Abstract: A deployable microwave phasing structure having a plurality of sub-panels forming a non-planar reflective surface when in a deployed state. In one embodiment, the phasing structure includes a plurality of joints configured to inter-connect the plurality of sub-panels. In one embodiment, the deployable microwave phasing structure includes a folding means for arranging the phasing structure into a plurality of states, the plurality of states including the deployed state and a collapsed state, wherein the collapsed state is characterized by a substantially planar profile.

Abstract: Various embodiments of a securing ring are described along with assemblies utilizing the securing ring. A securing ring includes a curvilinear body defining an opening and having a gap that defines confronting ring ends that are separable to receive at least one curvilinear device within the opening. The curvilinear body includes an outer surface and opposing first and second side walls that define a slot therebetween. The slot is configured for receiving the curvilinear device, and the outer surface, the first wall and the second wall provide a clamping force on the curvilinear device in the slot when the confronting ring ends are drawn together, with the clamping force securing the curvilinear device within the slot. The securing apparatus further includes a locking mechanism coupled to the confronting ring ends and configured to releasably engage the confronting ring ends to secure the confronting ring ends together.

Abstract: There is provided an antenna reflector including at least first and second reflector segments, each having first and second sides. The first and second reflector segments being configured to be connected together wherein the first sides of the first and second reflector segments define a substantially continuous surface of an antenna reflector. A first latch member is attached to the second side of the first reflector segment and a second latch member is attached to the second side of the second reflector segment. Each latch member includes an abutting surface which contacts one another when the first and second reflector segments are connected together. At least one protrusion extends from the abutting surface of the first latch member. There is at least one recess in the abutting surface of the second latch member. The protrusion is received in the recess when the respective abutting surfaces contact one another.

Abstract: An antenna for a compact satellite terminal. Antenna is a rigid parabolic structure of metal matrix composite capable of disassembly into segments affording a high degree of portability such as for man-packable satellite terminals and the like. A shallow feed horn assembly is joined to an orthomode transducer by a common hub, the hub also serving as the attachment point for a plurality of antenna segments, where a quick release means joins the segments to the hub. The feed horn, hub, orthomode transducer and antenna segments are designed for extremely compact stowability in a variety of applications.

Abstract: An apparatus for positioning and controlling a spherical, inflatable antenna includes a driven rotating table disposed in the horizontal plane which supports and drives a horizontal arm member to which is hingedly connected first and second upright support members at either end. The upright support members include journal bearings attachable to the surface of an inflatable antenna.

Abstract: A mobile satellite communication trailer comprising a frame, an antenna assembly coupled to the frame comprising a feed boom, a reflector dish coupled to the feed boom, and at least one bumper coupled to the feed boom intermediate the feed boom and the reflector dish. A shock isolator is positioned intermediate the frame and the feed boom. The mobile satellite system further comprises at least three adjustable stabilizing legs providing rigid support for said antenna assembly when said antenna assembly is in a transmission position, said stabilizing legs being convertible between said transmission position and said transport position, wherein one of said at least three adjustable stabilizing legs is moveably connected to said trailer front portion and at least two of said at least three adjustable stabilizing legs are moveably connected to at least one of said satellite antenna assembly and said trailer frame proximate said satellite antenna assembly.

Abstract: A satellite antenna arrangement for a satellite communication system comprising: a reflector for producing a far field pattern with near-zero field strength at a predetermined location to reject unwanted signals from said predetermined location or minimise signal power transmitted to said predetermined location, the reflector having a surface comprising a stepped profile arranged to generate the near-zero field strength in the predetermined location. The stepped profile may comprise a radial step. The location of the near-zero field strength can be steered by moving the reflector or by adjusting the amplitude and phase of an additional beam that covers substantially the same region as the main beam reflected by the reflector.

Abstract: A deployable reflector (RP), for a space observation instrument is disclosed. The deployable reflector has a chosen number of deployable reflecting elements (E1a-E3b) suitable, once deployed in a first position, for together defining a reflecting area in the form of a so-called Reuleaux triangle (RD) with closed convex curve whose width is constant as a function of direction.

Abstract: A method and apparatus for making a mesh reflector that may be used to produce a shaped reflector is provided. The mesh reflector may be an umbrella-style deployable mesh reflector capable of approximating both parabolic and arbitrarily shaped reflecting surfaces, including those with regions of reversed curvature. The reflecting surface may be provided by a soft mesh attached to a highly pre-tensioned net composed of two sets of substantially parallel chords forming a plurality of parallelogram-shaped facets. The net/mesh may be made to conform to the desired shape by pulling and/or pushing on it at each of its facet corners via a set of finely adjustable tension ties and/or compression rods, the distal ends of which react against a set of pre-tensioned catenary-shaped chords disposed on the aft side of the mesh.

Abstract: A phasing structure includes a support matrix for a reflective surface which reflects microwaves within an operation frequency band. The reflective surface includes a plurality of adjustable sub-panels. In one embodiment, the phasing structure may include a phasing arrangement of electromagnetically-loading structures supported by the support matrix. The sub-panels may be secured to the support matrix and individually adjustable using a securing means which, in one embodiment, includes one or more differential bolts.

Abstract: An elevation mechanism for a satellite antenna system. The elevation mechanism includes tilt links or arms, lift links, and a linear actuator with an adjustable length leg arrangement. Each tilt arm is pivotally mounted at its inner and outer end portions to the base or azimuth plate of the system and to the back of the dish of the system. Similarly, each lift link is pivotally mounted at its inner and outer end portions to the base and to the back of the dish. The linear actuator in turn is pivotally mounted at its inner end portion to the base and at its outer end portion to the lift links. In operation, the linear actuator can be moved between extended and retracted positions to cause the dish to move between its stowed position facing downwardly and a deployed position facing upwardly of the horizon at a targeted satellite.

Abstract: A deployable thin-film mirror telescope comprises a base structure and a metering structure. The base structure houses a thin-film mirror, which can be rolled for stowage and unrolled for deployment. The metering structure is coupled to the base structure and can be folded for stowage and unfolded for deployment. In the deployed state, the unrolled thin-film mirror forms a primary minor for the telescope and the unfolded metering structure positions a secondary minor for the telescope.

Abstract: A shape-memory reflector is provided according to various embodiments. The shape-memory reflector may comprise any of various shapes; for example, the shape-memory reflector may comprise an off-axis paraboloid or a non-asymmetric shape. The shape-memory reflector may include a plurality of panel shape-memory stiffeners and a plurality of longitudinal stiffeners. In a stowed configuration, the shape-memory reflector is stowed with reversing bends in the panel shape-memory stiffeners. In a deployed state, the panel shape-memory stiffeners may be unfolded and/or extended. The reflector transitions between the stowed and deployed states by heating the panel shape-memory stiffeners. Various methods for stowing and deploying the shape-memory reflector are also disclosed.

Abstract: An apparatus for positioning and controlling a spherical, inflatable antenna includes a driven rotating table disposed in the horizontal plane which supports and drives a horizontal arm member to which is hingedly connected first and second upright support members at either end. The upright support members include journal bearings attachable to the surface of an inflatable antenna.

Abstract: A deployable microwave phasing structure having a plurality of planar sub-panels, each of the planar sub-panels having a reflective surface configured to reflect microwaves. In one embodiment, the phasing structure includes a plurality of joints configured to inter-connect the plurality of planar sub-panels to provide a first reflective surface geometry. In one embodiment, the deployable microwave phasing structure includes a plurality of joints configured to inter-connect the plurality of planar sub-panels to provide a first reflective surface geometry. According to another aspect of the invention, the phasing structure includes a phasing arrangement configured to provide an electromagnetic response of a second reflective surface geometry.

Abstract: A phased array antenna for a telecommunications satellite, that is deployable from a retracted condition to a deployed condition when the satellite is on-station, comprising a base member of hexagonal form, and a plurality of deployable antenna panels stacked one on top of the other on the base member in the retracted condition, each antenna panel being connected to a respective side edge region of the base by means of a respective back flap hinge, and the hinges having pivot points that are offset relative to one another, such that the antenna panels can be hinged sequentially one after the other from the stick to a position in which each panel is adjacent a respective base side edge region to provide an extended flat two-dimensional area when deployed.

Abstract: A shape-memory reflector is disclosed along with methods for manufacturing, packaging and deploying the same. The shape-memory reflector may include an elastic reflector material, a shape-memory stiffener, and a plurality of radial stiffeners. The shape-memory stiffener may be coupled with the elastic reflector material in a band that encloses at least a portion of the elastic reflector surface, for example, the exterior of a paraboloid reflector. The plurality of radial stiffeners is coupled with the bottom surface of the elastic reflector material and extends radially from a central portion of the elastic reflector surface toward the outer edge of the elastic reflector surface. The shape-memory reflector may be packaged in a packaged configuration that includes a plurality of pleats within the elastic reflector material and/or the shape-memory stiffener, and the shape-memory reflector is configured to deploy into a deployed configuration (i.e. a paraboloid) by heating the shape-memory stiffener.

Abstract: The invention proposes a solution to the problem of installing an antenna with long focal length on a satellite, and, as a non-limiting example, on satellites at a height that is less than the required focal length. It is based, on the one hand, on a reflector stored “inverted and head down”, and, on the other hand, on a deployment movement sequence employing a long arm taken up in the top portion of the reflector via an articulation (1 axis) and a conventional deployment mechanism (1 or 2 axes).

Abstract: In one aspect, a space vehicle includes a structure configured to expand from a first configuration to a second configuration and at least two equipment compartments attached to the periphery of the structure. The structure includes at least one of an antenna mesh, a light-shielding mesh, an optical reflector mesh and a net. In another aspect, a space vehicle includes an antenna structure configured to expand from a first configuration to a second configuration and at least two equipment compartments attached to the periphery of the antenna structure. At least one of the at least two equipment components include a solar panel, a propulsion system and an antenna feed. In a further aspect, a space vehicle includes a payload element and at least two spacecraft-support structures attached to the periphery of the payload element. At least one of the at least two spacecraft-support structures includes a propulsion system and a tracking, telemetry and control system.

Abstract: A self-deployable, monolithic, open-lattice frame structure of resilient, tape-spring members. The structure is comprised of three or more longitudinal prismatic tape-spring members (longerons) and non-prismatic tape-spring members (battens) that are connected transversely to the longerons. The longerons can be reconfigured in a z-folding manner to compact the structure. The batten members have a twist at each end of the same magnitude and sense, such that when connected to the longerons, the concave surfaces of the battens substantially face along the longitudinal direction of the frame structure. This batten shape permits them to nest within adjacent battens when the structure is compacted.

Abstract: A multi-function, field-deployable resource harnessing apparatus having, in its embodiments, an inflatable reflector apparatus comprising at least one manufactured parabolic mirror made from a pressure-deformable reflective covering of an inflatable ring for focusing electromagnetic energy from radio frequency radiation (RF) through the ultraviolet (UV) radiation including solar energy. A first main embodiment of the inflatable reflector apparatus generally utilizes two pressure-deformable membranes, at least one of which is reflective. A second main embodiment utilizes a reflective membrane and a transparent membrane. In addition to the reflector apparatus, the modular apparatus typically further includes modular assemblies to increase versatility facilitate use, and/or enhance safety such as, for example, a modular support and orienting assembly, a separate support ring, a safety shield or cage, a focal point support assembly, a safety cover, a safety net or mesh, and a stabilizing assembly.

Abstract: A method and apparatus for making a mesh reflector that may be used to produce a shaped reflector is provided. The mesh reflector may be an umbrella-style deployable mesh reflector capable of approximating both parabolic and arbitrarily shaped reflecting surfaces, including those with regions of reversed curvature. The reflecting surface may be provided by a soft mesh attached to a highly pre-tensioned net composed of two sets of substantially parallel chords forming a plurality of parallelogram-shaped facets. The net/mesh may be made to conform to the desired shape by pulling and/or pushing on it at each of its facet corners via a set of finely adjustable tension ties and/or compression rods, the distal ends of which react against a set of pre-tensioned catenary-shaped chords disposed on the aft side of the mesh.

Abstract: A support structure (1) is provided comprising a plurality of curved surfaces A, B hingedly interconnected along their edges such as to provide effective deployment in two separate stages. Preferably, the structure has only two curved surfaces hingedly interconnected at a single non-planar hinge line. In FIG. 1(a), the two sheets A, B are coplanar in that they lie in the same horizontal plane, permitting the structure to be in a flat, first stage deployment position. In Figure (b), the structure is fully deployed in a second stage deployment position by bringing sheet A out of plane through some angle in relation to the position of sheet B, resulting in both sheets becoming curved. The structure has utility in various space-based as well as terrestrial reflective and absorbing applications, and bears definite advantage in terms of weight saving, high stiffness and well-defined surface precision.

Abstract: A method and apparatus are provided for controlling grating side lobes in a faceted mesh reflector. Facets may be formed of a like shape but with a majority of the facets across the reflector having varying size which reduces the grating lobe intensity in the far field pattern.

Abstract: An inflatable antenna may include a support structure comprised of a flexible material, the support structure having an inner wall and an outer wall, the inner wall and the outer wall defining an inflation region; a flexible antenna element contained within the support structure; a feed line and a phase line connected to the flexible antenna element; an inflatable bladder contained within the inflation region; and an inflation apparatus coupled to the support structure and in fluid communication with the inflatable bladder. In some embodiments, the inflatable bladder may be readily inserted and removed from the support structure through an opening within the support structure. The inflatable antenna may operate in the UHF satellite communications band. The feed line and phase line may be perpendicularly oriented with respect to the flexible antenna element. In some embodiments, the support structure may not include an inner wall.

Abstract: A dish assembly is disclosed which has a central hub, an outer rim member, and a plurality of concentric arcuate structural members comprising at least an inner and an outer arcuate structural members extending from the central hub to the outer rim member, each of the arcuate structural members having an upper channel member, a lower channel member, an inner arcuate surface and an outer arcuate surface which cooperate to constitute a box section configuration and wherein said each upper and lower channel member comprises a channel base and a pair of channel flanges, and the inner and outer arcuate surfaces of each of the arcuate structural members are abutted such that a gravitational or wind load is transferred from the outer arcuate structural member to the adjoining inner arcuate structural member via a fin disposed on the inner arcuate surface of each of the arcuate structural members.

Abstract: Isostatic deployable support structure for antenna reflectors for vehicles characterized in that it is constituted by six supports hinged to each of their ends in three points on the structure of the vehicle and in three points on the structure of the reflector, in which: —two out of the three points of hinging on the structure of the reflector are positioned in points that are diametrically symmetrical with respect to the plane of symmetry of the antenna optics, and the third one is positioned on the plane of symmetry of the antenna optics, at the end of the reflector that is closer to the illumination system of the reflector; —two out the three points of hinging on the structure of the vehicle are positioned in points that are symmetrical with respect to the plane of symmetry of the antenna optics, as distant as possible, in the area between the reflector and the illumination system, and the third one is positioned on the plane of symmetry of the antenna optics, above the side of the illumination system tha

Abstract: A deployable microwave phasing structure having a plurality of sub-panels forming a non-planar reflective surface when in a deployed state. In one embodiment, the phasing structure includes a plurality of joints configured to inter-connect the plurality of sub-panels. In one embodiment, the deployable microwave phasing structure includes a folding means for arranging the phasing structure into a plurality of states, the plurality of states including the deployed state and a collapsed state, wherein the collapsed state is characterized by a substantially planar profile.

Abstract: A deployable microwave phasing structure having a plurality of planar sub-panels, each of the planar sub-panels having a reflective surface configured to reflect microwaves. In one embodiment, the phasing structure includes a plurality of joints configured to inter-connect the plurality of planar sub-panels to provide a first reflective surface geometry. In one embodiment, the deployable microwave phasing structure includes a plurality of joints configured to inter-connect the plurality of planar sub-panels to provide a first reflective surface geometry. According to another aspect of the invention, the phasing structure includes a phasing arrangement configured to provide an electromagnetic response of a second reflective surface geometry.

Abstract: A stowable antenna system for a security system is providing which includes an electronic radiating element in the form of a furlable flexible sheet, a power supply to power the electronic radiating element and a housing to receive and store the radiating element in a furled condition. The radiating element may be extended to an unfurled condition for use in the security system. One or more risers may extend from the housing for supporting the radiating element in the unfurled condition. The electronic radiating element may be received in the housing and stored in the housing in a rolled up, windowshade configuration.

Abstract: An antenna reflector provided with a plurality of segments, each of the segments provided with a plurality of end faces positioned along surfaces of the segments. The end faces of adjacent segments arranged in lateral and radial pairs, the lateral and radial pairs coupled together. At least one of the end faces of the radial pairs and of the lateral pairs extending proud of the respective surfaces, whereby when the radial pairs and the lateral pairs are connected, the adjacent segments contact one another only via the radial and lateral pairs.

Abstract: Parabolic reflector includes a number of sectors (2) being connected to each other at a central hub (3), the parabolic reflector being collapsible from an extended position (9), in which the sectors together extend 360 °around the hub (3), to a retracted position (8), in which the sectors (2) are brought together into a compact unit. Each sector (2) is rigid and is firmly joined to a cylindrical hub sleeve (4). The hub sleeves (4) together form the hub (3), around which the sectors (2) are journalled for limited movement around a central axis extending through the center of the hub (3). The hub sleeves (4) are concentrically arranged one radially inside the other with consecutively decreasing radii, and the hub sleeves (4) have mutually cooperating guiding surfaces that permit axial displacement of the hub so as to enable relative rotation there between.

Abstract: Isostatic deployable support structure for antenna reflectors for vehicles characterized in that it is constituted by six supports hinged to each of their ends in three points on the structure of the vehicle and in three points on the structure of the reflector, in which: —two out of the three points of hinging on the structure of the reflector are positioned in points that are diametrically symmetrical with respect to the plane of symmetry of the antenna optics, and the third one is positioned on the plane of symmetry of the antenna optics, at the end of the reflector that is closer to the illumination system of the reflector; —two out the three points of hinging on the structure of the vehicle are positioned in points that are symmetrical with respect to the plane of symmetry of the antenna optics, as distant as possible, in the area between the reflector and the illumination system, and the third one is positioned on the plane of symmetry of the antenna optics, above the side of the illumination system tha

Abstract: A broad-band millimeter wave imaging system with improved thermal resolution as compared to prior art devices. The system is useful for producing images of metal and non-metal objects such as guns, knives and explosives hidden under clothing. A cylindrical antenna focuses millimeter wave radiation from a substantially one dimensional section of a target region onto a linear array of radiation collectors. Radiation collected at each collector is amplified to produce a set of amplified millimeter wave signals and the amplified signals pass through focusing delay lines to a millimeter wave lens. Millimeter wave signals are collected at the output of the lens and the collected signals are monitored by an array of detectors. The combined effects of the delay lines and the lens produce a focus of the amplified millimeter wave radiation emitted and reflected from the one dimensional section of the target region.

Abstract: A phased array antenna for a telecommunications satellite, that is deployable from a retracted condition to a deployed condition when the satellite is on-station, comprising a base member (12) of hexagonal form, and a plurality of deployable antenna panels (14) stacked one on top of the other on the base member (12) in the retracted condition, each antenna panel (14.1-14.6) being connected to a respective side edge region of the base by means of a respective back flap hinge (16.1-16.6), and the hinges having pivot points (18) that are offset relative to one another, such that the antenna panels (14) can be hinged sequentially one after the other from the stick to a position in which each panel is adjacent a respective base side edge region to provide an extended flat two-dimensional area when deployed.

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

Abstract: An antenna system is provided including a rapidly expandable-collapsible housing which mounts two sections of fabric material each having an array of antenna elements formed of electrically conductive material such as copper thread embedded in the fabric sections. The fabric sections are movable between the expanded and collapsed positions with the housing and are located in different planes.

Abstract: A phased array balloon antenna having an inner membrane coupled to an outer membrane and a phased array antenna connected to an inner membrane. The phased array antenna transmits an energy towards a reflective film on the outer membrane, reflecting the energy outwards and illuminating an area smaller than that illuminated by the phased array alone.

Abstract: A deployable reflector of the invention includes connection members that bridge plural extendable structures constituting a deployable truss structure and connect portions corresponding to nodes of a buckling mode occurring in the extendable structures when a surface cable system is given tension, with portions corresponding to antinodes thereof. The surface cable system includes an internal surface cable system and a circumferential surface cable system connected to the outer circumference thereof. A cable used for the internal surface cable system is high in stiffness and small in ratio of length variation to tension variation. A cable used for the circumferential surface cable system is lower in stiffness and smaller in ratio of the tension variation to the length variation than that used for the internal surface cable system. Given tension by the deployable truss structure via the circumferential surface cable system, the internal surface cable system forms predetermined surface shape.

Abstract: A lightweight structure for space application is deployable from a compact bundle of interconnected struts into a plurality of tiled substantially rectangular bays. Each bay preferably comprises four or six hinged strut members having substantially rectangular cross sections, such that a solar or other suitable blanket may be compactly nested within the bundled struts. In one aspect of the invention, the blanket is attached to two opposed strut members of a six-member strut bundle, such that the blanket is unfolded during deployment of the strut bundle into a substantially rectangular bay. In another aspect of the invention, the blanket is attached to, and held against, a single strut in a strut bundle. After the strut bundle is deployed into a substantially rectangular bay, the blanket is spread across the bay via a cable mechanism or other deployment mechanism.

Abstract: A millimeter wave imaging system that includes at least one millimeter wave frequency scanning antenna for collecting frequency dependent beams of millimeter wave radiation from a narrow one-dimensional field of view. The collected radiation is amplified at the collected frequencies and the amplified signals are separated into frequency dependent bins with a tapped-delay beam-former. These bins are then sampled to produce a one-dimensional image of the antenna field of view. A two dimensional image of a target may be obtained by moving the target across the field of view of the scanning antenna. In a preferred embodiment the antenna is only 4.5 inches in length and constructed from WR-10 waveguide with inclined slots cut in one of the narrow walls at 79 mil spacings. This geometry creates a frequency-scanned antenna spanning a 20 degree vertical field of view over a 75.5–93.5 GHz operational band of the sensor, starting at approximately 1 degree below horizontal at 93.

Abstract: An apparatus and method for use in deploying a wireless communication device is provided that includes an antenna element and a reflector secured proximate a first end of the element. The reflector includes a base, and a flexible wall with a first end positioned proximate the base extending away to a second end positioned about the element. The wall can be deformed from an original position to a deformed position where the second end is temporarily positioned proximate the element and released such that the wall returns to the original position. The method includes deforming the reflector from an original position to an altered position where portions of a rim are proximate the element. The reflector is positioned in contact with the communication device, secured in the altered position, maintained in the altered position with a reduced profile, and released such the reflector elastically returns to the original position.

Abstract: A deployable electromagnetic concentrator comprises a facet stem hub assembly having at least one rotatable segment and a plurality of facets stems coupled thereto. At least one of the facet stems is coupled to at least one of the rotatable segments. The concentrator further comprises a plurality of facet stems, each being coupled to a different one of the rotatable segments for rotating the plurality of facets from a substantially overlapping configuration to a substantially non-overlapping configuration.

Abstract: A large aperture lightweight antenna uses an inflatable spherical surface deployed within a lighter than air platform. Beam steering is accomplished by moving the RF feedpoint(s) with respect to the reflector. The antenna can use an inflatable collapsible transreflector.

Abstract: A deployable antenna and method for using wherein the deployable antenna comprises a collapsible membrane having at least one radiating element for transmitting electromagnetic waves, receiving electromagnetic waves, or both.

Abstract: An embodiment of the invention generally relates to an apparatus for deploying a segmented reflector antenna. The apparatus includes a plurality of segments that can be rigid or flexible where each segment is hinged to an adjacent segment on either longitudinal side. The apparatus also includes a base, a plurality of inner deployment beams, and a plurality of outer deployment beams. Each inner deployment beam connects an inner side of a respective segment to the base and having a folded position and an extended position. Each outer deployment beam connects an outside side of a respective segment to the base and has a folded position and an extended position. The plurality of segments in a hinged folded position in response to the plurality of inner deployment beams being in the folded position and the outer deployment beams being in the folded position.

Abstract: A dish antenna kit has at least one reflector, one feed horn, and an alignment tool. The alignment tool has a light source and a base. The base has at least one inner cylindrical surface having a diameter slightly exceeding the outer diameter of a rim of the feed horn. The alignment tool base positions the light source axis with respect to the feed horn axis. A method of aligning the feed horn with respect to the reflector includes: placing the alignment tool on the feed horn; activating the light source; rotating the alignment tool so that a light beam advances in an arcuate path on the surface of the reflector; determining from the arcuate path the offset of the feed horn with respect to a focus point on the reflector surface; and, if the offset is not within the predetermined tolerance, adjusting the feed horn attitude.

Abstract: An antenna reflector and an associated latch system are provided. The antenna reflector includes a plurality of reflector portions that are connected in a predetermined configuration to define a continuous surface, such as a parabolic surface. The latches connect the reflector portions. Each latch includes first and second latch members, which define reference surfaces that are structured to contact when the latch is closed. In particular, the reference surfaces are disposed at predetermined and dissimilar distances from connection features of the respective latch members. For example, the first and second reference surfaces of the respective latch members can be disposed at first and second distances from apertures through the respective latch members. The first distance can be greater than the second distance so that, when a fastener is disposed through both apertures, the reference surfaces are urged together and the reflector portions are connected in a predetermined configuration.

Abstract: The elevation angle and azimuth angle and the required angles of rotation for the first antenna 33 and the second antenna 34 are calculated using predetermined calculating means. The elevation adjustment mechanism and azimuth adjustment mechanism and rotating mechanisms of the first antenna 33 and the second antenna 34 are controlled so that the first antenna 33 and the second antenna 34 will be pointed toward respective communication targets T1 and T2 (the first satellite and the second satellite).

Abstract: A framework for a deployable antenna is disclosed herein. The framework basically includes a plurality of elongate ribs, a matching plurality of foldable resilient members, and a hub. Each of the elongate ribs has both a proximal end and a distal end. The foldable resilient members serve to interconnect the proximal ends of the elongate ribs to the hub. Within such a configuration, each of the foldable resilient members is capable of storing strain energy whenever forcibly folded and also releasing the strain energy whenever subsequently permitted to elastically unfold. Thus, whenever the elongate ribs are released from a stowed position in which the foldable resilient members are forcibly folded, the strain energy causes automatic deployment of the antenna as the foldable resilient members are permitted to elastically unfold. In sum, therefore, the framework obviates many conventional uses of electro-mechanical motors or actuators in deploying various antennas.