Abstract: A space deployable antenna reflector surface is formed as a continuous laminate that is shaped to conform with a prescribed energy-focusing surface geometry. The laminate is formed of very thin layers of flexible material, such as very thin sheets of graphite epoxy, containing collapsible radial and perimeter stiffening regions or stiffeners. Due to its thinness, the reflector laminate is collapsible into a folded shape, that facilitates stowage in a restricted volume, such as aboard the space shuttle. The stiffening elements of the laminate antenna structure of the invention facilitate deploying and maintaining the reflector in its intended geometric shape, and collapsing the reflector laminate into a compact serpentine stowed configuration.

Abstract: A broadband collapsible impulse radiating antenna having a reflector 36 and feed arms 24 made from a flexible conductive material. An umbrella-like support mechanism is used to collapse and deploy reflector 36. The umbrella-like mechanism consists of a plurality of support ribs 52, a center support rod 22, center push rods 28, feed arm support rods 26, and push sleeve 32. Support ribs 52 are attached to the reflector 36 and are pivotally connected to a central hub 66. Push sleeve 32 slides along center support rod 22 causing the radial center push rods 28 to provide a radial force to reflector 36 and thereby deploy and collapse the antenna. Center can 12 contains center support rod 22 and an RF splitter 86 that splits the input signal into two feed cables of equal length leading to the feed point 54. Optional expandable seams can be provided in the reflector and feed arms so that the surface curvature of the reflector can be adjusted.

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

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

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

Abstract: A compactly stowable and deployable support architecture, such as may be used for supporting an energy directing surface, includes radial and hoop support members for deploying a surface, such as a mesh-configured antenna reflector. A multi-sided foldable hoop structure has a plurality of foldable joints, and generally radial struts that extend from and are foldable about corner joints of the hoop structure. At least one drive mechanism is coupled to torque tubes that drive geared hinges of the multi-sided hoop structure. The hinges and drive linkages are geared to synchronously unfold the multi-sided foldable hoop structure and the radial struts, so that the antenna surface may be smoothly deployed from its stowed condition.

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

Abstract: An architecture deploying an energy-directing mesh so as to conform with a prescribed surface includes a plurality of radially extending support structures. Cords extend between the support structures in a generally circumferential fashion, and have attachment locations for the energy-directing material offset from the support structures. Each of a plurality of outermost intercostal cords is retained in tension between the support structures and is configured to substantially conform to the perimeter of the prescribed surface. Flexible intercostal compression reactor members are arranged to be placed in tension in a generally arcuate shape between adjacent support structures. Flexible radial compression members are placed in compression between the intercostal compression reactor members and the outermost intercostal cords, so that the outermost cords substantially conform with the perimeter of the prescribed surface.

Abstract: A deployable phased-array-of-reflectors antenna includes individual reflectors and feed arrays. Each feed array is disposed above a corresponding individual reflector. The individual reflector antennas are preferably disposed adjacent to one another (e.g., on a hexagonal lattice) to form a phased array antenna using the individual reflectors antennas as elements. Phase and amplitude control electronics are coupled to each reflector antenna to provide steering for the signal energy coupled between the reflectors and the feed arrays. Switching electronics are coupled to the feed arrays and selectively activate and deactivate beam forming clusters of feeds in the feed arrays. A method for generating a steerable antenna pattern couples signal energy through a beamforming section to form steered signal energy. Next, the method couples the steered signal energy between a phased array of reflector antennas.

Abstract: A self-actuated structure, such as an antenna structure, is provided that can be stowed in a compact manner and can be deployed in a self-actuated fashion. The self-actuated structure includes a flexible skin, a boom extending thereacross and rings about which the flexible skin can be folded such that a payload volume is defined therewithin. The self-actuated structure also has a plurality of ribs extending parallel to the boom that cooperate with the flexible skin to define a number of channels extending between the boom and an edge of the flexible skin. The structure also includes a plurality of self-deploying stiffeners disposed within respective channels. In this regard, the stiffeners can have an unbiased relaxed shape, such as a “U” shape, in the absence of external forces and a biased shape, such as a flat shape, upon the application of external bias forces.

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

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

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

Abstract: A large, low cost and high quality optical telescope system (1) includes a segmented primary mirror (2) having a plurality of spherical mirror segments (3) arranged in a non-spherical shape (4), a parabolic shape in the disclosed embodiment, so that the rays incident upon the individual spherical mirror segments stay separated at an exit pupil (5) of the system, allowing for correction of aberrations. A discontinuous pupil corrector in the form of a segmented mirror (7) having a plurality of aspheric correction terms in it, is located at the exit pupil for correction of aberrations introduced from respective ones of the plurality of spherical mirror segments of the primary mirror. The discontinuous pupil corrector preferably is a segmented deformable mirror. The telescope system and related method can achieve diffraction limited performance for very large systems. The disclosed embodiment is a 35 meter aperture, deployable space telescope system.

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

Abstract: An antenna reflector for a spacecraft, produced in an elastically deformable way and capable of changing from a folded position to a deployed position at least partly under the action of its own elasticity. The reflector includes at least one fold line, the general direction of which is at least approximately parallel to the axis of the casing and about which said reflector is folded in its folded state.

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

Abstract: The low earth orbit radar remote sensing or telecommunication satellite includes an antenna forming member in a plane passing through the center of Earth, for example, the plane of its orbit. The antenna(s) are on one or both faces of the member. The height of the antenna forming member is greater than its dimension in the direction of travel of the satellite, so that the satellite is naturally stabilized by the gravity gradient. The solar generator cells are carried by the antenna forming member on the face that is kept facing towards the Sun in the case of a 6 H/18 H local time heliosynchronous orbit. The antenna forming member comprising a plurality of hinged panels over which the received or transmitted wave phase control means are distributed, it includes a plurality of GPS sensors distributed over the panels, enabling measurement and subsequent compensation by the phase-shifters of deformations of the member.

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: The present invention is directed to a method of and a device for adjusting the concavity of a springback antenna reflector. The method and device of the present invention can be used to adjust the concavity of the springback reflector prior to stowage within a satellite to correct actual or anticipated variations in the desired shape of reflector that are caused by storage of the reflector, fabrication of the reflector, thermal effects on the reflector, and moisture absorption by the material from which the reflector is fabricated. By adjusting the concavity of the reflector to correct the variations in the shape of the reflector, degradation of the performance of the reflector due to distortions in the shape of the reflector may be greatly reduced.

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

Abstract: An antenna reflector for a spacecraft includes a radial slot which facilitates stowage of the reflector in the spacecraft. When the reflector is in a folded position, opposing edges of the radial slot overlap in such a way that the reflector assumes an at least approximately conical shape, thereby allowing the reflector to be housed in a casing so as to be oriented vertically in line with the spacecraft.

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: A shape memory alloy hinge assembly for deploying at least a first object in a controllable, substantially shockless manner is disclosed. Generally, the hinge assembly includes at least a first flexure member capable of moving from a first, folded configuration to a second, straightened configuration, and a controller for controlling the movement of at least the first flexure member as the first flexure member moves or reconfigures from the folded configuration to the straightened configuration.

Abstract: An antenna reflector for a spacecraft is elastically deformable so as to be capable of changing from a folded position, when inside the spacecraft, to a deployed position, outside the spacecraft, at least partly under the action of its own elasticity. The reflector is separated into at least two parts by first opposing slot edges forming a crossing slot, so that in the folded position, the first opposing edges move with respect to each other so as to allow a protruding peripheral part of the reflector to be arranged closer to a longitudinal end of the spacecraft with damaging any portion of the reflector. In one embodiment, the two parts may be further separated by a radial slot which is arranged substantially orthogonal to the crossing slot.

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: A new combination is formed of a deployable solar array and a deployable perimeter truss reflector within a single structure, defining a deployable perimeter truss reflector and solar array combination. In that combination the pliant reflective mesh, which serves as the RF reflector, is located at one circular end of the perimeter truss and the solar array is located at the other end. The solar array is formed with photovoltaic cells formed on both sides of a pliant film base. The photovoltaic cells are exposed to sunlight, either directly, or through the mesh, which is eighty percent porous to sunlight. Constructed in deployed form, for storage the truss contracts to the conventional non-deployed condition of a barrel-like configuration; and both the pliant reflective mesh that forms the reflector and the pliant base supporting the photovoltaic cells become tucked in place inside opposite ends of the barrel.

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: This invention is directed to a apparatus that includes an inflatable antenna reflector assembly for generating electromagnetic plane waves. The apparatus can be used in a variety of applications in which plane waves are beneficial, such as in a compact range to simulate the long-range behavior of a radar system to test a target for its radar signature. The inflatable reflector assembly of the apparatus includes a base, an arched frame mounted to the base, and an envelope-like cover that fits over the frame. The cover's front side is transmissive to electromagnetic waves, and its rear side is reflective to such waves. The apparatus can include a point source antenna feed, in which case the cover's reflective portion is made to be parabolic, or the antenna feed can be a line source, in which case the cover's reflective portion is spherical. The base can be rested directly on the floor or ground for support.

Abstract: A deployable reflector having an umbrella-like structure in which a plurality of tubular parabolically curved ribs are connected end-wise to a central hub by associated strain energy hinges, which are flexible and spring-like in characteristic, creating a spring force when stressed. A thin pliant metal coated film material is shaped for expansion into a parabolic shape serves as the reflective surface. Rib anchors, suitably radially extending pockets, attached to the backside of the material receive the ribs that radially extend from the hub. When stowed and restrained, such as by a cable, the curved ribs are all held down, collapsing the parabolic shape of the material, and stressing the hinges, which produce a counter-biasing force. When the restraining force is released to deploy the reflector, the biasing force created in the spring-like flexible hinges automatically pivots the ribs outwardly, pulling the material into its parabolic shape.

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: 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: A friction retaining device for holding and releasing reflector panels of a satellite. The retaining devices having a friction bushing mounted thereon to prevent the reflectors from becoming disengaged from the clamp. The retaining device has a pair of opposing arms having upper ends that communicate with bumpers on the reflectors and lower portions that communicate with a release mechanism. Upon actuation of a pyrotechnic device, the reflectors are deployed. At the same time, the release mechanism disengages the lower portions of the opposing arms allowing them to remove the bumpers from the reflectors.

Abstract: The integration of traveling wave tube amplifiers and multiplexers onto passive transmit array antenna panels deployed out board of a spacecraft bus to simultaneously provide a spacecraft transponder that permits antenna pattern flexibility in orbit, high DC to RF power conversion efficiency, facilitates higher spacecraft power and provides a spacecraft with deployed payload panel architecture having multiple independent beams that can be electronically reconfigured on the ground or in orbit.

Abstract: An apparatus for deploying an umbrella-type structure such as an antenna reflector is provided. The umbrella-type structure includes a plurality of rib members movable from a stowed configuration to a deployed configuration. The deployment apparatus comprises a movable deployment tube and a hub pivotally attached to the plurality of rib members and slidably attached to the deployment tube. The hub is adapted to move along the deployment tube. The deployment apparatus further includes a plurality of rib deployment straps connecting the deployment tube to the rib members and a mechanism for moving the deployment tube in order to tension the rib deployment straps which in turn pull the rib members into the deployed configuration. The apparatus includes structural members made of composite materials, having a low (near zero) coefficient of thermal expansion, low density, and high strength.

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: In a parabolic reflector system for directing or receiving radiation from or to a radiation feed, having a parabolic reflector surface defining a parabolic reflector axis, a parabolic reflector focus and a radiation aperture, wherein the parabolic reflector has a flat plate shroud attached thereto at the aperture thereof and a radome covering the shroud aperture.

Abstract: An antenna structure, such as an antenna reflector, comprises a collapsible mesh and catenary tie/cord attachment structure, retained in tension by a plurality of variable geometry spreader-standoffs connected to an inflatable tubular support hoop. The standoffs decouple the energy-focusing geometry of the antenna surface from the hoop, so as to reduce the sensitivity of the shape of the surface to variations in the shape of the tubing. Each spreader-standoff is connected to the hoop at a hinge joint of a pair of spreader-standoff elements, by a radial connection element retained in tension by the adjoining tubing. The hinge joint of a respective spreader-standoff pair is adjacent to an inner diameter side of the hoop, while distal locations of the spreader-standoff elements are located beyond an outer diameter side of the inflated hoop.

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: 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: A planar antenna comprises an emitting circuit plate having an emitting element made of a micro-strip antenna element, a first dielectric plate, and a feeder circuit plate having a feeder line, in which said feeder line are electromagnetically connected to said emitting element in said emitting circuit plate, and said emitting element is a ring circular emitting element containing a cross bridge conductor in the center thereof.

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

Abstract: An antenna having dual reflectors connected by a moving mechanism for moving the reflectors between stowed and deployed positions. In the stowed position the reflectors overlap and are positioned close to each other. In the deployed position the reflectors are spaced apart.

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: 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 parabolic antenna for measuring the level in containers is proposed, a transmitted pulse from a transmitting and receiving device being focused via the parabolic antenna and directed onto the surface of a filled material whose level is to be determined, and the pulse reflected at the surface of the filled material being received again by the receiving device via the parabolic antenna. For the purpose of introducing the measuring instrument through an opening in the container, the parabolic antenna can be folded and unfolded by being positively moved.

Abstract: A large aperture light-weight space borne telescope is provided which may be launched by a relatively small launch vehicle. A 6 to 8 meter primary telescope composed of, e.g., 30 segments arranged in two concentric rings is provided. Supplemental outer mirror segments are stowed behind and substantially perpendicular to the main mirror which is usable in the absence of supplemental mirror deployment. Deployment of outer mirrors segments provides a large aperture telescope with a large field of view. Other deployable components include a secondary mirror, a bus, deployable with respect to the optics portion, and one or more sun shade sheets or panels.

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.