Abstract: A mobile tracking antenna for microwave signals from a satellite or distant transmitter includes a micro- electromechanical system produced by semiconductor processing. Specifically several micro faceted reflector segments have their facets selectively controlled by a feedback control system and reflects the signal onto a four sector horn which then by error signals actuates electrostatic positioning means on the micro facets to center the signal on the optimum receiving portion of the horn. Each segment covers a portion of the 360.degree. receiving spectrum. The particular segment is selected by a maximum signal being received.

Abstract: An adaptive antenna array 104 is disclosed. The adaptive antenna array 104 includes a plurality of reflector elements 202 and an array control processor 208 that regulates several resolvers 209, 210, 211 to generate independent magnetic fields. The array control processor 208 also generates reflector element command and control information and transmits the command and control information with a transmitter 218 to the reflector elements 202. The reflector elements 202 include a detector 706 that detects the transmitted command and control information. The reflector elements 202 further include a signal reflector 308 that reflect incident RF energy, a magnetic transceiver 310, and a reflector element controller 314. The reflector element controller 314 is connected to the detector 706 and interprets the command and control information 402.

Abstract: A latch mechanism for a cellular phone includes a rotatable detent portion attached to the helix of the antenna. A fixed detent member permanently attached to the phone includes a passageway to allow the antenna and rotatable detent to pass therethrough. A biased teeth is mounted between a plurality of guide detents formed on the inner surface within the fixed detent member and the base of the phone. While the teeth ring is allowed to move axially, it is keyed to prevent rotation. Accordingly, the detents formed on the rotatable detent member cause the rotatable detent member to rotate as it passes between the guide detents and as it engages the teeth ring. The forced rotations cause the detents of the rotatable detent portion to become engaged and disengaged with a latching undercut portion formed on a bottom portion of the guide detents.

Abstract: A universal communication system enables dedicated and independent communications capability to NSTS payload elements and ground based communications networks. The system may either utilize existing communications satellites as an intermediate network to provide continuous communications with payload elements, regardless of orientation or configuration of the NSTS Orbiter, or may communicate directly with ground stations via down link capability. In addition, the universal communications system can provide supplemental and independent communications capacity to the NSTS Orbiter's primary communication system.

Abstract: A waveguide lens antenna system is shown which includes a collapsible support structure and a collapsible waveguide lens array. The collapsible waveguide lens array includes a plurality of integrally connected tubular waveguide cells that form an array which focuses transmitted signals onto a satellite signal processing device. The array is coupled to a support structure that is affixed to a mounting surface, such as a satellite, and that correctly positions the array when the array is operationally deployed.

Abstract: A deployable antenna system comprised of a pair of independently flexible membranes carrying elements of the antenna system, apparatus fixed to corresponding extremity locations of the membranes for stretching the membranes taught and flat, spacers rigidly fixed to corresponding facing locations on the membranes, the locations being selected such that a line passing through each of the spacers is orthogonal to the surface of the membranes when the membranes are stretched, and at another angle to the surface when the membranes are either relaxed or one membrane is shifted laterally to the other.

Abstract: A dish antenna framework is constructed from tetrahedral strut assemblies. Each assembly is made up of six struts joined at their ends to four nodes. The nodes also constitute dish mounting points for the dish on the dish antenna framework. These points are located on the envelope of the dish. The framework supported on base frame is rotated about the vertical axis using a movable hydraulic ram arrangement wherein a ram cylinder is attached by an arm to the base frame to be rotated, a ram piston is removably attached to anchor members fixed to a platform. Rotation is effected by expanding and contracting the hydraulic ram. The ram is guided between anchor members by guiding means.

Abstract: A reflector assembly for use in antennas or solar collectors in which light weight and high reflector surface shape accuracy are essential for maintaining desired RF or light reflection requirements. The assembly is provided with a rigid, deployable outer support rim and at least one curved frame net supported by the outer rim. The frame net may be formed of a network of intersecting bands extending across the surface. A reflective material is placed against the frame net. A load is applied to the frame net to form a concave surface. The assembly is collapsible for convenient delivery into space prior to deployment.

Abstract: A flexible feed line is provided for use with a selectively deployable antenna system. The feed line is resilient and expandable so that it can maintain connections within antenna feed circuits while the antenna is being deformed or moved for stowage. An antenna system for use with the feed lines of the present invention may consist of a deployable quadrifilar helical antenna elements having four resilient conductive strips bonded thereto. Flexible feed lines are attached to each of the conductive helical strips. The feed lines expand to accommodate the shape of the antenna elements when compressed for stowing and return to their operating shape when deployed, thus providing identical feed paths to each of the antenna conductors when the antenna system is deployed.

Abstract: Antenna assemblies and stowage and restraint system thereof, comprising at least one dual band reflector having overall L-band-reflective properties and having a central stiffened Ku-band-reflective area having high reflector surface accuracy surrounded by a flexible annular area having L-band reflective properties. The reflector also has a support hingedly attached to a spacecraft body for deployment between a stowage position in which it is pivoted and restrained up against a face of the spacecraft body and the flexible annular reflector areas partially flexed therearound, and a deployed position in which it is enabled to relax and return to extended, parabolic condition.

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 method for stowing a unitary flexible antenna reflector 10 in a confining envelope and deploying the reflector from the envelope. In a most general sense, the invention includes the steps of: a) applying a deforming force to diametrically opposed positions 16 and 18 near an edge of the reflector 10 to place the reflector in a deformed state; b) maintaining the reflector 10 in the deformed state until deployment; and c) releasing the reflector 10 from the deformed state. In a specific embodiment, the step of maintaining the reflector 10 in a deformed state includes the step of attaching a restraining element between the diametrically opposed positions on the edge of the reflector which is released on deployment.

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 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: 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: 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.

Abstract: A large, deployable reflector (10) having several long, tapered petals (20) hinged at the tapered end to a top ring. The top ring (22) is attached to a central disk (26) positioned below the top ring (22) such that it is contained within the petals (20) when they are in the closed position. The center disk (26) is attached to the top ring (22) by several screw jacks (28) such that the center disk (26) moves up to a position proximate the 10 top ring (22) as the petals (20) are moved outward from the closed position to the open position. In the deployed position, the reflector surface forms a substantially solid, parabolic surface. Telescoping struts (40) are attached to the underside of selected ones of the petals (20) to enable steering of the reflector (10). The struts (40) are positioned such that the central axis of the paraboloid formed by the deployed reflector (10) remains clear.

Abstract: A redeployable, furlable rib reflector which is furlable and unfurlable between a first stowed position and a second deployed position. The reflector includes a hub assembly having spaced apart top and bottom plate members adapted to receive an antenna feed assembly mounted thereon and a plurality of attachable modular rib assemblies spaced about a periphery thereof. Each modular rib assembly includes a rib member for supporting a metalized mesh reflector surface attached thereto, a channel section base member, and a hinge assembly for pivotally connecting the rib members to their respective channel section base members. The channel section base members, in turn, are attachable between the top and bottom plate members of the hub assembly and also form a portion of the peripheral wall of the hub assembly.

Abstract: A marker beacon deployable by being launched through overhead foliage is able of landing atop and settling on the foliage for visual and infrared detection. A tether limits the flight range of the beacon and operates a switch to the electronic portion of the device to initiate radio signalling. The radio information assists in initial detection of the beacon by a seeking craft. Received signals from the seeking craft activate a flare stored within the beacon unit to further assist in locating the beacon. The beacon is also deployable by launch at sea, and by both place-and-leave and hand-held means on land and sea.

Abstract: An in-service reconfigurable antenna reflector having a rigid support structure, a deformable reflective surface having radio reflection properties and actuators operating on the deformable reflective surface to deform it. The reflective surface is elastically deformable with stiffness in bending and the actuators operate at control points of the deformable reflective surface, transversely thereto.

Abstract: An array antenna mounted on a spacecraft in its stowed state. After the spacecraft is launched in a predetermined position or on a predetermined orbit, the array antenna is extended to a flat plate form or a curved surface form. The array antenna has a structure that a plurality of subarrays are connected by plate springs or the like. The array antenna is extended in a kite form by using cables for connecting a spacecraft body and the subarrays or is extended by using an extension pole mounted on the spacecraft body. Each subarray includes a variable phase shifter to switch a shape and a direction of a directivity beam. A feeder line, a power supply line, a control signal line and the like connect the spacecraft body and each subarray.

Abstract: A metallized mesh fabric construction for use as the individual reflector panels of a radio frequency (RF) deployable parabolic reflector of the type which includes a plurality of panel supporting rib members which, upon deployment, unfurl in a spiral manner from a central hub to form the parabolic reflector surface. The mesh fabric includes silver coated nylon strands and stretch resistant plastic or synthetic strands interwoven in a "Marquisette" or "Leno" style weave. The stretch resistant strands of the mesh fabric are oriented along the chordal direction (i.e., transverse to the radial direction of the unfurlable ribs) in order to withstand the tension placed on the mesh fabric during deployment of the reflector and hence maintain the shape and accuracy of the reflector surface and resist creep. The weave has openings sized sufficiently large to minimize the effects of wind load yet sufficiently small to provide good reflective performance of radio frequencies up to and including X-Band frequencies.

Abstract: An antenna apparatus includes a power converting section which receives microwave energy and converts it to DC power. An actuator for folding/unfolding a mirror-supporting member and an actuator for adjusting the configuration of an antenna reflection mirror are driven and controlled by the DC power supplied from the power converting section.

Abstract: Disclosed is a method and apparatus for electrostatically shaping a membrane suitable for use in antennas or the like, comprising an electrically conductive thin membrane where the periphery of said membrane is free to move in at least one direction, a first charge on the electrically conductive thin membrane to electrostatically stiffen the membrane, a second charge which shapes the electrostatically stiffened thin membrane and a restraint for limiting the movement of at least one point of the thin membrane relative to the second charge. Also disclosed is a method and apparatus for adaptively controlling the shape of the thin membrane by sensing the shape of the membrane and selectively controlling the first and second charge to achieve a desired performance characteristic of the membrane.

Abstract: A reflector (3) may be mounted in a hollow housing (2) adapted to fly in ambient air. The reflector device (3) may be formed from a coating on the surfaces of blocks, the coating being metal or dielectric. Reflecting surfaces whether self supporting or not may be formed as intersecting circles or polygonal (more than four sides). They may be suspended in housing (2) adapted to fly either directly or indirectly by means of an intermediate body within the housing.

Abstract: A compact, reliable, paraboloid shaped assembly 7 is used as a reflector 7 on a satellite. The apparatus 7 is assembled from multiple panels 2, 3, 4, which connect to a central base 1 using hinges 20, 21. The apparatus 7 is compacted by rotating some or all of the panels 2, 3, 4 to be adjacent to one side 12 of the central base in stages, such that alternate panels 3 are rotated first. Folded onto these panels 3 are the remaining backwards-folding panels 2. The panels 4 which are not rotated backwards are then rotated forwards, completing a highly compact design. For deployment, the panels 2, 3, 4 are rotated in the reverse order and direction in which they were compacted. Latches 10 connect adjacent panels 2, 3, 4 and hold the panels 2, 3, 4 in the deployed position.

Abstract: A collapsible, dish shaped assembly, for example, for use with a satellite. The dish shaped surface is assembled from two sets of rigid panels. The first set of panels is rotated into position on hinges, which attach the panels to a base. The second set of panels is then rotated into position, also on hinges at the base, such that the second set of panels fill in the spaces between the panels of the first set. A latch connects each pair of adjoining panels. The latch comprises a protrusion which slides into a corresponding cavity. The resulting latch is resistant to lateral force. The latching process is facilitated by magnetic forces, which also add to the final latching force. The latches can be disengaged by jacking screws.

Abstract: A stowable and self-deployable array antenna includes flat, rectangular antenna panels hinged side-by-side so that when deployed they are coplanar, and they fold like an accordion for stowing. The deployed array antenna is stiffened by lateral stiffening panels hingedly attached to every other hinge between antenna panels, and to the unhinged ends of the antenna panels. Foldable longitudinal stiffening panels hinged between adjacent lateral stiffening panels. Each hinged connection includes a pair of thin spring elements, corresponding to a portion of a cylinder. The two spring elements of each hinge are spaced apart with their concave sides facing, and with the axes of the defining cylinder parallel. The hinge pivots, when the spring elements buckle, about a line orthogonal to a line extending between the cylinder axes. The hinges are used as the structural elements of self-deployable masts. The mast may have a polygonal cross-section.

Abstract: A collapsible truss structure having a shape of a rectangular parallelepiped when expanded is an open truss framework made up of skeletal members pin jointed together by joint connectors to form sixteen rectangular bays, four of which have diagonal braces, and supports panels for covering one face of the structure. The joint connectors permit the structure to be folded by power means in two directions into a compact slab for storage and/or transportation with the panels assembled therewith, while elastically biasing means automatically unfold the structure into its expanded state. Planar, single-curvature, and double-curvature panels can be thus supported. This structure can be optionally assembled with other structures to form larger structural assemblies.

Abstract: A large antenna array is constructed in sub-arrays which are supported in a stacked and folded (stowed) condition, and then deployed by first unfolding and then expanding the stack. The sub-arrays are compressed together to yield a very compact stowed configuration, due to the absence of a continuous ground planes. The compressed sub-arrays are contained within a foldable cage like frame.

Abstract: An adjustable focal length reflector for operation in space includes a membrane having a reflective surface. The membrane is subjected to incident radiation pressure. An assembly is located at the perimeter of the membrane to exert force on the membrane to counteract the incident radiation pressure in order to vary the focal length of the reflective surface. In a preferred embodiment the assembly includes an inflatable torus whose internal pressure is varied to vary the amount of force exerted on the membrane.

Abstract: A foldable reflector which includes a plurality of rib assemblies mounted around a base. The axes around which the ribs assemblies pivot lie in substantially the same plane. Each rib assembly has a rib portion and an offset member. The rib portions, which deploy flexible reflective material, lie substantially forward of the plane in both open and closed positions. The offset member have attachment points which extend to the forward side of the plane when the rib assemblies are in the closed position, and to the back side when they are in the open position. Elastic means extending between the attachment points of adjacent offset members bi-stably hold the rib assemblies in both the open and closed positions. A lock plate with radially extending portions locks the rib assemblies in the open positions when the lock plate is rotated to a position wherein the radially extending portions obstruct the pivoting of the ribs.

Abstract: A paraboloidal antenna system is disclosed which is segmented. Each segment is attached to a back up structure at three points, and is capable of linear normal motion at these points. The segments can be individually adjusted so as to conform to the true paraboloidal surface after the backup structure has been deformed. The adjustable attach points include digitally-controlled actuators. A laser reference system is used to detect deviations from the true paraboloidal contour. The laser beam is split to set up two sources along the paraboloid axis, and the ensuing hyperboloidal fringe pattern is of circular symmetry. Sensors determine the number of fringes lost or gained as the backup structure deforms. This data is used to guide the actuators to correct for the deviations.

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

Abstract: A single axis tracking system for a satellite moving in an inclined orbit. A linear antenna mount is used which is equipped for longitudinal tilt adjustment to enable an antenna to accurately track the longitudinal centerline of the figure 8 path of a satellite in an inclined orbit from any geographic location within the footprint of the satellite. The trajectory of the satellite is determined relative to the geographic location of the antenna mount. A time referenced tracking control signal moves the antenna mount. The signal from the satellite is periodically sampled and compared with stored values to verify the calculated trajectory. If a significant deviation occurs over a predetermined period, a new trajectory is automatically calculated and the time referenced trajectory signal is adjusted accordingly.

Abstract: A radiometer system is disclosed, the system incorporating a cylindrical parabolic reflector and a plurality of radiation sensors disposed along the focal line of the reflector in a minimum redundancy array. Digital processing circuitry is connected to the output of the sensors for digitally processing signals using a cross-correlation signal processing and fast Fourier transform circuitry to generate image signals, the system providing reduced weight and increased signal integration time. Several embodiments of the system are disclosed including analog and digital versions having a multiplicity of antenna configurations.

Abstract: The antenna system is provided with at least one active radiation source (1) and a reflective surface (2), which is located in at least one part of the radiation (3) generated by the active radiation source (1). The reflective surface (2) is provided with a number of independently adjustable plates (2.j) for generating at least one radiation beam. The antenna system may be provided with means (4) to independently adjust the plates (2.j) for the purpose of (dynamically) orientating the antenna beam.

Abstract: A portable antenna satellite system which has a dish made of substantially identical segments which fold around a central hub and a handle and horn stem that fold along with a tripod into a compact bundle for transporting and which can be easily and readily opened, stacked to the ground and "aimed" at a satellite.

Abstract: The figure of an unfurled antenna comprising a radio-frequency reflective fabric (10) is mapped and controlled by a system comprising a plurality of light-emitting devices (14, 15) mounted at precisely specified locations on ribs (11), which support the fabric (10). Light from each of the light-emitting devices (14, 15) passes through a corresponding window assembly (16) on a hub (12), which support the ribs (11) and also houses a telescope of the Schmidt-Cassegrain type. A biconical reflector (27) mounted within the hub (12) directs rays of light from all the light-emitting devices (14, 15) to a primary mirror (21) of the telescope, from which the rays are reflected to a secondary mirror (22), which focuses the rays so as to form images on photodetector arrays (31) and (32). The images formed on the photodetector arrays (31) and (32) are swaths of light, which cross the photodetector arrays (31) and (32) at positions determined by the actual positions of the light-emitting devices (14, 15).

Abstract: An unfurlable antenna reflector comprises a rigid central truss (12) on which are pivotally mounted circumferentially spaced booms (18). A network of tensioning cables (24) interconnect the ends of the booms to define a reflector-supporting net when the booms are in their fully deployed position. The booms deploy sequentially, to minimize shock loading, and have lengthening means (22) which simultaneously extend the outer ends of the booms after all the booms have reached their deployed position. A flexible mesh-like reflector surface (20) is connected to the net and is formed into a predetermined non-planar shape by net-shaping secondary cables (30).

Abstract: A stowable reflector assembly includes a flexible reflector shell that is rolled into an essentially cylindrical shape and retained by remotely controlled clamps. An underlying folding structure is deployed by remote signal and forms an underlying structure upon which the flexible reflector unrolls. Magnetic strips and auxiliary retaining mechanisms align and retain the reflector on the underlying support and urge it to a position from which it can accurately reflect electromagnetic radiation.

Abstract: A foldable and deployable antenna reflector includes a central panel having along its circular periphery a circular-sawtooth shaped contour with ramplike edges separated by radial cut backs and a plurality of similar, rigid segments, each having a foot edge are respectively hinged by means of a single hinge axis to the ramplike sawtooth edges.

Abstract: An expandable structure is formed by assembling together a plurality of structure modules each comprising a polygonal prism-shaped frame. Each pair of adjacent structure modules are connected together using frame members in common to form a hoop-shaped frame structure as a whole. Thus, it is possible to form a large-sized expandable structure, for example, an expandable antenna having an enlarged aperture. Since frame members of each pair of adjacent structure modules are used in common, it is possible to obtain a compact expandable structure.

Abstract: Antenna reflector mounting system for rapidly supporting reflector segments in precise alignment. A multi-faceted hub member is provided, each face of the hub member defining a rectangular opening of a cavity. A rod is located at the base of each cavity, supported between two walls thereof. A tongue member connected to the narrow end of an antenna segment is inserted in the cavity. The tongue member has a portion extending out from the connected antenna segment and downwardly at an angle. Once the tongue member is inserted over the rod, the distant end of the segment may be rotated vertically. Rotation of the tongue member about the rod pulls the connected antenna segment into alignment with the hub member.

Abstract: A radio-frequency reflective surface is made of a fabric woven from a yarn having an effective coefficient of thermal expansion of substantially zero over a useful temperature range. The yarn comprises a metallic filament around which non-metallic rovings are wound. The coefficients of thermal expansion of the filament and the roving material are related to each other so that mechanical strain thermally induced in the filament by changes in temperature is counteracted by mechanical strain thermally induced in the rovings. Intermodulation products at yarn intersections of the fabric are substantially zero.

Abstract: An offset collapsible/deployable dish having solid, relatively rigid folding panels which are unfoldable to a dish configuration conforming to an offset surface of revolution, such as an offset paraboloid generated about an axis offset from the dish, and foldable to a collapsed configuration contained within an envelope substantially smaller than the rim diameter of the dish. A radiation device utilizing the offset dish as a microwave, optical, or high energy beam reflector.

Abstract: In a microwave antenna of light weight and small bulk consisting of a reflector and a mirror, the reflector is constructed of vertical combs, horizontal combs and oblique combs. The vertical combs have a pseudo-random distribution with respect to a central comb. The reflector structure has both a shaping function and a supporting function.

Abstract: A space deployable solar energy concentrator is formed of a dome-shaped arrangement of compactly stowable flat panel segments mounted on a collapsible, space-deployable support structure of interconnected linear components. The support structure is comprised of a plurality of tensioned, curvilinear edge strips which extend in a radial direction from a prescribed vertex of a surrounding umbrella-like framework of radially extending rib members. Between a respective pair of radially-extending, curvilinear edge strips an individual wedge-shaped panel section is formed of a plurality of multi-segment lens panel strips each of which is supported in tension between the pair of edge strips by a pair of circumferentially extending catenary cord members connected to a pair of ribs of the surrounding umbrella-like framework. A respective lens panel strip is comprised of a plurality of flat, generally rectangular-shaped, energy-directing panels arranged side-by-side in the circumferential direction of the dome.

Abstract: Rear and forward reflector shells or dishes (36,38) are independently supported on a dynamically rigid truss structure (12) by means of separate studs extending from the forward nodes of the truss to the two shells. Forward node (22) carries adjustable rear shell stud (52) and independently carries adjustable forward shell stud (80). Both of the studs have flat portions oriented normal to the radius of the shell so that radial shell expansion due to temperature and temperature differential minimize shell distortion.

Abstract: A method of sectioning an antennae reflector without distorting the shape of the reflector surface. The reflector is supported in a substantially relaxed state so that only its internal residual stresses determine its shape. A plurality of beam pairs are attached to the outer surface of the reflector and are used to mark the corresponding curves along which the reflector is to be sectioned. When the cut lines have been marked so as to be visible on the inner surface of the reflector, the reflector is then cut along the cut lines marked on the inner surface thereof to section the antennae for transport and storage.