Abstract: Methods, systems, and devices for wireless communications are described. An example method for object detection is provided which may include capturing at least three polarization angles of a scene. The method may include translating polarization parameters associated with the at least three polarization angles to a reference angle to create a vector map and resolving the vector map into parallel components and perpendicular components, wherein the parallel components are parallel to a plane of incidence of light in the scene and the perpendicular components are perpendicular. The method may further include determining a range map based at least in part on the parallel and perpendicular components, detecting an object present in the scene using the range map and an airlight scattering polarization component, and outputting an indication of the object.

Abstract: A space-grade solar array includes relatively small cells with integrated wiring embedded into or incorporated directly onto a printed circuit board. The integrated wiring provides an interface for solar cells having back side electrical contacts. The single side contacts enable the use of pick and place (PnP) technology in manufacturing the space-grade solar array. The solar cell is easily and efficiently packaged and electrically interconnected with other solar cells on a solar panel such as by using PnP process. The back side contacts are matched from a size and positioning standpoint to corresponding contacts on the printed circuit board.

Abstract: A three-dimensional print head apparatus including a securing mechanism, a hopper, a nozzle, a barrel, and a heating system. The securing mechanism is adapted to secure to a wrist joint of a robotic arm. The hopper is secured to the securing mechanism and has a cavity and a lower aperture. The nozzle has an upper aperture and a lower aperture. The barrel has an elongate, hollow member with a first end secured to the lower aperture of the hopper and a second end secured to the upper aperture of the nozzle. The heating system is positioned along the barrel.

Abstract: A method for depositing a multilayer coating onto a substrate includes supporting the substrate on a platen comprising an electrically conductive material disposed in a deposition chamber, connected to an electrical power supply and electrically insulated from an electrode. The pressure in the deposition chamber is less than 10 Torr when a first feedstock is fed to the substrate. The electrical power supply is activated to create a plasma surrounding the substrate which ionises and/or activates particles within the first feedstock, allowing the ionised and/or activated particles from the first feedstock to deposit on the substrate and polymerise, thereby forming a first a coating on the substrate. Particles of a second feedstock, different from the first feedstock, are fed to the substrate and are ionized and/or activated by the plasma and allowed to deposit on the substrate and polymerise to form a second coating on the substrate.

Abstract: A stacked, high-blocking III-V semiconductor power diode having a first metallic terminal contact layer, formed at least in regions, and a highly doped semiconductor contact region of a first conductivity type and a first lattice constant. A drift layer of a second conductivity type and having a first lattice constant is furthermore provided. A semiconductor contact layer of a second conductivity, which includes an upper side and an underside, and a second metallic terminal contact layer are formed, and the second metallic terminal contact layer being integrally connected to the underside of the semiconductor contact layer, and the semiconductor contact layer having a second lattice constant at least on the underside, and the second lattice constant being the lattice constant of InP, and the drift layer and the highly doped semiconductor contact region each comprising an InGaAs compound or being made up of InGaAs.

Abstract: Embodiments of the present disclosure are directed to techniques for autonomously transitioning a spacecraft from a power-saving state to a power-consuming state at a time after launch of the spacecraft on a launch vehicle. Because the spacecraft can autonomously detect conditions for transitioning to the power-consuming state, commands received via an umbilical connection to the launch vehicle, or detecting the presence or absence of such a connection, is unnecessary, thereby removing several technical barriers to eliminating such umbilical connections altogether. In some embodiments, low-cost vacuum detection devices that use very small amounts of power may be used by the spacecraft to detect when the spacecraft has reached an altitude suitable for transitioning to the power-consuming state.

Abstract: A radiative fin for a spacecraft is disclosed having an end fitting of heat conductive material, configured to be mounted on the spacecraft, a flexible radiative laminate, connected to the end fitting at one end and having an opposite free end, at least one pyrolytic graphite sheet, and at least one heat emission layer in contact with the pyrolythic graphite sheet on at least part of the surface of the pyrolythic graphite sheet, and a flexible rod, extending from the end fitting along at least part of a side of the flexible radiative laminate and being affixed to the latter. The flexible rod is adapted to occupy a folded position and a deployed position and to exert, while in the folded position, a deployment torque adapted to bring the flexible rod back to the deployed position.

Abstract: Techniques for deploying a plurality of smallsats from a common launch vehicle are disclosed where a structural arrangement provides a load path between an upper stage of the launch and the plurality of spacecraft. Each spacecraft is mechanically coupled with the launch vehicle upper stage only by the structural arrangement. The structural arrangement includes at least one trunk member that is approximately aligned with the longitudinal axis of the launch vehicle upper stage, a plurality of branch members, each branch member being attached to the trunk member and having at least a first end portion that is substantially outboard from the longitudinal axis; and a plurality of mechanical linkages, each linkage coupled at a first end with a first respective spacecraft and coupled at a second end with one of the plurality of branch members, the trunk member or a second respective spacecraft.

Abstract: A connecting-separating device is for separating satellites from launchers or satellite dispensers. Circumferentially aligned clamps can be coupled on their inner face on rings of separable elements constituting the union interface between the two separable elements. A release mechanism connects two of the clamps through one of the ends of the clamps. The two clamps are connected by the release mechanism include a protrusion protruding from their outer faces at the end opposite the end connecting with the release mechanism. The rest of the clamps include a protrusion protruding from their outer faces at each of their ends adjacent the adjacent clamps, so that each pair of clamps adjacent and not connected to one another by the release mechanism are connected to one another by connectors connecting the protrusions.

Abstract: An additive manufacturing device build platform is disclosed having a build area having an initial build surface, the initial build surface further having an outer area that is separable from the initial build area for use as a secondary build surface, the outer area having a rotation mechanism wherein the secondary build surface is locatable in a different plane away from the initial build surface by placement of the outer area with the rotation mechanism. Another system and method are also disclosed.

Abstract: In order to provide processor elements and programmable devices, which have little restriction on logical block arrangement and wiring, and which can improve a degree of integration, processor element 1 includes: arithmetic units 11 that perform arithmetic processing on the basis of functions which have implemented instruction sets generated in accordance with programs; registers 12 that store arguments of the functions; bypass switches 13 of the arithmetic units 11; bypass switches 14 of the registers 12; a connection setting unit 16 that switches the connections of function units 20; a multiplexer 17 that switches the input to the connection setting unit 16; a demultiplexer 18 that switches the output destination of the output from the connection setting unit 16; and a selection unit 15 that switches, in accordance with a state, the bypass switches 13, 14, the connection setting unit 16, the multiplexer 17 and the demultiplexer 18.

Abstract: A product display merchandiser includes a product support, a pair of sidewalls extending upwardly from respective sides of the product support, a first product stop extending upwardly from a front end of the product support, and a second product stop extending from at least one of the pair of sidewalls.

Abstract: A solid state power amplifier uses a Doherty power amplifier that can be implemented as a monolithic microwave integrated circuit. By adjusting the DC bias of the amplifying stages in each branch of the Doherty amplifier, the output power, linearity, and DC power can be adjusted to provide a specified output, where the specification for the output can include the maintaining of desired DC power and linearity. The Doherty power amplifier can be used in a satellite payload or other application utilizing solid state power amplifiers, while providing the proper amount of RF output power and DC power. A single amplifier can have its bias levels adjusted for different output levels, helping to minimize the number of designs that are required for a given satellite payload, reducing the variety of parts in a satellite payload.

Abstract: A device and method for printing 3D articles including electronic and functional elements including 3D printer and a plasma jet printer based on a dielectric barrier atmospheric pressure plasma jet system in which both printing and in-situ treatment and post-deposition treatment can be carried out to tailor the materials characteristics. Plasma jet printer comprising of electrodes in the nozzle/print head for applying electric field and generating atmospheric plasma that could be used for non-gravity based highly directional printing in any direction. Integration of dielectric barrier plasma printer and plasma treatment jets with the 3D printer increases the capability of embedding high performance electronics in a 3D printed structure aiding in additive manufacturing of functional devices. Ability to use a range of materials for print head assembly including micro machined silicon increases the resolution of the plasma jet printer to sub-micron level.

Abstract: An all-printed physically unclonable function based on a single-walled carbon nanotube network. The network may be a mixture of semiconducting and metallic nanotubes randomly tangled with each other through the printing process. The unique distribution of carbon nanotubes in a network can be used for authentication, and this feature can be a secret key for a high level hardware security. The carbon nanotube network does not require any advanced purification process, alignment of nanotubes, high-resolution lithography and patterning. Rather, the intrinsic randomness of carbon nanotubes is leveraged to provide the unclonable aspect.

Abstract: Systems and methods can support a portable aperture array antenna system having a support structure of a substantially hemispherical geometry formed of a plurality of rigid linear elements. A membrane may be positioned upon an outer surface of the support structure. A plurality of antenna elements may be positioned coplanar to the membrane. A radio frequency transmission assembly may operate to couple output signals from the antenna elements into one or more signal-processing modules. The signal-processing modules may be configured to model the motion of two or more satellites, focus electromagnetic beams in the respective directions of the satellites, and steer the electromagnetic beams from horizon to horizon to follow the satellites simultaneously without motion of physical components.

Abstract: A stacked high barrier III-V power semiconductor diode having an at least regionally formed first metallic terminal contact layer and a heavily doped semiconductor contact region of a first conductivity type with a first lattice constant, a drift layer of a second conductivity type, a heavily doped metamorphic buffer layer sequence of the second conductivity type is formed. The metamorphic buffer layer sequence has an upper side with the first lattice constant and a lower side with a second lattice constant. The first lattice constant is greater than the second lattice constant. The upper side of the metamorphic buffer layer sequence is arranged in the direction of the drift layer. A second metallic terminal contact layer is arranged below the lower side of the metamorphic buffer layer sequence. The second metallic terminal contact layer is integrally bonded with a semiconductor contact layer.

Abstract: For power-enhanced slew maneuvers, a method determines a power collection function for a satellite. The method determines a power cost function for the satellite. The method calculates a power enhanced slew maneuver based on the power collection function and the power cost function.

Abstract: A byte stuffing circuit and a byte stuffing method are provided. The byte stuffing method includes: receiving a first data stream and generating a second data stream according to the first data stream, where a first size of the first data stream is N bytes, and a second size of the second data stream is 2N bytes; in response to an Xth byte of the second data stream matching a first flag byte, overwriting the Xth byte with a first stuffing byte, and inserting a second stuffing byte into an (X+1)th byte of the second data stream, where X is a positive integer between 1 and 2N?1; combining a remnant data stream and a first part of the second data stream to generate a third data stream, and configuring a second part of the second data stream as the remnant data stream; and outputting the third data stream.

Abstract: An indication device for monitoring the structural integrity of a repair location on a laminate structure, produced from a composite material, of a part of an aircraft outer skin is specified. The indication device has at least one elongate, thin indicator strip. The indicator strip is detachably applied to the outer layer of the laminate structure in the immediate vicinity of the repair location. The indicator strip is designed to indicate a predefined residual strength of an adhesive joint of a repair patch to the surrounding composite material.