Abstract: An element comprising a non-stick surface for substantially cleanly removing a product which is arranged against said non-stick surface. The element comprises a first layer of an pervious material, which is configured to allow a fluid to flow there through. An outer surface of said first layer provides the non-stick surface. The element comprises a second layer of an impervious material, which is configured to substantially block a flow of fluid there through. The second layer is arranged at a side of said first layer opposite to the outer surface. The element comprises ducts or chambers which are arranged in said first layer or in between said first and second layer. Said ducts or chambers are arranged in fluid connection with said pervious material and are configured for feeding a pressurized fluid to the pervious material. At least the first layer is formed using a three-dimensional printing tool.

Abstract: An on-orbit recycling method for a buffer foam of a cargo spacecraft includes the following steps: mechanically cutting a shaped PU foam into foam micro-blocks, and putting the foam micro-blocks into a packaging bag for packaging, where the packaging bag is filled with a foaming adhesive; the foaming adhesive includes a component A and a component B, which are independently packaged in a two-component packaging bag; and the component A and the component B are separated by a film; and squeezing the film between the component A and the component B, such that the two components are fully mixed, foamed and expanded to finally burst the two-component packaging bag, where after the packaging bag is burst, the foaming adhesive expands into gaps of the foam micro-blocks; and in a microgravity state of space, the foaming adhesive expands and fills uniformly in all directions and fully infiltrates the foam micro-blocks.

Abstract: Technology is disclosed for a spacecraft launch restraint and dispensing structure. Stacks of spacecrafts may be arranged around a central post. The dispensing structure has primary tie-down mechanisms that axially clamp the stacks of spacecrafts when in a stowed position. Each primary tie-down mechanism may have a rod located between two adjacent stacks, such that the rod tensions two stacks. In a deployment position, the primary tie-down rods extend away from the stack such that an ejection path is cleared. The dispensing structure also includes secondary tie-down mechanisms that radially connect the spacecrafts to the central post. After the primary tie-down rods are moved to the deployment position, the secondary tie-down mechanisms still hold the spacecrafts. The spacecrafts may be deployed by issuing control signals to the secondary tie-down mechanisms when the primary tie-down rods are in the deployment position.

Abstract: A solar array structure, such as for a spacecraft, uses thin solar array panels that, when in a stowed configuration, are stiffened by being bent or curved in one direction to be shaped like a section of a cylinder and placed within a rigid structural frame. As a curved solar panel is not as efficient as a flat panel directly facing the sun, the solar array panels are curved in their stowed configuration for launch only, but flatten after deployment by use of a partially flexible structural frame, where a rectangular frame is made of two opposing rigid sides and two opposing flexible sides, with a thin flexible solar panel attached to rigid sides only. The rigid sides are compressed during stowage to curve the panel before hold-down tensioning. The structure and panels return to their flat free state configuration after release.

Abstract: Technology is disclosed herein for a spacecraft launch restraint and dispensing structure. The dispensing structure has a number of trusses and a central structure. When the trusses are in a support position, each spacecraft may be supported at one point by the central structure and at two points by one or more of the trusses. Therefore, each spacecraft may be supported at three points, thereby providing a stable support for each spacecraft. The spacecrafts do not touch each other and do not bear the weight of other spacecrafts. In a deployment position, the trusses extend away from the satellites and do not support the satellites; however, the satellites initially remain connected to the central structure. In the deployment position, the trusses are out of an ejection path such that the satellites can be ejected in a desired sequence from the central structure.

Abstract: A system for analyzing a volatile component in extraterrestrial soil through penetration heating induction includes the following: a penetration heater, provided therein with a volatile component measurement and analysis module configured to analyze a volatile component in a detected medium; a gas capture hole, provided on a side wall of the penetration heater and used to divert the volatile component in the detected medium to the volatile component measurement and analysis module; a temperature acquisition module, disposed on the penetration heater and configured to acquire a temperature of the detected medium; and a heating module, disposed on the penetration heater and configured to acquire the temperature of the detected medium. The system has a compact structure, a simple function, and low engineering costs, and can directly detect and analyze a volatile component in deep extraterrestrial soil.

Abstract: A filter unit is provided to retrofit within signal lines that couple analog cockpit gauges to transducers in rotorcraft systems. The filter unit may include a housing assembly and an electromagnetic interference (EMI) filter assembly housed therein. The filter assembly may include a printed circuit board (PCB) having conductive PCB traces and a signal line input connector configured to connect to multiple transducer signal lines. The filter assembly may also include a signal line output connector configured to connect to multiple analog cockpit gauge signal lines and a plurality of common mode chokes electrically connected between the signal line input connector and the signal line output connector. Each common mode choke may be positioned on the PCB so that it does not electrically/magnetically interfere with the other common mode chokes of the plurality of common mode chokes.

Abstract: An effective system for verifying safety of an artificial intelligence system includes a feature quantity information accepting unit which accepts feature quantity information that includes values of plural feature quantities, that are assumed as those used in an artificial intelligence system, in each of plural first test data used for a test for verifying safety of the artificial intelligence system; and a judgment unit which judges a first combination, that is a combination that is not included in the plural first test data, in combinations of values that plural feature quantities may take, or a second combination, with it plural correct analysis results that should be derived by the artificial intelligence are associated, in the combinations of the values that the plural feature quantities may take.

Abstract: A referencing system to assist a receiver aircraft in relative positioning during in-flight refueling operation that includes an array of references congregated on a spot of the tanker aircraft, wherein the array of references provide a distinguishable visual indicator depending on the sector where the receiver aircraft positions.

Abstract: A III-V semiconductor pixel X-ray detector, including an absorption region of a first or a second conductivity type, at least nine semiconductor contact regions of the second conductivity type arranged in a matrix along the upper side of the absorption region, and optionally a semiconductor contact layer of the first conductivity type, a metallic front side connecting contact being arranged beneath the absorption region, and a metallic rear side connecting contact being arranged above each semiconductor contact region, and a semiconductor passivation layer of the first or the second conductivity type. The semiconductor passivation layer and the absorption region being lattice-matched to each other. The semiconductor passivation layer being arranged in regions on the upper side of the absorption region. The semiconductor passivation layer having a minimum distance of at least 2 ?m or at least 20 ?m with respect to each highly doped semiconductor contact region.

Abstract: A flow distributor for a heat transfer device having a plurality of channels includes a sheath defining a plurality of distributor holes, each distributor hole configured to be in fluid communication with a respective channel inlet of each channel of the heat transfer device and an insert defining a plurality of fluid channels therein and a fluid inlet, each fluid channel in fluid communication with the fluid inlet. The insert is disposed within the sheath to seal the fluid channels with each fluid channel in fluid communication with a respective one of the distribution holes. The fluid inlet includes an inner inlet and an outer inlet radially outward from the inner inlet for mixing a fluid flow in the fluid inlet for evenly distributing fluid flow (e.g., a two phase flow) into the fluid channels of the insert and into each channel of the heat transfer device.

Abstract: A method of determining a phase shift caused by reflection at, or transmission through, a dielectric coating as a function of wavenumber includes obtaining a nominal phase shift for the dielectric coating as a function of wavenumber, determining a first wavenumber and a second wavenumber for performing measurements of phase shift at these wavenumbers based on the nominal phase shift, determining a wavenumber shift based on a first measurement of phase shift at the first wavenumber, a second measurement of phase shift at the second wavenumber, and the nominal phase shift as a function of wavenumber, and determining the phase shift as a function of wavenumber based on the wavenumber shift and the nominal phase. Further described is a method of determining a layer design for a dielectric coating, wherein the dielectric coating comprises a plurality of stacked layers.

Abstract: A low-earth orbit (LEO) satellite includes a global positioning receiver configured to receive first signaling from a first plurality of non-LEO navigation satellites of a constellation of non-LEO navigation satellites in non-LEO around the earth. An inter-satellite transceiver is configured to send and receive inter-satellite communications with other LEO navigation satellites in a constellation of LEO navigation satellites. At least one processor is configured to execute operational instructions that cause the at least one processor to perform operations that include: determining an orbital position of the LEO satellite based on applying precise point positioning (PPP) correction data to the first signaling, wherein the PPP correction data is received separately from the first signaling; and generating a navigation message based on the orbital position.

Abstract: Structures and processes for improving radiation hardness and eliminating latch-up in integrated circuits are provided. An example process includes forming a first doped buried layer, a first well, and a second well, and using a first mask, forming a second doped buried layer only in a first region above the first doped buried layer and between at least the first well and the second well, where the first mask is configured to control spacing between the wells and the doped buried layers. The process further includes using a second mask, forming a vertical conductor located only in a second region above the first region and between at least the first well and the second well, where the vertical conductor is doped to provide a low resistance link between the second doped buried layer and at least a top surface of the substrate.

Abstract: A monolithic multi-junction solar cell comprising a first III-V subcell and a second III-V subcell and a third III-V subcell and a fourth Ge subcell, wherein the subcells are stacked on top of one another in the specified order, and the first subcell forms the top subcell and a metamorphic buffer is formed between the third subcell and the fourth subcell and all subcells each have an n-doped emitter layer and a p-doped base layer and the emitter doping in the second subcell is lower than the base doping.

Abstract: A space and wave division multiplexing and demultiplexing system and method for quantum key distribution (QKD) using free space laser communications. The system operates to transmit a quantum channel, including a key of QKD, included in a combined laser transmission with a classical channel, including an encrypted message of QKD. The laser transmission can be transmitted through free space to a lens, wherein it is diffracted into two separate diffraction patterns and captured by a double clad optical receiver fiber having an inner core and a concentric outer core. The diffraction pattern of the classical channel is captured by the outer core, while the diffraction pattern of the quantum channel is captured by the inner core, thus allowing separate treatment of each channel.

Abstract: The disclosed propulsion system of a space vehicle and the methods of operating the propulsion system use a microwave energy source to heat propellant in a propellant chamber that pierces and traverses a waveguide carrying the microwave energy. In some implementations, the microwave energy ionizes and further heats the propellant in the propellant chamber. The partially ionized and heated propellant may exit the propellant chamber via a nozzle to generate thrust.

Abstract: A tasking network system comprising a client system configured to send a tasking order and providing instructions for operating a remote device anonymously. An operations center including configured to receive an incoming tasking order and processor handling the incoming tasking order without receiving the client ID from the client. A security tag is associated with the tasking order which may be correlated in a remote server.

Abstract: A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays (such as flexible panels) and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.