Abstract: A method for the production of a reflector for antennas to be used in outer space in which a thread (7) is wound on a winding spindle (1), to obtain a netting or network structure. The winding spindle (1) has contour segments (2) on its surface, whose contour corresponds to the contour of a sector of the reflector surface being produced. After winding, the resulting thread network structure is hardened on the winding spindle (1) and the thread network structure is divided into individual sections. The contour segments (2) are separated from the winding spindle (1) and together with the sections of the hardened network structure thereon are fitted together on an assembly rig so that the individual sections collectively form a reflector. The winding of the thread of the network structure on the spindle can vary in at least one direction or in its angle of placement a, so that the network structure has a different, selectable rigidity in individual areas.

Abstract: A satellite communications antenna includes a low-windload reflector so that the antenna may be used on high windload locations, such as on a ship. The reflector has a support structure which includes a grid-like structure having relatively large apertures therein to allow wind to pass therethrough. The reflector further includes reflective radiators, such as dipoles, mounted to the support structure for focusing at least one desired frequency of operation. The reflector is also formed in component parts for easy assembly/disassembly should it be necessary to deploy the system elsewhere.

Abstract: A dish antenna heating assembly includes a dish antenna having a convex rear surface. a heating element associated with at least a portion of the convex rear surface a fabric cover overlying at least that portion of the convex rear surface with which the heating element is associated, and spacer elements disposed between the convex rear surface of the dish antenna and the fabric cover.

Abstract: A reflector assembly in a satellite system includes a reflector having a reflecting surface and a back surface. The back surface is opposite the reflecting surface and has a plurality of ribs extending transversely therefrom. The reflector assembly further includes a layer of air-entrapped foam insulation having an inside surface. The inside surface has a plurality of grooves configured to receive the plurality of ribs therein. The reflector assembly further includes a heater assembly attached to the inside surface of the layer of air-entrapped foam insulation. The heater assembly includes a plurality of heater pads, a plurality of jumper wires electrically interconnecting the heater pads in series, and two end wires. Each end wire is connected to a respective end one of the heater pads. Each of the plurality of heater pads is disposed between a corresponding adjacent pair of the grooves.

Abstract: The reflective mesh material that forms the reflector in a foldable perimeter truss antenna is remotely adjusted to shape using remotely controlled stepper motors carried on the truss. Connected to the end of the catenaries, which shape and support the pliant reflective mesh material on the truss, the stepper motors adjust the tension on the catenaries and thereby change its shape. An RF receiver and electronic controller associated with each stepper motor receives the tension command information from a remote source and controls the stepper motor in accordance with that information.

Abstract: A deployable segmented dish-like reflector includes a main body with one or more additional reflector segments. Each reflector segment is connected to the main body with one or more link members, such that the entire reflector may be stowed into a compact volume and subsequently deployed to its operational configuration. The system provides a mechanism for stowing the at least one segment in an overlapping manner, substantially parallel to the main body, in order to minimize its stowage volume. The linkage arrangement allows the at least one reflector segment to be deployed from the stowed position to a desired final position. Rate control and deployment coordination may be introduced in a variety of ways.

Abstract: Paraboloidal grid reflectors and antennas are provided which are lighter and have less wind loading because they efficiently realize selected front-to-back ratios by recognizing the angular distribution in typical differential path losses and feed gains. In particular, the reflectors are formed with adjacent pairs of parallel elongate members that are positioned at respective angles &thgr; from the paraboloidal vertex and spaced apart by respective spaces S that generally increase with increased angle &thgr;. In some reflector embodiments, the spaces S increase with increased angle &thgr; for a contiguous majority of adjacent pairs and may be constant for a contiguous minority that typically adjoins the vertex. In other reflector embodiments, the spaces S increase with increased angle &thgr; for all of the adjacent pairs.

Abstract: A reflector for an antenna includes a plurality of reflector elements, each having a transmission line and an aperture at a distal end of the transmission line. Each transmission line having a length which varies in accordance with the position of each aperture relative to the antenna. The varying length of transmission creates a time delay that phases re-radiated waves.

Abstract: An antenna-oriented reflecting material using triaxial woven fabric is usable for frequency bands as high as 20-60 GHz. A reflecting material 1 usable for the high frequency bands is manufactured without spoiling advantages of triaxial woven fabric 2 by controlling mainly a construction n, a volume resistivity .rho. and a mass per unit length .eta. of the triaxial woven fabric. Particularly the setting of each parameter is determined by a composite model reflection ratio .GAMMA. obtained from a sum of a first reflection ratio .GAMMA.'s based on a surface resistance of the triaxial woven fabric and a second reflection ratio .GAMMA.p based on opening, holes of the triaxial woven fabric. It is preferable that a construction be 5-28 yards/in a mass per unit length .eta. be 10-460 tex g/1000 m, and a volume resistivity .rho. be 0.7 to 2.0.times.10.sup.-3 .OMEGA..multidot.cm.

Abstract: An unfurlable reflector antenna system having one or more unfurlable arms that are each shaped in the form of a parabolic right cylinder when it is unfurled. Each arm comprises an RF reflecting membrane or a thin shell as the reflector structure. Each arm is coupled by way of a line feed to a receiver. The system is specifically designed for use on a spacecraft. Each arm may be stowed by flattening the parabolic membrane or shell, and then rolling up the arm, which is accomplished without stretching. The sparse reflector antenna array system is thus stowable in a compact configuration, yet easily unfurls to provide a very large diameter lightweight reflector.

Abstract: A device for angular adjustment of a direction-indicating object of an antenna device such that the direction-indicating object performs a mechanical movement without rotating. The inside of a first end of a rigid tube is rotatably arranged via two bearing devices in relation to a fixed part of the antenna device around an axis of rotation, the fixed part is attached to a foundation. An antenna part of the antenna device includes the direction-indicating object. The antenna part is rotatably arranged via a bearing device on a bevelled outer edge of a second end of the tube around a central axis. The outer edge is bevelled to an intended fixed angle which determines the fixed angular adjustment of the antenna part with respect to the fixed part of the antenna device. A cardan coupling is arranged between the fixed part and the antenna part such that the cardan coupling prevents the antenna part from being able to rotate in relation to the fixed part.

Abstract: A non-mobile antenna for receiving non-geostationary satellite signals comprised of a plurality of supporting members and rods is adapted with an upper and a lower array of reflecting members focusing the signals on a focal axis for processing.

Abstract: An antenna system including a support structure and an antenna assembly having an open grid reflector structure in a closed ring and dipole elements. The antenna assembly includes a number of antenna panels, each including a number of the dipole elements, the closed ring is self-supporting and connected to the support structure by radial beams and struts, and the antenna panels are interconnected by a variable angle connection.

Abstract: An antenna reflector comprising a single membrane antenna reflector surface and means for supporting said antenna reflector surface are disclosed wherein a shape of said antenna reflector is reconfigured to assume a stowed position. The shape of the stowed reflector allowing a large, single piece antenna reflector to be stowed efficiently inside a minimum payload area of the space vehicle. The method and apparatus of this invention ensure that both the deployed and stowed surfaces of the membrane antenna reflector are isometric, or length preserving, mappings of one another. The circumferential dimension of the antenna reflector is decreased having the effect of rolling up the paraboloid so that its surface is similar to a cone. Additionally, the method and apparatus are employed such that when the antenna reflector surface is deployed the antenna reflector membrane unrolls without stretching.

Abstract: The invention relates to high stiffness parabolic structures utilizing integral reinforced grids. The parabolic structures implement the use of isogrid structures which incorporate unique and efficient orthotropic patterns for efficient stiffness and structural stability.

Abstract: Three reflector plates comprising: a lateral reflector plate having two half plates each opposingly placed across a rotation supporting shaft introduced therebetween, a longitudinal reflector plate having two half plates each opposingly placed across the rotation supporting shaft therebetween, and a bottom reflector plate placed at the central portion of the rotation supporting shaft, wherein these three reflector plates are brought into mutual orthogonal intersection at their diameters, and the rotation supporting shaft is provided with an inclination supporting hole with an inclination of a "detection design angle", thereby enabling to maintain the detection design angle when in use and enabling to easily assemble into the shape for use even in case of emergency, and further enabling the reflector plates to be stacked flat one upon another and stored free from bulkiness when not in use.

Abstract: Self-tuning materials which can efficiently emit or receive radio waves in spite of being simple in their construction and small in their dimension, and are applied to patch antenna, wave directors or the like. Metallic chips containing two or more kinds of ingredients which are distributed in a layered, net-like or needle-shaped configuration, and an organic or inorganic bonding material which is small in dissipation of electric power under radio waves of high frequencies are mixed with each other, and are pressurized under a high pressure while being highly electrified in the direction perpendicular to the pressurizing direction to mold the metallic chips and the bonding material in a plate-shaped configuration while being heated.

Abstract: A deployable perimeter truss reflector is capable of achieving a hitherto unobtainable thirty to one ratio in size between its size in the deployed condition and the stowed condition. The improved truss reflector structure is characterized by deployable spars that are attached to and extend from a basic frame structure to the truss. When deployed the spars are positioned outwardly and away from the basic frame of the truss, carrying the catenaries, and, the latter carrying the reflective surface into position at an end of the truss cylindrical truss. New catenary systems, deployment mechanisms, basic truss structures and cable management systems are also described.

Abstract: A single surface reflector antenna and method for making same comprises a plurality of hat-shaped cross section ribs formed on the back surface of a reflector shell with flexible tooling. All antenna shell and backing structure components are comprised of triaxial weave graphite laminate layers thereby allowing the backing structure to conform precisely to the shape of the antenna shell when cured and heat cycled.

Abstract: A micromachined reflector antenna system is integrated onto a substrate by firstly etching a reflector aperture surface defining a dish cavity in an oxide layer and secondly rotating a hinge over the reflector aperture surface with the hinge being used as the reflector central feed. The micromachined reflector antenna system can be made with an array of reflector antennas and integrated onto a single substrate with front end receiver circuits operating as a high frequency receiver on a chip with reduced size and cost and operating at hundreds of GHz.

Abstract: A transreflector is made by forming a series of spaced parallel stripes of a conductive material on one surface of a synthetic resin carrier film. The film is placed against the surface of a mold defining the desired concave internal curve for the transreflector, and the mold cavity is closed by placing over the film in spaced relationship a second mold half having the desired convex external curve for the transreflector. A fluid synthetic resin is introduced into the mold cavity to form the desired transreflector element with spaced parallel stripes disposed on the internal concave surface thereof. The carrier film is removed from the transreflector element with the conductive material stripes remaining on the transreflector element.

Abstract: A carbon fiber hybrid laminate includes a first group of carbon fiber reinforced laminae having a positive CTE and, second group of carbon fiber reinforced laminae having a negative CTE, wherein the hybrid laminate has a tailorable in-plane CTE in the range of .+-.0.2.times.10.sup.-6 in/in/.degree. F.

Abstract: A metallodielectric photonic crystal including a plurality of elements, each having a non-dielectric component, arranged with respect to each other in a three-dimensionally periodic lattice. The non-dielectric components being spatially isolated from one another, the lattice exhibiting a band gap in the spectrum of electromagnetic radiation modes propagating through said lattice. A support structure positions the elements in the three-dimensionally periodic lattice. In an exemplary embodiment, the elements are metallic spheres arranged within dielectric material. The three-dimensionally periodic lattice can include a face-centered-cubic lattice which exhibits a unidirectional photonic band gap, or a diamond lattice which exhibits an omnidirectional photonic band gap. The diamond lattice structure includes a gap width to midgap frequency ratio which can exceed 60%.

Abstract: An apparatus and method for setting the upstand height of the studs of an array of studs used to form antenna panels is disclosed. The apparatus includes a transducer beam having a row of spaced-apart distance transducers. The apparatus also includes an actuator beam having a row of spaced rotary actuators. The actuators rotate the threaded studs to raise or lower the studs until the corresponding transducer indicates that the stud has achieved an intended height. Also disclosed is a method using an array of laser diodes, rather than the transducer beam, arranged at one end of the base plate and an array of photo diodes at the opposite end. The output of the diodes indicates the height of the studs.

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 reflector assembly in a satellite system includes a reflector having a reflecting surface and a back surface. The back surface is opposite the reflecting surface and has a plurality of ribs extending transversely therefrom. The reflector assembly further includes a layer of air-entrapped foam insulation having an inside surface. The inside surface has a plurality of grooves configured to receive the plurality of ribs therein. The reflector assembly further includes a heater assembly attached to the inside surface of the layer of air-entrapped foam insulation. The heater assembly includes a plurality of heater pads, a plurality of jumper wires electrically interconnecting the heater pads in series, and two end wires. Each end wire is connected to a respective end one of the heater pads. Each of the plurality of heater pads is disposed between a corresponding adjacent pair of the grooves.

Abstract: An umbrella-like antenna reflector assembly for use on an orbiting spacecraft. The reflector has a main rib and a plurality of secondary ribs each connected to a hub assembly by a respective hinge mechanism such that activation of the hub assembly causes the reflector to move between collapsed and opened configurations. The reflector further has a mesh member attached to the ribs. A deployment boom connects the main rib of the reflector to the spacecraft. The deployment boom is operable with the main rib and the spacecraft to move the reflector between a collapsed and stowed configuration proximate the spacecraft and an open and deployed configuration outside the spacecraft. The storage profile is sufficiently slim to permit launching of a 6-25 meter diameter reflector attached to a full-sized spacecraft on one or more commercially available launch vehicles without the need for mid-rib hinges. A feed assembly is connected to the spacecraft.

Abstract: One aspect of the invention relates to a reflective mat useful to provide an electromagnetically reflective surface on a high-frequency radio antenna. In one version of the invention, the reflective mat includes a conductive mat shaped to conform to a signal receiving surface of an antenna core. The conductive mat has a core contacting surface, which is coated with an adhesive material for joining the conductive mat to the receiving surface, and a signal reflecting surface which is coated with a curable finishing material.

Abstract: A parabolic reflective antenna having a front concave surface and a rear convex surface. The reflective antenna including a heating assembly for preventing and removing ice and snow during cold weather. The heating assembly includes first and second woven supporting structures. A heating element is supported between the first and second supporting structures, the first and second woven supporting structures being interposed between the front and rear surfaces of the antenna. Heat generated from the heating element emanates to the front concave surface of the reflective antenna.

Abstract: A lateral reflector plate comprising two rotatable half plates mutually opposed through a rotation supporting shaft introduced therebetween, and a longitudinal plate comprising two half plates mutually opposed through the rotation supporting shaft introduced therebetween are vertical to each other, and a foldable bottom reflector plate comprising four quarter plates is intersected orthogonally with the lateral and longitudial reflector plates, and also the rotation supporting shaft is provided with an inclination supporting hole with an inclination of the detection design angle.

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 grid-type microwave antenna, easy to manufacture, assemble and disassemble, is formed of a number of spaced reflector rods which, when mounted in a frame, form a parabolic reflecting surface. The frame includes U-shaped channels for mounting and supporting the spaced reflector rods. Each of the rods has a curvature so that the combination of the rods spanning the frame forms a parabolic reflector. The frame is formed by channels having holes to receive the central and the end portions of the reflector rods. Insulating sleeves are provided for the central portion of each rod. Insulating cups are used for the end portions of each rod.

Abstract: In accordance with the teachings of the present invention, a telescoping deployable mesh antenna reflector for space communication applications and a method of deployment is provided. The antenna reflector includes a plurality of telescoping radially extending ribs between which a plurality of interconnected guylines are secured to form a wire truss structure. The telescoping radially extending ribs include pivotally coupled inner and outer ribs that are collapsed and folded to stow the antenna. A highly reflective wire woven mesh is connected to the front surface of the wire truss structure with flexible radially extending strip members allowing for folding and telescoping of the antenna reflector.

Abstract: The invention is directed to a reflector assembly in a satellite system including a reflector having a reflecting surface and a back surface. The back surface is opposite the reflecting surface and has a plurality of ribs extending transversely therefrom. The reflector further includes a heater assembly embedded therein. The reflector assembly further includes a layer of closed cell plastic foam insulation which covers the heater assembly within the reflector. An inside surface of the insulation is disposed adjacent to the back surface of the reflector and includes a plurality of grooves. The plurality of grooves are configured to receive the plurality of ribs therein. The layer of insulation also includes a coating of ultraviolet radiation protectant disposed over an outside surface of the insulation.

Abstract: The present invention is directed to a fabric capable of reflecting electromagnetic waves. The fabric contains metal-coated (preferably aluminum) glass fibers bonded together with sheath-core binder fibers. The glass fibers are typically less than 11/4 inches long and the binder fibers are originally approximately 2 inches long. The glass and binder fibers are thoroughly mixed and spread across a flat surface, such as a conveyor, prior to heating. After heating, the mixture is compressed to form the reflective fabric.

Abstract: A reflector is constituted by a right pseudo-dihedral, a ridge (C) of which is in the form of a portion of a helix so as to provide a calibrator or a beacon.

Abstract: A wave reflecting dish is constructed to provide a one piece unit having a hollow, watertight region between a first external surface having a paraboloidal contour and a second external surface which includes a base. Heater elements are positioned in the hollow region on a surface opposite the first external surface. Insulating material cover the heater elements and the hollow region is filled with a foam material. Snow, ice, and water drainage from the first surface is provided through a hole which extends through the unit from the first surface to the second surface. Provisions for mounting wave emitting and receiving apparatus are provided within the first surface. Attachment pads for mounting the dish on an external structure are provided on the base.

Abstract: A composite antenna and method for constructing same is disclosed. The composite antenna has a grid comprised of electrical conductors woven into the warp of a resin reinforced cloth forming one layer of the multi-layer laminate structure of the antenna.

Abstract: An antenna includes a parabolic reflector and a supply line attached thereto. The supply line includes two rectangular electromagnetic (waveguides) that are essentially parallel to each other. A tube-shaped exciter is common to the (waveguides) and is located at open ends of the waveguides. A back side of the reflector has a mechanically stable receptacle, which is used to attach the reflector to a support. The receptacle includes a metal ring with an L-shaped cross section in an opening that corresponds to a central opening in the reflector. The ring has a cylindrical area and, at a right angle to the cylindrical area, a base area that extends toward the inside of the ring. In the installed position, the cylindrical area of the ring penetrates and is centered in the opening of the reflector. A holding plate, which firmly surrounds and supports both waveguides, fits precisely into the ring and is attached to the ring in removable form when mounted.

Abstract: Space antenna reflectors comprising composite membranes having a fabric core comprising high modulus fibers, such as of graphite, woven along three or more axes and encapsulated within a cured plastic as a single ply composite material, such reflectors having quasi isotropic strength properties, i.e., the same strength, thermal stability and distortion-resistance in substantially all directions although they are based upon a single, lightweight ply of woven graphite fabric. The present reflectors may have a molded or honeycomb support, for attachment to a spacecraft or satellite.

Abstract: A portable antenna with a collapsible reflector dish made from a flexible mesh so that the reflector can be folded in upon itself from the deployed position. When closed, the antenna is contained within an outer casing. The outer casing has a top side that opens when the antenna is deployed. Depending upon the specific application, the top side of the outer casing may be flat or conical. The antenna can be deployed by remote element. The driving element extends the support frame for the reflector dish to its deployed position, and raises the boom into its operating position.

Abstract: A heated microwave antenna ideal for the direct broadcast satellite service, and heated conversion kits for retrofitting to conventional antennas. Antennas modified in accordance with the invention are highly weather resistant, as the dish is warmed to avoid snow and ice accumulation to prevent signal degradation. The heated microwave antenna mounts upon a mast that is bracketed to a satisfactory support. The dish focuses microwave signals upon a low noise broad band amplifier (LNB). The dish comprises multiple laminations from internal elements that are sandwiched together, and exhibits significant mechanical strength and substantial weather resistance. The preferred dish comprises a metallic reflector, a heated grid, an insulation layer, and a backing plate nested together to form a composite, laminated unit. The grid comprises a resistive heater element activated by a temperature-responsive thermostat. A concentric trim ring surrounding the dish periphery waterproofs the antenna.

Abstract: A "shutter" type structure for transmitting electromagnetic energy within a selected frequency range and preventing the transmission of such energy outside such range during a first open shutter mode of operation and for preventing the transmission of any electromagnetic energy during a second closed shutter mode of operation. The structure includes an insulative member having an array of symmetrical conductive elements on at least one surface, such elements being interconnected by diode elements in both vertical and horizontal directions. The diodes are placed in their conductive states during the first mode of operation and in their non-conductive states during the second mode of operation.

Abstract: The reflector consists of a ground plane, enclosed in a ground plane frame, and a phasing plane, enclosed in a phasing plane frame. Spacers maintain the planes in connected, spaced relationship. The phasing plane includes a plurality of reactive elements sensitive to different frequencies in the bandwidth of the reflector. Thus, an E-M wave directed at the reflector is reflected to the angle of the received wave.

Abstract: A shielding screen for use in an integrated antenna system that includes at least two antennas that emit interfering signals that interfere with each other and at least one antenna that emits a non-interfering signal that does not interfere with the interfering signals. The shielding screen incorporates a frequency selective surface configured and dimensioned to reflect the interfering signals and to transmit the non-interfering signals. The shielding screen is positioned between the antennas that emit interfering signals and has a surface disposed substantially orthogonal to a line extending therebetween. The screen is dimensioned to block the interfering signals emitted by each of the two antennas from impinging upon the other of the antennas.

Abstract: A foldable self-supporting vaulted shell for use in space, the shell comprising a thin flexible membrane and a plurality of thin battens forming ribs for tensioning said membrane. Each of the battens has a first main face and a second main face, one of the main faces facing the membrane. The membrane includes guide pocket for said battens. The guide pocket terminating at at least one end by abutment-forming end-reception means for receiving corresponding ends of the battens, and forming abutments such that in a deployed condition, the ends of the battens transmit axial force to the membrane. As a result tensioning of the membrane occurs. The shell occupies a small volume in its folded condition for storage in a launcher for the purpose of being placed into orbit. Such a shell is suitable for making microwave antennas. The invention also relates to a method of packaging such a shell.

Abstract: Films of thermoplastic poly(arylene ether imidazole)s (PAEI)s are used as surface modifiers for neat resin panels and composite resin panels. The PAEI polymer contains imidazole groups along the backbone which co-cure, i.e., react chemically, with epoxies or bismaleimides during processing and thereby provide excellent adhesion between the PAEI film and an epoxy or bismaleimide neat resin or composite resin facesheet. The film provides good adhesion and a smooth surface to the finished part and acts as a release agent from the mold. The as-processed integral structures have very smooth (specular) surfaces, and since the film releases readily from a glass mold, no release agent is necessary. The PAEI film is thermally stable, resistant to electron radiation, and adheres tenaciously to the facesheet. The film maintains good adhesion even after thermal cycling from room temperature to .about. -196.degree. C.

Abstract: A method for sewing a plurality of gore-shaped metalized mesh fabric panels to each other to form a parabolic dish-shaped reflector surface for subsequent attachment to the radially extendable rib members of a deployable parabolic reflector. The method includes using a template having "cut" and "sew" lines indicated thereon for cutting out a desired number of gore-shaped panels from a bolt of metalized mesh fabric and sewing the panels together along adjacent side edges thereof to form the dish-shaped reflector surface. The dish-shaped reflector surface is then attached to the reflector by sewing the mesh fabric panels to stitch holes provided in each rib member. The reflector surface is accurized by using a wedge-shaped tool which is placed on a slack reflector panel adjacent a gore seam.

Abstract: An open mesh material for use as a high performance RF reflective antenna surface and which is formed as a Leno type weave using electrically conductive composite yarns which have a construction for avoiding loose metal-to-metal contacts which generate undesirable passive intermodulation products (PIM). The composite yarns are formed by counter-wrapping stretch resistant nonconductive strands about an insulated metal strand and a stretch resistant nonconductive filler yarn. The insulated metal strand preferably includes a beryllium-copper wire which is encapsulated within a polyamide coating. The woven mesh is coated with a RF energy transparent silicone-based paint to provide additional insulation to the plastic coated wires at the weave junctions and has a surface resistivity sufficiently low to facilitate bleed off of building electro-static charges.

Abstract: A balloon with an internal corner reflector for radio waves is built with the reflecting plane of the reflector freely suspended from a cord frame system which is only secured in the points of suspension. The reflector is suspended inside a balloon which is composed of single flat pieces of a resilient material. Manufacture of the reflector balloon may substantially be done in one plane and the balloon primarily envelopes the reflector very tightly. The suspension utilizes the resiliency of the balloon corners. Balloons which are observed from below may have four internal corners with downwards facing openings and may also be designed to provide rotation.