The shell (2) is buoyantly supported within the vessel by the water (12,13) while being restrained within the boundaries of the toroid (9) and base (10) but free for rotational movement as required to track the sun.

Abstract: A space deployable antenna that includes an inflatable envelope, a cylindrical reflector formed on a wall of the envelope, a catenary support frame for maintaining the cylindrical shape of the cylindrical reflector, and a feed array support structure connected to the catenary support frame.

Abstract: 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.

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: 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.

Abstract: A polyhedral-shaped inflatable structure having substantially continuous inner and outer flexible surfaces is inflatable with air or gas so that a radar reflector, comprising a plurality of conterminous corner reflectors, is thereby positioned within the inflatable structure to reflect radar waves. The corner reflectors are preferably made of metallized reflective plastic film attached to a plurality of support filaments. Support members attached to the support filaments are pivotally disposed adjacent to the inner flexible surface to position the radar reflector within the inflatable structure. Removable fasteners are disposed adjacent to the outer flexible surface and concentrically proximate to the support members to thereby fasten the radar reflector to the inflatable structure without puncturing the inner and outer flexible surfaces.

Abstract: A reconfigurable antenna capable of dynamic reconfigurability of several antenna parameters. Specifically, the present invention is an antenna comprising a plurality of surface PIN devices arranged in a gridlike array. Each of the SPIN devices can be individually activated or deactivated. When a SPIN device is activated, the surface of the device is injected with carriers such that a plasma is produced within the intrinsic region of the device. The plasma can be sufficiently conductive to produce conductor or metal like characteristics at the surface of the device. Various ones of the SPIN devices can be activated to electronically paint a conductive pattern upon the substrate supporting the PIN devices. Through selective activation of the SPIN devices various surface antenna patterns can be produced upon the substrate including dipoles, cross dipoles, loop antennas, Yagi-Uda type antennas, log periodic antennas, and the like.

Abstract: The deployable antenna with the tensegrity support structure and mounting frame has improved specific mass, compact stowage volume and high deployment reliability. The reflector is mounted to the tensegrity support structure via the mounting frame which ensures proper deployment of the reflector in the desired antenna operating shape.

Abstract: A back frame 60 helps to minimize distortion of a dish assembly 100 by supporting the shape of the dish assembly and supporting the weight of a feed legs assembly 120. The back frame 60 includes a template assembly 61, a center frame 70, and a feed leg mount 90. The template assembly 61 includes dish-engaging leaves 62, 64, 66, and 68 which are double-hinged at an intersection point to provide support for the individual pieces of the dish assembly 100. The center frame 70 includes legs 72, 74, 76, and 78 that are connected in a substantially diamond-shaped configuration. The center frame 70 attaches to the dish-engaging leaves at the comers of the diamond-shaped portion. A cross-connect bar 80 provides an attachment point to the controller assembly. The center frame 70 also includes connection arms 82, 84, 86, and 88 that connect directly to the dish assembly 100.

Abstract: An expandible antenna device comprising an expandible shell defining an interior chamber, wherein the shell is radially expandible from a central axis within the chamber; an elongated support structure disposed along the central axis and at least partially within the chamber; and an antenna element coupled to the shell such that the antenna is dimensionally stable when the shell is in an expanded position is disclosed. Additionally, an antenna element comprised of conductive elements joined by fluid filled bulbs or tubes wherein the fluid is capable of ionization is also disclosed.

Abstract: In an inflatable structure provided with an array antenna or the like, a membrane of a multi-layer inflatable structure is provided with an airtight layer for forming an airtight space inside and a rigidizing layer provided outside the airtight layer, and the rigidizing layer is composed of a triaxial woven fabrics of reinforcing fibers, to thereby achieve a light mass and a high level of precision, and enable adaptation to a demand for increased size.

Abstract: An array antenna including: a frame having a two-dimensional array of a plurality of openings; an electromagnetically radiating tile disposed in each opening; and mounting means for holding at least one tile in a corresponding opening of the frame, each of the mounting means comprising at least two biasing members, each biasing member exerting a biasing force on the tile relative to the frame. Preferably, each biasing member is a leaf spring having first and second ends attached to the frame and a bowed section attached to the tile. Furthermore, it is preferred that each biasing member further have a way to vary the biasing force with temperature, such as fabricating the bow portion from a first and second material, each having a different coefficient of thermal expansion. Also provided is a spacecraft which utilizes the array antenna of the present invention.

Abstract: An antenna system and improved antenna support structure that is preferably used on a spacecraft. An exemplary antenna system comprises an antenna dish, an antenna positioning mechanism, and the present antenna support structure coupled between the antenna dish and antenna positioning mechanism. The antenna support structure comprises a composite ring attached to a rear surface of the antenna dish and a boom structure coupled to the composite ring and to the antenna positioning mechanism that comprises a plurality of tubular fingers that interconnect the composite ring and the antenna positioning mechanism. The boom structure may further comprise one or more lateral supports that interconnect the plurality of tubular fingers. The composite ring is preferably disposed in a plane containing the center of gravity of the antenna dish. The composite ring, tubular fingers, and lateral supports preferably comprise graphite fibers.

Abstract: A screw motion-driven tensegrity antenna support architecture is configured to stably deploy and adjustably control an energy-focusing surface, such as an RF wave-reflecting conductive mesh. A parallel platform structure is configured of an upper hexagonal platform and a lower hexagonal base, the perimeter geometry of each of which is defined by plural interconnected tensioned ties. Vertices of the hexagonal tie base and the hexagonal upper tie platform are interconnected by pairs of legs, each including a compression strut and a tension tie. The stability of the structure requires that the sum of the tie tension forces matches the sum of the compression forces in the struts. To control deployment from a stowed condition and the geometric parameters of the deployed RF reflecting surface, a screw motion-based drive system is coupled to the struts to define relative mutual rotation and pitch between the upper platform and lower base.

Abstract: A dual reflector antenna system includes a subreflector and a main reflector with optimized shapes defined from a desired field distribution pattern and a feed pattern. The reflector shapes capture maximum energy from the feed and allow sidelobes to closely track a predetermined sidelobe envelope for optimal overall antenna efficiency.

Abstract: The present invention provides a transformable linked structure, a deployable diagonal structure, a plane stowage-type deployable truss and a line stowage-type deployable truss with high rigidity and reliability constituted by the above-described transformable linked structure and the above-described deployable diagonal structure, and also provides a plane/line stowage truss structure extremely approximated to a spherical surface using the two types of deployable trusses. The present invention discloses a module linked structure for linking deployable trusses securely and a holding/releasing mechanism for realizing reliable holding and release. Further, the present invention provides a modular deployable antenna with high precision even if it is large-sized which is realized by spreading mesh on the plane/line stowage truss structure.

Abstract: For use upon a high-frequency communications antenna comprising a reflector and a feed waveguide, a tool is provided to facilitate adjustment of polarization alignment by rotating the feed waveguide within the antenna. The tool engages a feed hub coupled to the feed waveguide provides a readily accessible lever arm to facilitate rotating the feed hub. Use of the tool allows fine adjustment of polarization alignment and reduces the incidence of damage and impairments that occur when other feed system components are improperly used to apply torque.

Abstract: A reconfigurable adaptive wideband antenna includes a reconfigurable conductive substrate for dynamic reconfigurablility of the frequency, polarization, bandwidth, number of beams and their spatial directions, and the shape of the radiation pattern. The antenna is configured as a reflect array antenna having a single broadband feed. Reflective elements are electronically painted on the reconfigurable conductive surface using plasma injection of carriers in high-resistivity semiconductors.

Abstract: A system and method for increasing the power density distribution uniformity of a gyrotron radiation beam provides a mirror for reflecting the gyrotron beam onto an object to be irradiated, where the shape of the mirror surface is changed by a plurality of controllable and movable mirror support members in a chaotic or random manner during generation of the gyrotron beam on the mirror surface, and the shape of the mirror surface is changed at a predetermined frequency F according to a predefined algorithm.

Abstract: A collapsible conductive material includes a generally mesh-configured, collapsible surface, that defines the intended reflective geometry of an antenna. A distribution of tensionable cords and ties form radial truss elements with a plurality of inflatable radially extending ribs and posts of a support structure. The antenna is fully deployed once the support structure is inflated to at least a minimum pressure necessary to place the ties and cords in tension so that the reflective surface acquires a prescribed (e.g., parabolic) geometry, which is stably maintained by the radial truss elements.

Abstract: 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.

Abstract: A plurality of paraboloidal reflector cells are mounted side by side in a concave spherical array in the interior of a toroidal support structure. Groups of adjoining reflector cells are selected for activation to point the antenna in a given direction. The activated elements of the group operate to roughly steer a beam in the desired direction, by switching feeds. Inter-element time delay steering is then used to precisely steer the beam to the desired direction. The groups of reflector cells are selected to provide a required number of pointing angles within a small cone, determined by the center of the group. Each reflector cell, moreover, includes a planar array of feed elements located at or forward of the focal point of its respective reflector element. A predetermined number of feed elements in each feed array of a beam group are selected for operation at any one time and comprises feed elements pointing closest to the desired beam position.

Abstract: Apparatuses, methods and systems for mesh integration and tension control, mesh retention, and mesh management of mesh-type deployable reflectors. The mesh members are comprised of a plurality of wedge-shaped gore members, each of which are pre-tensioned initially utilizing double-sided tape in a temporary manner prior to final stitching. String-like chord catenary members are positioned in pockets formed on the outer end of the gore members. The mesh member is attached to a ribbed reflector frame structure through a plurality of nodal assembly mechanisms. The nodal assemblies have spring biasing members for tensioning radial and transverse chord members along the reflector surface. A plurality of string-like members positioned in washers on the mesh member are used to maintain a tension field in the mesh member when the reflector is in its collapsed and stowed condition.

Abstract: An inflatable antenna system combining a fixed aperture with an inflatable aperture that greatly increases the reflector size of the antenna system. The fixed portion provides a “risk buffer” in that a moderate gain capability is retained in the event of an inflation failure. In a parabolic dish embodiment, an inflatable annulus is stowed compactly under a fixed dish to fit a variety of spacecraft and launch vehicle envelopes. Moderate gas pressure deploys the inflatable portion, which forms a larger reflector surface. After inflation, the materials that form the inflated reflector surface can be made rigid. A fixed feed system for the smaller fixed dish assures operation of the smaller fixed dish throughout the mission. Moreover, the smaller fixed antenna can receive signals that can be used to derive pointing information used to point the larger inflated antenna in a particular direction thus providing a dual-use capability.

Abstract: A reconfigurable antenna capable of dynamic reconfigurability of several antenna parameters. Specifically, the present invention is an antenna comprising a plurality of surface PIN devices arranged in a gridlike array. Each of the SPIN devices can be individually activated or deactivated. When a SPIN device is activated, the surface of the device is injected with carriers such that a plasma is produced within the intrinsic region of the device. The plasma can be sufficiently conductive to produce conductor or metal like characteristics at the surface of the device. Various ones of the SPIN devices can be activated to electronically paint a conductive pattern upon the substrate supporting the PIN devices. Through selective activation of the SPIN devices various surface antenna patterns can be produced upon the substrate including dipoles, cross dipoles, loop antennas, Yagi-Uda type antennas, log periodic antennas, and the like.

Abstract: A deployable reflector for an electronically scanned reflector antenna is provided. The deployable reflector may be confined to a relatively small volume for transportation of the reflector to a deployment site. Upon deployment, the reflector of the present invention forms a relatively large reflector surface, having a precisely controlled surface geometry. The reflector generally includes a plurality of panel members interconnected to a plurality of ribs interconnected to an extendable boom. The antenna reflector of the present invention is particularly well suited for a space-based antenna, where a reflector that can be collapsed into a small volume for transport and deployed to form a large reflector surface having high gain is desirable.