Abstract: Spacecraft and antenna apparatus that can be more easily deployed from a stored state can include: a main-reflection unit including a plurality of ribs formed to be deployable in a stored state in which the ribs are folded and a sheet body provided between a plurality of the ribs and configured to be capable of reflecting a radio wave radiated from a radiator and emitting the radio wave outside, and a restriction member configured to restrict deployment of the plurality of ribs in the stored state, and release the restriction by operation of a restriction release member different from the main-reflection unit.

Abstract: A satellite system can include one or more satellites that orbit the Earth. The one or more satellites may have satellite buses that support antenna arrays. The antenna arrays may include space fed arrays. Each space fed array may have an antenna feed array and an inner array that is coupled to a direct radiating array. The direct radiating array may operate in the same satellite band as the space fed array, or upconversion and downconversion circuitry may be used to communicatively couple a direct radiating array that operates in a different satellite band to the space fed array. The satellites may have peripheral walls with corner fittings that can be selected to provide the satellite bus with particular leg strengths. This can reduce overall mass of the satellites in a payload fairing while accommodating different types of antenna arrays.

Abstract: An antenna diameter adjustment method for adjusting an antenna diameter by changing a distance between a part of each of a plurality of reflectors at which the radio signal is reflected, the plurality of reflectors each being configured to reflect radio signals emitted from a plurality of radiators from a center of a circle along a radial direction thereof and to radiate the radio signal toward an opposite antenna apparatus, and the center of the circle along the radial direction of the circle.

Abstract: A high throughput fractionated satellite (HTFS) system and method where the functional capabilities of a conventional monolithic spacecraft are distributed across many small or very small satellites and a central command and relay satellite, the satellites are separated and flight in carefully design formations that allows the creation of very large aperture or apertures in space drastically reducing cost and weight and enabling high throughput capabilities by spatially reuse spectrum.

Abstract: A system includes one or more antennas; and a processor to control a directionality of the antennas in communication with a predetermined target using 5G protocols.

Abstract: Provided is a deployable reflector that includes a reflector, a tensioning frame with a deploying ring including upper booms and lower booms, sections composed of lower rods and upper rods and including pantograph levers, stanchions mounted between the upper booms and the lower booms, scissors-like levers located at an intersection of the pantograph levers, first sleeves put on the pantograph levers, second sleeves disposed on the lower rods and the upper rods, cylindrical joints disposed on the second sleeves, an expansion ring for connecting the upper rods and the lower rods, a reflector fixing mesh having triangular cells composed of elastic rods, an upper concave mesh and a lower convex mesh fastened with peripheral units and composed of triangular shape cells, where the reflector is attached to the upper concave mesh directly or is fastened to the upper concave mesh with a spatial shape gasket.

Abstract: The invention is directed to deployable reflectarray antenna structure. In one embodiment, the deployable reflectarray antenna structure includes a pair of flexible electrical elements, a feed antenna, and a deployment mechanism that employs a plurality of tapes to respectively transition the pair of flexible electrical elements from an undeployed state in which the elements are folded towards a deployed state in which the deployment mechanism and electrical elements cooperate to form a reflectarray and a subreflector of a reflectarray antenna structure. Further, the deployment mechanism also operates to position the reflectarray and subreflector relative to one another and to the feed antenna so as to realize a reflectarray antenna structure.

Abstract: Deployable reflector system includes a support structure and a reflector surface secured to the support structure. The support structure transition from a compact stowed configuration to a larger deployed configuration to deploy the reflector surface. The reflector surface is comprised of a carbon nanotube (CNT) sheet. The sheet is intricately folded in accordance with a predetermined folding pattern to define a compact folded state. This predetermined folding pattern is configured to permit automatic extension of the CNT sheet from a compact folded state to a fully unfolded state. The unfolding operation occurs when a tension force is applied to at least a portion of the peripheral edge of the CNT sheet. In some scenarios, the support structure can comprise a circumferential hoop.

Abstract: A doubly curved reflector for compact storage in a folded state includes a plurality of gores, each gore having on either long side a gore side curve. At least one hinge is mechanically coupled between each adjacent gore, the at least one hinge including a fold roll hinge or a living hinge. In a stowed doubly curved reflector state each gore folds about the at least one hinge when folded closed such that a face surface of each gore folds against an adjacent face surface of another gore into a substantially cylindrical structure. In a deployed doubly curved reflector state, each hinge. A doubly curved reflector for compact storage in a folded state and a locked open state, a method of manufacture, and a method for designing a substantially wrinkle free doubly curved foldable reflector having gores of a composite material are also described.

Abstract: A reusable modular spacecraft has a spacecraft bus structure configured to support spacecraft subsystems, at least one interchangeable housing component configured to be interchangeably received and supported by the bus structure, and a wireless system configured to permit wireless communication between the at least one interchangeable housing component and spacecraft subsystems supported by the bus structure. In embodiments of the spacecraft, the wireless system includes a wireless hub and a wireless coordinator for wireless transmission of data between the at least one interchangeable housing component and the spacecraft subsystems. An electrical/power transfer interface unit is provided to the at least one interchangeable housing component for transferring electricity, power, data and/or providing thermal management and control.

Abstract: A circuit has at least one amplifier and a signal routing device such as one or more switches, and an array of antenna elements from which some subset must be enabled and processed at a time. The antenna elements can be grouped in accordance with an organization scheme (e.g., rows, columns) to enable more flexibility in selecting and routing the signals. The system is used to create one or more beams, which can be pointed (steered) to a wide range of directions by means of selecting one or more feed antennas in a switched-feed antenna without including full receive and transmit circuitry (DSP, frequency conversion) for each feed in the array. In this case, minimizing the number of DSP chains is desirable to reduce the cost, power, and complexity of the antenna. The resulting beam(s) can be combined and manipulated to support multiple users, track several targets, increase operational range, increase radar resolution, or data-rate in communications.

Abstract: Perimeter truss reflector includes a perimeter truss assembly (PTA) comprised of a plurality of battens, each having an length which traverses a PTA thickness as defined along a direction aligned with a reflector central axis. A collapsible mesh reflector surface is secured to the PTA such that when the PTA is in a collapsed configuration, the reflector surface is collapsed for compact stowage and when the PTA is in the expanded configuration, the reflector surface is expanded to a shape that is configured to concentrate RF energy in a predetermined pattern. Each of the one or more longerons extend around at least a portion of a periphery of the PTA. These longerons each comprise a storable extendible member (SEM) which can be flattened and rolled around a spool, but exhibits beam-like structural characteristics when unspooled.

Abstract: A method of manufacturing an antenna using a radome (10) comprising a front portion (30) and a rear portion (20), the front and rear portions (20, (30) configured to define an interior cavity in which an antenna arrangement is received, the method comprising placing an antenna panel on an inside of one of the front and rear portions, and bringing the portions together, whereby the front portion (30) includes a peripheral channel region (31) configured to contain an adhesive sealant (60) and receive a peripheral edge (21) of the rear portion (20) that is partially submerged in the adhesive sealant (60) before it cures. Additional mechanical fastening clip engagement members (23; 33) are provided inside both the front and rear portions (20; 30) that engage with one another and mechanically secure the radome front and rear portions (20; 30) to each other, in addition to the adhesive joint provided by the adhesive sealant (60) once cured.

Abstract: A computer assisted method for manufacturing a foldable paraboloid antenna includes election of a two-dimensional radial Origami pattern with triangular cells and election of a paraboloid surface. The Origami pattern is projected from the paraboloid surface focus onto the paraboloid surface to print the Origami pattern on the paraboloid surface, obtaining triangles with curved sides. A pattern with triangles with straight sides on the paraboloid surface is obtained by joining vertices of the projected curved-sided triangles. The method includes scaling and calculating centroids of the triangles, to reduce each triangle referenced on the corresponding centroid and to determine spacing, obtaining a mesh with segments and triangular cells delimited by the segments. The triangular cells have triangles of reflective rigid material. The mesh is flexible, so each segment width is at least the sum of the thicknesses of two adjacent rigid triangles, and periphery cells have a rounded outer edge.

Abstract: A deployable assembly for antennae includes a structure having a reflective surface and n pairs of segments, each pair of segments corresponding to one side of a deployed polygonal shape. N hinge joints are between the two segments of a side. N hinged angular links are between every two adjacent sides. The structure is changeable from a stowed substantially cylindrical shape into a deployed substantially planar polygonal shape with n sides. A deployable boom is between two segments. The boom lays stowed between the two segments before deployment and ends in a feeder electromagnetically feeding the antenna and includes a clamping element for keeping the structure closed when stowed. The feeder acts as structural support element when stowed and electromagnetic feeder for the antenna when deployed. A cable network shapes the reflective surface, with corresponding cables held by tensor elements protruding from the back of the segments.

Abstract: A method and apparatus for electrical addressing for an antenna (e.g., a metamaterial radio-frequency (RF) antenna are described. In one embodiment antenna comprising: a plurality of radio-frequency (RF) radiating antenna elements located in a plurality of rings; and matrix drive circuitry coupled to the plurality of RF radiating antenna elements to drive the antenna elements, wherein the matrix drive circuitry to uniquely address each of the antenna elements using a matrix of a plurality of rows and a plurality of columns with a non-grid-based addressing structure.

Abstract: An antenna structure may include a solid antenna structure and a mesh antenna structure. The mesh antenna structure may be coupled to an outer edge of the solid antenna structure through two or more ribs. The two or more ribs may be configured to extend away from the solid antenna structure to expand the mesh antenna structure and increase a surface area of the antenna structure.

Abstract: An optical structure is provided. The optical structure includes an optical element and a plurality of protrusions. The optical element has a planarized top surface. The plurality of protrusions are disposed on the planarized top surface, wherein each of the plurality of protrusions independently has a size in the subwavelength dimensions.

Abstract: An antenna includes ribs that have been folded to fit within a frame, a conductive mesh coupled to the ribs, an arm that has been folded to fit within the frame, and a feed disposed at a distal end of the arm.

Abstract: A deployable structure for use in establishing a reflectarray antenna is provided that includes a flexible reflectarray and a deployment structure that includes an endless pantograph for deploying the flexible reflectarray from a folded, undeployed state towards a deployed state in which the flexible reflectarray is substantially planar. In a particular embodiment, the deployment structure includes a plurality of tapes that engage the endless pantograph and are used to establish a positional relationship between the deployed reflectarray and another component of the reflectarray antenna.

Abstract: A deployable reflector for an antenna is disclosed. The deployable reflector comprises a deployable membrane configured to adopt a pre-formed shape in a deployed configuration, and an electrically conductive mesh disposed on a surface of the membrane wherein the electrically conductive mesh is configured to permit relative lateral movement between the electrically conductive mesh and the membrane during deployment of the reflector. In the deployed configuration, the conductive mesh adopts the shape of the membrane and forms a reflective surface of the reflector. A method of manufacturing the deployable reflector is also disclosed.

Abstract: A system includes one or more antennas; and a processor to control a directionality of the antennas in communication with a predetermined target using 5G protocols.

Abstract: In one embodiment of the present disclosure, a satellite communication system includes a satellite constellation including a plurality of satellites in non-geosynchronous orbit (non-GEO), wherein at least some of the plurality of satellites travel in a first orbital path at a first inclination, and an end point terminal having an earth-based geographic location, the end point terminal having an antenna system defining a field of regard for communicating with the satellite constellation, wherein the field of regard is a limited field of regard, wherein the field of regard is tilted from a non-tilted position to a tilted position, and wherein the tilt angle of the tilted position is a function of the latitude of the geographic location.

Abstract: In particular, a method performed by one or more devices is disclosed, the method comprising: obtaining a first intensity information item (210) representative of a spectral image (208) resulting from an soiling (202, 302) of a textile (200, 304); obtaining a second intensity information item (212, 214) representative of a spectral image (216) characteristic of at least one property of at least one part of the textile (200, 304); determining at least one treatment parameter, wherein the determination of the treatment parameter takes place dependent both on the composition of the soiling (202, 302) from the first intensity information item (210) and on the at least one property of at least the part of the textile (200, 304) from the second Intensity information item (212, 214); and outputting or triggering an outputting of the at least one treatment parameter.

Abstract: A 2.2M offset antenna includes a reflector hub; a positioner for supporting the reflector hub; a plurality of reflector panels including a first plurality of side panels and a second plurality of side panels, the first plurality of side panels and the second plurality of side panels each being selectively securable to the reflector hub; each side panel of the first plurality of side panels being uniquely sized relative to the other side panels of the first plurality of side panels such that the first plurality of side panels may be nested together in a stacked configuration when separated from reflector hub; and each side panel of the second plurality of side panels being uniquely sized relative to the other side panels of the second plurality of side panels such that the second plurality of side panels may be nested together in a stacked configuration when separated from reflector hub.

Abstract: A method for manufacturing in space a rigid structure having a lattice is disclosed. The method includes creating of at least two framework elements from a coil of metal strip or wire, and creating of the lattice by cold-connecting the framework elements.

Abstract: A large reflector inflatable telescope. The telescope has an inflatable hull with a conical lower portion and a hemispherical upper portion. The conical portion is transparent to electromagnetic waves so that radio or light waves can reach an inner reflector, which is interposed between the conical portion and the hemispherical portion. The presence of the inner reflector allows the conical portion and the hemispherical portion to be inflated at different pressures such that the reflector becomes spherical or parabolic. If desired, the reflector can be made adjustable with a membrane behind the reflector that provides electro-static force to shape the reflector.

Abstract: An expandable antenna includes: a plurality of ribs arranged with a regulated angular pitch at an outer circumferential portion of a hub; and a metal mesh installed between the plurality of adjacent ribs, wherein each of the plurality of ribs is formed in a horizontally elongated thin flat plate shape with elasticity, and a segment to which the metal mesh is attached is formed in a parabolic shape. A flat plane of each of the plurality of ribs is arranged so as to be substantially parallel to a central axis of the hub. The object of the present invention is to provide the expandable antenna which can be easily expanded in outer space with a simple structure and can realize a desired shape after expansion.

Abstract: A method for deploying a trough structure. The methods comprise: causing a first telescoping segment to move in a first direction away from a proximal end of a telescoping boom; and transiting a flexible element from an untensioned state to a tensioned state as the first telescoping segment is moved in the first direction. The flexible element is coupled to a distal end of the first telescoping segment by a first bulkhead and is coupled to a distal end of a second telescoping segment by a second bulkhead. The first telescoping segment is coupled to the second telescoping segment of the boom when the first telescoping segment reaches an extended position. The flexible element has a parabolic trough shape when in the tensioned state.

Abstract: A deployable structure includes a plurality of interconnected elongated support members, deployed from a stowed state to an expanded state in which the support members are arranged in a ring. Each support member is provided with a connector (28) for longitudinal movement during deployment with respect to the support member. An actuating support member (27) has a drive member (50) for longitudinal movement with respect to the actuating support member, and an electromagnetic device arranged to drive the drive member in one direction with respect to the actuating support member. The drive member is connected to the connector by a lost motion connector, thus the connector is capable of moving in said one direction even if the drive member is not moved by the electromechanical device.

Abstract: An inflatable non-imaging solar concentrator based concentrating solar thermal and photovoltaic system powered water desalination system comprises a concentrating electricity and heat cogeneration subsystem, a battery storage subsystem, a thermal storage subsystem with electric heater, a thermal power regeneration subsystem, and a water distillation system with electric heater. The inflatable non-imaging solar concentrator makes the concentrating system substantially low cost, and the hybrid solar thermal and photovoltaic panels used to construct the cogeneration receiver make the system ultra-high efficient. The cogenerated thermal energy is stored in a thermal storage and the cogenerated electric energy is stored in a battery storage to heat the stored thermal energy to pre-set high temperature for thermal power regeneration. The thermal energy after thermal power generation is used to desalinize water with assistance of electric heater powered by the stored electricity.

Abstract: An inflatable antenna is disclosed herein that is capable of being deployed in space and other suitable environments and configured to improve RF performance and mechanical stability. Related methods for manufacturing and deploying such inflatable antennas are also described. The inflatable antenna can be configured to form a Gregorian dual reflector confocal parabolic antenna system when inflated. Various antenna structures, mechanisms, and manufacturing and deployment techniques are also disclosed herein that improve the precision and accuracy of RF reflective surfaces of the primary and secondary reflectors, confocal alignment of the primary and secondary reflectors, mechanical stability, and/or to improve the range of RF operation. The inflatable antenna can be manufactured and deployed with less complexity and more precision than existing inflatable antennas.

Abstract: An antenna having a feed horn assembly, a parabolic reflector assembly, and a mounting bracket assembly. The feed horn assembly has a circuit board housing having first and second molded housing halves and a main support arm. The feed horn assembly is adjustable, whereby the main support arm is adjusted from a collapsed configuration to an elongated configuration and vice-versa. The feed horn assembly further has a printed circuit board, a coaxial feed cable, an arm holder, and a coaxial radio frequency connector. The printed circuit board is triangular in shape. The circuit board housing houses the printed circuit board. The main support arm has a plurality of arm adjustment holes and extends from the arm holder to the circuit board housing. From the collapsed configuration to the elongated configuration there are intermediate configurations. The antenna has single polarization.

Abstract: An air compressor includes a tank unit that stores compressed air, a motor unit that generates compressed air to be stored in the tank unit, a pressure detection unit that detects a pressure value in the tank unit, and a control unit that drives the motor unit when a pressure value in the tank unit detected by the pressure detection unit is equal to or less than a motor start pressure value, and stops the motor unit when the pressure value in the tank unit detected by the pressure detection unit is equal to or greater than a motor stop pressure value. The control unit changes at least either of the motor start pressure value or the motor stop pressure value every time when a predetermined time passed.

Abstract: A stackable pancake satellite that is configured so that a plurality of the satellites can be stacked within a payload fairing of a launch vehicle. Each satellite includes sections that are folded or rotated together prior to launch, and unfolded or rotated away from each other when deployed. A first section is a satellite body having a first side that acts as a thermal radiator and a second side opposite the first side that includes an antenna. A second section includes one or more solar panels attached adjacent to the first side of the satellite body. A third section includes a splash plate reflector attached adjacent to the second side of the satellite body that reflects signals between Earth and the antenna. When deployed, the solar panels are pointed towards the Sun and the splash plate reflector directs the signals between the Earth and the antenna.

Abstract: Reflector antenna system includes a hoop assembly comprising a plurality of link elements which are rigid and extend between a plurality of hinge members, the hoop assembly expandable between a collapsed condition where the link elements are substantially parallel to one another and an expanded condition wherein the link elements define a circumferential hoop around a central axis. The hoop assembly defines a plurality of N rectangular sides, each comprised of an X-member including first and a second link element in a crossed configuration. A plurality of tension elements extend around the periphery of the side and apply tension between opposing ends of the first and second link elements in directions aligned with the top, bottom and two opposing sides.

Abstract: A reflector assembly including a truss engaging the first net at a first plurality of points along the first net perimeter edge and engaging a second net at a second plurality of points along the second net perimeter edge. A truss deployment assembly moves the truss between a truss stowed condition and a truss deployed condition, the truss in the truss deployed condition tensioning said first net or said second net to maintain a substantially flat or parabolic net outer surface. A reflector disposed at the first net sends or receives remote data.

Abstract: A balloon reflector antenna for a satellite, including a spherical balloon with a surface transparent to electromagnetic waves and a reflective surface opposite the transparent surface. The balloon reflector antenna may further include a feed system extending from the center of the balloon that receives electromagnetic waves reflected off the reflective surface and/or outputs electromagnetic waves that are reflected off the reflective surface.

Abstract: A foldable radio wave antenna includes a foldable parabolic reflector member formed a foldable tension member attachable to the peripheral rim of the reflector member.

Abstract: The present disclosure describes an antenna that has a parabola-shaped, flexible reflector member and one or more radial ribs embedded in the flexible reflector member and arranged to bias the reflector member in an open state.

Abstract: Optical modules used in exposure processes, in particular to optical modules of microlithography systems, are disclosed. Methods for deforming an optical element of an optical module as well as to optical imaging arrangements, optical imaging of methods and a method of manufacturing an optical element, are also disclosed. The disclosed technology may be used in the context of photolithography processes for fabricating microelectronic devices, in particular semiconductor devices, or in the context of fabricating devices, such as masks or reticles, used during such photolithography processes.

Abstract: A collapsible truss and method that is particularly suitable for staging and lighting, for shows, performances and other events. This evolved and novel modular truss can be collapsed to a significantly smaller size (i.e. increased density), and consequently requires significantly less space for storage and transportation. Further, in addition to the advantage of rapid assembly from collapsed parts to a full truss, the modular construction of the truss provides cost effective repair of this truss over traditional rigid welded trusses by simple replacement of damaged parts.

Abstract: Gossamer apparatus and systems for use with spacecraft may include a deployable gossamer apparatus. The deployable gossamer apparatus may include a plurality rib members and gossamer material extending therebetween and may be configured in a stowed configuration and a deployed configuration. The rib members of the deployable gossamer apparatus store potential energy used for deployment of the deployable gossamer apparatus.

Abstract: The present invention relates to an in-service reconfigurable antenna reflector comprising a rigid support and a membrane, deformable and having radio-electric reflectivity properties. According to the invention, the reflector comprises a plurality of coupling means connecting the rigid support and the membrane, comprising a first link of finger ball joint type connected to the rigid support, and a second link of finger ball joint type connected to the membrane. Each coupling means furthermore comprises a linear actuator, comprising a rotary motor and a screw-nut assembly, connected to the two links of finger ball joint type, and able to generate, in an operational configuration, a translational motion allowing the deformation of the membrane.

Abstract: A reflector is provided according to various embodiments. The reflector may include a backing structure having various configurations. The backing structure, for example, can comprise a plurality of trusses, flexible couplings, stiffeners, and crossbeams in any number of arrangements.

Abstract: An airborne photovoltaic solar system, comprising a parabolic reflector-concentrator (110, 1210), spread by wind, a solar panel (102, 1202) raised to high altitude using at least one lighter than air balloon (103, 1201), tracking the sun using aerodynamic surfaces and/or changes in buoyancy, relying on wind and/or cold air to cool the solar panel in one embodiment, as well as related methods and variations and alternatives.

Abstract: A high impact and load bearing building panel includes a first magnesium oxide board, a phenolic resin sheet, an expanded polystyrene layer, and a second magnesium oxide board. The phenolic resin sheet is laminated with the expanded polystyrene layer, and the first magnesium oxide board is laminated with the phenolic resin sheet opposite of the expanded polystyrene layer. The second magnesium oxide board is laminated with the expanded polystyrene layer opposite of the phenolic resin sheet. The high impact and load bearing building panel is used for building construction to constructs exterior walls, interior walls, roofs, floors, and foundation systems.

Abstract: A mechanical support ring structure for supporting a deployable space reflector antenna. The mechanical support ring structure is convertible from a folded state into a deployed state and includes a ring-shaped pantograph having a plurality of circumferentially arranged pantograph sections which are deployable for converting the mechanical support ring structure from the folded state into the deployed state, and a plurality of circumferentially arranged support rods, each pantograph section being arranged between a respective pair of support rods, wherein each pantograph section includes one or more pairs of pantograph rods which intersect crosswise with each other at a respective crossing position.

Abstract: A passive intermodulation modulation reducing structure for a multicarrier reflector system, including a plurality of flexible reflector gores, each gore having a thin layer of conductive metal, a first layer of dielectric material laminated to one face of the conductive metal, and a second layer of dielectric material laminated to an opposite face of the conductive metal. Capacitive coupling joins the reflector's RF components. The structure can be a deployable parabolic reflector for a satellite antenna.

Abstract: A structural insulated building panel with a moisture barrier seal includes a structural insulated panel, a seal section, a first spline-receiving grove, and a second spline-receiving groove. The seal section is extended from a phenolic resin sheet of the structural insulated panel so that the seal section can be positioned in between multiple structural insulated panels in order to prevent moisture penetration. The seal section is adjacently positioned with the second spline-receiving groove of the initial structural insulated panel and extends into the first spline-receiving groove of the adjacent structural insulated panel during the installation of multiple structural insulated panels.