Abstract: A hybrid reflector antenna particularly suited for reflecting a frequency band in a satellite includes a central portion fully reflective to the frequency band. A first annular band is disposed directly adjacent to the central portion. The first annular band is partially reflective to the frequency band. The reflector may include several annular bands having various degrees of reflectivity and thus attenuation. The present invention may be implemented using two such reflectors, one for transmitting and one for receiving in a satellite, for either single or multiple beam applications. This invention offers more compact and lower mass/cost antenna configurations compared to conventional antennas from multiple beam satellite payloads.

Abstract: A parabolic antenna comprising at least a reflector of deformable material, the reflector having a parabolic shape of a preferred curvature, and a rigid structural substrate comprising a foam sufficient to maintain the parabolic shape of the reflector against significant deviation from said parabolic shape. The deformable material of the reflector is characterized by its inability to maintain the parabolic shape of a preferred curvature in the absence of the rigid structural substrate. A method of forming the inventive antenna is disclosed, comprising the steps of: Providing a backing section and a reflector made of deformable material, the backing section and reflector being mateable to define a hollow interior cavity; maintaining the reflector on a forming die in conformance with a preferred curvature of the reflector; and injecting an expandable, foam slurry into the hollow interior cavity and curing the foam slurry to form the antenna.

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: The present invention provides a system for avoiding code collisions from multiple SAW identification tags and a method of operating such system. In one embodiment the invention provides for (1) focusing an interrogation pulse to within a defined space; and (2) discriminating between coded responses returned from tags located within such defined space.

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 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: The present invention relates to an antenna (1), comprising a dielectric substrate (2) comprising a front (3) and a back (4) dielectric face, at least one dipole element comprising a first (5) and a second (6) element for radiating and receiving electromagnetic signals, said first element (5) being printed on said front face (3) and said second element (6) being printed on said back face (4), said first and said second element having a spiral shape, respectively, both spirals being open, and metal feeding elements for supplying signals to and from said dipole element, said metal feeding elements comprising a first line (7) printed on said front face (3) and to said first element (5) coupled at a first feeding point and a second line (8) printed on said back (4) face and coupled to said second element (6) at a second feeding point, said first and said second feeding point overlapping each other.

Abstract: An optically transparent dielectric reflector (200) that reflects an incident millimeter-wave beam at a design frequency. The reflector (200) includes layers of different optically transparent dielectric materials. The thickness of the individual layers is chosen so that the transmitted wavbes cancel almost completely in the forward direction, yielding a high degree of transmission loss and substantial reflection. In the preferred embodiment, the invention is comprised of alternating layers of optical sapphire and air. In the best mode, there are seven sapphire layers, with outer sapphire layers (50) having a nominal thickness of 70.8 mils, inner sapphire layers (52) with a nominal thickness of 30.4 mils, and air layers have a nominal thickness of 32.0 mils Vented metal spacers (54) are used to maintain optimal thickness of air layers.

Abstract: A transmitter-receiver antenna of a radar is prepared as a parabolic antenna, and a wave reflector is constituted by a reflector array having a plurality of reflectors, and multiple beam widths of a transmission wave in the vicinity of the radar and a reflected wave in the vicinity of the electric wave reflector are set to be greater than a beam width C that can be blocked by a non-detection subject, such as a bird, that is excluded from detection subjects. Thus, it becomes possible to improve the identifying precision between the detection subject and the non-detection subject, and consequently to provide an immersion object detection device with high reliability that can reduce erroneous detections.

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 wave-scanning antenna is disclosed that does not require a rotary joint. The antenna produces a collimated beam that can be scanned through 360 degrees. The beam is directed perpendicular to the antenna's axis of rotation to form a disc-like surveillance volume, or at an angle above or below the perpendicular to form a cone-shaped surveillance volume. The radar's structure contains a transmitter and receiver coupled to a horn protruding through open centers of the support bearing and driven gear into the antenna housing. Energy emitted by the horn proceeds upward until deflected through an angle of 90 degrees by an angled reflector located on the axis of rotation. The energy is collected by a dielectric lens and focused into a collimated beam. Reflected energy is collected by the lens and directed by the reflector to the horn, where it is fed to a waveguide coupled to the receiver.

Abstract: A flat metal plate (20) has a plurality of holes (50) that have a property that changes across the surface of the plate so that the flat plate (20) mimics the behavior of a curved wavefront transformer. The changing property can include a dimension, such as radius or depth, such that the holes (50) near the center of the plate (20) are smaller, for example, than the holes (50) further away from the center of the plate (20). The size of each hole (50) is a function of the local phase change imparted on an electromagnetic wave of a particular wavelength or frequency that hits the hole (50), plus the propagation phase change that occurs in the reflected wave exiting the hole (50) as it travels the distance between the hole (50) and the focal point.

Abstract: According to an aspect of the present invention, an antenna system comprises: an antenna panel (1) which has fine irregularities (4) on front and back surfaces thereof, the fine irregularities (4) being formed by blasting so as to regularly reflect service radio waves having longer wavelength than sunlight and scatter sunlight. Further, according to another aspect of the present invention, a method for manufacturing an antenna system in which an antenna panel (1) is manufactured by combining a plurality of constituent parts, comprises the steps of: finishing front and back surface portions of each of the constituent parts so as to thin down the thickness of constituent parts; blasting the front and back surface portions of the constituent parts with abrasive grains; combining the plurality of constituent parts subjected to the blasting step so as to form the antenna panel (1) into a desired shape; and attaching an assistant reflecting mirror (3) to the antenna panel (1) acting as a main reflecting mirror.

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: A concave reflector is shaped to receive energy emanating from a signal source positioned at the reflector's vertex and to reflect all received energy in a uniform output direction. The reflector additionally introduces a designated constant phase shift into all reflected energy relative to unreflected energy from the signal source, regardless of where the received energy impinges upon the reflector. When the source signal is periodic, this reflector design minimizes near field interference between the reflected signals, since they all have the same phase shift relative to the unreflected source signal. Furthermore, if the reflector is designed to implement zero phase shift, reflected and non-reflected signals tend to combine additively in the far field, focusing most of the transmitted energy toward the center of the transmission pattern.

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: 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: In this antenna in an element in an electrically conductive material, the element comprises a gauze coated at least in part by a coating of thermoplastic material.

Abstract: The invention provides a reflector forming a parabolic antenna, the reflector being characterized by the fact that it is made up of n contiguous layers of dielectric material defined by n+1 surfaces having distinct parabolic equations and shaped to define a common electromagnetic focus.

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: 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: The present invention provides a low-cost, frequency-tunable, steerable, reflector array capable of simulating the electromagnetic effects of a parabolic or similarly-shaped reflector on a planar or conformal surface. Simple scatterers such as short circuited dipoles, disposed on a geometrically planar or conformal substrate, are configured from a series of scatterer sub-elements, electrically connected serially to one another by MEMS switches. These connected scatterer sub-elements form a reflective array disposed above a ground plane on the substrate. By properly controlling the length and spacing of the activated dipole elements, it is possible to simulate the equiphase reflection profile of a horn feed or sub-reflector feed of a parabolic or similar reflector. In addition, the array may be steered by selectively controlling the scatterer configurations.

Abstract: An antenna suited for receiving/transmitting electromagnetic signals from/to at least two satellites, which are fixedly placed at points on the geostationary path, is waveguide or lens type, formed by a multitude of waveguiding channels, which for example can be rotationally symmetrically arranged about an axis. Signals from remote points, which arrive in directions somewhat deviating from the direction of the axis, e.g. in an angle &agr;in thereto, exit after being refracted in the antenna in a different direction, so that the angle &agr;ut on the exit side differs from the angle &agr;in on the entrance side. It is achieved by having all of the waveguiding channels form suitably adapted angles to the axis. For a concave antenna it can give an increased separation between the positions, to which signals from remote objects are refracted by the antenna. It results in, for example, large more efficient receiver horns being used for the same size of the antenna.

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: The present invention relates an antenna arrangement (23, 330, 430, 530, 630) comprising a fit layer (331, 431, 531, 631) consisting of a dielectric material and a second reflective layer (335, 435, 535, 640, The dielectric material has variable dielectric characteristics. An electromagnetic radiation (50) passing through said first layer (331, 431, 531, 631) and at least partly reflected by said second layer (335, 435, 535, 640) is modulated by varying said variable dielectric characteristics of said first layer.

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: Array fed multiple beam antenna systems and methods for use on an orbiting spacecraft carrying a communication system. The antenna systems include a reflector and a relatively small array feed compared to the reflector. The array feed has feeds (radiators) that illuminate the reflector and that are disposed in a focal plane of the reflector. A power division network excites the radiators of the feeds. The antenna system is capable of very wide scan angle operation and may be used to provide multiple spot beam coverage over the surface of the Earth viewed from a synchronous orbit spacecraft. Phase aberration normally associated with scanning is corrected by adjusting excitation coefficients of each array feed. The spot beams are scanned across a field of regard by controlling the position of each feed in the focal plane and using the appropriate amplitude and phase distribution associated with a particular spot beam (array feed). The amplitude and phase distributions may be fixed or varied during operation.

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: A parabolic reflector assembly (10) comprising a base member (11) formed of magnetic material and defining a parabolic surface (12), and a flexible magnet sheet (18) carrying a reflective sheet (19) magnetically bonded to the parabolic surface to form a parabolic reflecting surface. A method of manufacturing the parabolic reflector assembly is also disclosed. The parabolic reflector assembly typically may be used as a concentrator is solar energy concentrating apparatus.

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: The present invention relates to a rigid surface reflecting electromagnetic waves, especially for antenna reflectors, electromagnetic shielding, and waveguides. According to the invention, this surface consists of an interlacement (7) of electrically conducting wires (2, 3) which consist, on the surface, of a stable metal diffusion alloy ensuring that said wires are fastened together and that said surface is rigidified.

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: The present invention relates to a system for shielding an edge of a satellite antenna from a surface of a vehicle on which the satellite antenna is installed. The system includes a signal reflecting device including a satellite antenna having an edge portion. The edge portion includes a substantially straight edge segment and an edge guard structured to surround the edge segment.

Abstract: A perimeter truss structure (103) that may be used, for example, to support an RF reflector may include multiple deployed bays (200) arranged in a ring. Each deployed bay (200) includes a first upper horizontal support member (726) attached to a first vertical support member (706) and collapsible on a first joint (728) translating on a second vertical support member (708), as well as a first lower horizontal support member (714) attached to the second vertical support member (708) and collapsible on a second joint (744) translating on the first vertical support member (706). The first and second vertical support members (706, 708) define a ring inside (122) and a ring outside (124). The first upper horizontal support member (712) is disposed on one ring side (e.g., the outside), while the first lower horizontal support member (714) is disposed on the opposite ring side.

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 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.

Abstract: A reflective panel for deflecting electromagnetic waves comprised of a resistive material varying in resistivity across the panel; a center portion on the panel, having a predetermined resistivity; a periphery portion on the panel having a higher resistivity than the center portion; and wherein the center portion of the panel is adapted to reflect the electromagnetic waves and wherein the periphery portion is adapted to minimize diffractions.

Abstract: An antenna system suitable for use in communicating with satellites has multiple antenna units adjacent to each other and oriented in the same direction. These antenna units are driven together in tandem in altitude and azimuth by a common drive unit. The signals received by the antenna are combined together in an in phase relationship in a combiner unit to provide received signals which reinforce each other.

Abstract: An antenna suited for receiving/transmitting electromagnetic signals from/to at least two satellites, which are fixedly placed at points on the geostationary path, is waveguide or lens type, formed by a multitude of waveguiding channels, which for example can be rotationally symmetrically arranged about an axis. Signals from remote points, which arrive in directions somewhat deviating from the direction of the axis, e.g. in an angle &agr;in thereto, exit after being refracted in the antenna in a different direction, so that the angle &agr;ut on the exit side differs from the angle &agr;in on the entrance side. It is achieved by having all of the waveguiding channels form suitably adapted angles to the axis. For a concave antenna it can give an increased separation between the positions, to which signals from remote objects are refracted by the antenna. It results in, for example, large more efficient receiver horns being used for the same size of the antenna.

Abstract: An antenna apparatus such that a dielectric strip and a dielectric resonator are provided to form a primary vertical radiator, another dielectric strip is provided which is coupled to the dielectric strip to form a directional coupler, and a radiation beam is tilted by changing the relative position of the primary radiator with respect to the dielectric lens by displacing the primary vertical radiator in the directional coupler.

Abstract: A technique for manufacturing a domed housing, including a transreflector element for use in a microwave antenna. The dome incorporates a metallic polarizing grid as part of a complex curved shape using an insert mold process. As a result, the transreflector component can be inexpensively formed as an integral part of the supporting structure and any alignment features, without the need for additional molding steps or multiple component parts.

Abstract: A deployable antenna reflector structure (10) that provides a reduced number of components without compromising mechanical stability or deployment reliability. The structure (10) uses a truss hoop (21) with identical elements (20) and parallel pivot axes (30) to transition from a stowed position (50) to a deployed position (51). The use of identical elements (20) provides reduced manufacturing and assembly costs due to the reduction in components and added simplicity of the design. The truss hoop (21) achieves mechanical stability by making use of a two-dimensional element design having vertical portions (23) and horizontal portions (22) located in the same plane. Each parallel pivot axis (30) is defined by two pivot points. The first pivot point (31) connects horizontal portions (22) of adjacent identical elements (20) and the second pivot point (31) connects vertical portions (23) of adjacent identical elements (20). The structure (10) also provides a reflector (40) and a deployment control mechanism.

Abstract: An antenna reflector for satellites or space vehicles having a number of hexagonal individual reflectors (1) which can be arranged around a rigid central element (2). The reflectors (1) are connected to the central element (2) by a support structure (3) that can collapse to hold the reflectors in a compact storage state or be extended to deploy the reflectors. The reflectors (1) are folded like an umbrella in a transport state when the reflectors are collapsed and at the place of use, they are brought into their operating positions and spread out, so that they collectively form a reflector surface. Each reflector (1) has a foldable surface structure connected by a multiple number of ribs (11) to a rigid, central structure (12).

Abstract: A perimeter truss's mesh material (3) and radially extending support catenaries (7 & 9) extending from a central hub (8) are, by rotation of the hub, rolled up together like a bolt of cloth, essentially in synchronism with the folding of the perimeter truss (5), to thereby form a small sized body that fits within the barrel-like configuration formed by the folded perimeter truss.

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: Providing a tapered surface reflectivity to the reflecting surface of the parabolic reflector in a parabolic antenna using resistive material reduces side lobes and produces steeper roll off in the principal lobe, permitting use in the antenna of a smaller diameter microwave feed than required by an antenna without that tapered surface resistivity and, effectively, emulates the latter antenna. As a consequence of the smaller feed diameter, multiple feeds may be positioned contiguously to form multi-beam antennas that produce contiguous beam patterns. A satellite cellular communications multi-beam antenna incorporating the invention achieves greater regional coverage of the Earth.

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.