Abstract: Disclosed are watercrafts with rotatable air propulsion steering units and retractable measurement instruments. The watercraft can include a substantially flat bottom, a top deck, a rotatable air propulsion steering unit configured to propel the watercraft and to rotate in order to steer the watercraft when the watercraft is submerged in a liquid body without requiring a submerged rudder steering system under the substantially flat bottom. The watercraft can also include a retractable measurement deck configured to alternatively raise measurement instruments above the liquid body and lower into the liquid body.

Abstract: An optical receiver component, wherein the receiver component comprises a first type of partial-voltage source with a first absorption edge and a second type of partial-voltage source with a second absorption edge, and the first absorption edge lies at a higher energy than the second absorption edge. Each partial-voltage source produces a partial voltage, provided a photon flux at a specific wavelength strikes the partial-voltage source, and the two partial-voltage sources are connected in series. A first number of series-connected sub-partial-voltage sources of the first type and a second number of series-connected sub-partial-voltage sources of the second type are provided. The first number and/or the second number are greater than one, and the respective deviation of the source voltages of the sub-partial-voltage sources among themselves is less than 20% in both types. Each sub-partial-voltage source comprises a semiconductor diode with a p-n junction.

Abstract: A spacecraft includes an aft surface, a forward surface and a main body structure disposed therebetween, a stowage and deployment arrangement (SDA) joined to the main body structure by a first mechanical coupling, and an antenna that includes a respective feed element and a rigid antenna reflector coupled with the main body by way of the SDA. The feed element is joined to the main body structure by a second, different, mechanical coupling. The spacecraft is reconfigurable from a launch configuration, with the reflector is disposed forward of the forward surface, with its aperture plane substantially parallel to the forward surface, to an on-orbit configuration. The SDA repositions the reflector to a second position corresponding to the on-orbit configuration. In the second position, the reflector is disposed, Earth facing, substantially aft of the forward surface and outboard of the main body structure and is illuminated by the respective feed element.

Abstract: Use of a single alloy conductor to form simultaneous ohmic contacts (SOC) to n- and p-type 4H-SiC. The single alloy conductor also is an effective diffusion barrier against gold (AU) and oxygen (O2) at high temperatures (e.g., up to 800° C.). The innovation may also provide an effective interconnecting metallization in a multi-level metallization device scheme.

Abstract: The disclosed subject matter relates to a reaction wheel system for controlling and stabilizing a satellite or other spacecraft. The reaction wheel system includes a reaction wheel rotor and a containment structure stator including a plurality of contactor assemblies for securing the reaction wheel rotor when not in rotation and for electromagnetically inducing substantially frictionless rotation of the reaction wheel rotor.

Abstract: A solid-state radiation detector includes a pattern of conductive metal on a zinc oxide substrate. The pattern provides an arrangement of interdigitated electrode fingers. The wide band gap substrate is sensitive to UV light, which can cause a conductivity change in the substrate. The electrode fingers are configured to sense a difference in substrate conductivity resulting from UV light. The detector has a fast response time, which enables it to detect Cherenkov light. The compact detector provides savings on size, weight, and required power. Thus, the solid-state detector can be used to replace photomultiplier tubes in Cherenkov detectors. The features of the novel detector allow for an improved system to detect and monitor UV radiation, especially during deep space missions.

Abstract: A heat transfer interface is provided for radio-frequency resonator cavity filters used in vacuum environments such as are encountered by spacecraft and satellites. The heat transfer interface may include a thermally conductive structure that encircles or partially encircles a tubular structure of the resonator cavity filter and heat transfer legs that extend from positions that are on opposite sides of the thermally conductive structure and at approximately the same distance from a support surface to the support surface. The heat transfer legs and the thermally conductive structure may be made from a material or materials having a thermal conductivity of 350 W/(m·K) or greater.

Abstract: An extended structure additive manufacturing device and method are provided. The device includes a movable material bonding component and a movement mechanism which enable the device to create parts outside the conventional additive manufacturing device print volumes defined by the device and its print-head. Methods of making parts involve creating a portion of a part and moving the extended structure additive manufacturing device relative to the part and printing a second portion of the part. Parts incapable of being formed using a conventional additive manufacturing device may be made using the extended structure additive manufacturing device and/or methods disclosed herein.

Abstract: Recycling devices for producing additive manufacturing filament from received materials including objects to be recycled, discarded objects, obsolete objects, and the like. A recycling device may include a material processing system an extrusion mechanism and a spooling assembly. The material processing system receives material, reduces the size of the received material via a material size reducer and actively pushes the material through at least a portion of the device. The extrusion mechanism produces filament from the material and the spooling assembly loads the filament onto a spool for later use. The spooling assembly may include detachable elements configured to interface with and supply filament to an additive manufacturing device. Depending on configuration, recycling devices may create filament from plastic, metal, in-situ material, or a combination thereof.

Abstract: An apparatus, method, and computer program that can learn a linear or non-linear transfer function are disclosed. In one embodiment, for example, a computer-implemented method may include creating a plurality of combinations for at least one input, and calculating an output for the plurality of combinations. The method may also include calculating an error based on the calculated output.

Abstract: A stacked optocoupler component, having a transmitter component with a transmitting area and a receiver component with a receiving area and a plate-shaped electrical isolator. The isolator is formed between the transmitter component and the receiver component, and the transmitter component and the receiver component and the isolator are arranged one on top of another in the form of a stack. The transmitter component and the receiver component are galvanically separated from one another but optically coupled to one another. The isolator is transparent for the emission wavelengths of the transmitter component and the centroidal axis of the transmitting area and the centroidal axis of the receiving area are substantially or precisely parallel to one another.

Abstract: A fiber composite component includes a composite including cured matrix material and a fiber material embedded therein. At least one partial area of the fiber composite component is provided with at least one thread, which undulates as it extends along a surface area of the composite, so that sections of the thread alternately run inside of the composite and outside of the composite. An adhesive arrangement for such fiber composite components is also disclosed. Finally, methods for manufacturing such a fiber composite component or for manufacturing such an adhesive arrangement are disclosed.

Abstract: A method for suppressing a parasite signal received with a useful signal by a network of elementary antennas of a payload of a satellite. The suppression method includes an analogue formation step for forming analog beams and a digital formation step for forming a digital beam. The analog formation step includes forming of an useful analog beam in which the parasite signal is attenuated with respect to the useful signal and of an auxiliary analog beam in which the useful signal is attenuated with respect to the parasite signal. The digital formation step includes forming of a digital beam in which the parasite signal has been suppressed, by combining the signals obtained by digitizing the auxiliary beam and the useful beam.

Abstract: A device (10) for the electric power supply of a load (11), includes at least two energy storage elements (13, 14), elements for determining the power needs of the load (11), elements (16, 17) for monitoring each energy storage element (13, 14), which are able to provide information about a maximum instantaneous power of each energy storage element (13, 14), a calculation body (19) for determining a maximum secured power according to the electromotive force (Ebat(t)) and the resistance (Rbat(t)) of the Thévenin model, a maximum specified current and a maximum specified voltage, and elements (Cbat(t), Csc(t)) for controlling each energy storage element (13, 14), the elements being adjusted over time according to the power needs of the load (11) and the maximum secured power of each energy storage element (13, 14).

Abstract: A spaceplane suitable for aeronautical flight comprising a body and a wing defining a lower airfoil surface in addition to attitude control means that comprise one or a plurality of shutters disposed under the lower airfoil surface of same and maneuverable between a stowed position and an inclined extended position for aerodynamic braking during the transition from a phase of space flight to a phase of aeronautical flight of the aircraft.

Abstract: A method for autonomous controlling of an aerial vehicle, wherein a flight operator commands the aerial vehicle, comprising the steps of: measuring flight and/or system data of the aerial vehicle; performing an evaluation of a flight condition of the aerial vehicle based on the measured data and based on at least one decision criterion; and, issuing at least one autonomous controlling command, if, as a result of the evaluation of the flight condition, the aerial vehicle is in danger.

Abstract: Described herein is a space based subsystem of a satellite, and methods for use therewith, for receiving an optical ISL beam from another satellite, and in dependence therein, producing a further optical ISL beam for transmission to a further satellite. Additionally, the subsystem can also produce RF service downlink beams for transmission to service terminals. The subsystem can include, inter alia, receiver optics, optical amplifiers, a WDM demultiplexer, beam splitters, a WDM multiplexer, and transmitter optics. In certain embodiments, because RF frequencies of a wavelength division multiplexed optical signal produced by the WDM multiplexer are within a same specified RF frequency range within which the satellite and the further satellite are configured to transmit RF service downlink beams, there is an elimination of any need for the satellite and further satellite to perform any frequency conversions when producing the RF service downlink beams in dependence on the optical ISL beams.

Abstract: A method and system for performing electrical tests on complex devices. The method comprises: a first stage that includes generating a model of the device in a digital electronic circuits description language based on stimuli transfer, preparing a stimulus vector and simulating the model with the stimulus vector for obtaining the continuity and insulation test program to be performed to the device; a second stage where the device is connected to a workbench formed by an electrical testing machine and a matrix switch via a connection interface; and a third stage where the test program on the device is executed. The system comprises the workbench and a computer system with software adapted to execute the method.

Abstract: First and second applications are executed in a red domain, and a third application is executed in a black domain, with a lower security level, and via which a ciphered communication tunnel passes between the first and second applications. The first application transmits to the second application a nominal sequence of packets ordered according to their respective sizes; said nominal sequence is intercepted by the third application which, when it wishes to transmit information to the red domain, modifies said nominal sequence by deleting at least one packet, each deleted packet being dependent on said information; on reception of a sequence of packets supposed to be the nominal sequence of packets, the second application checks whether at least one packet has been deleted; and, if such is the case, the second application retrieves said information from the size of each packet thus deleted.

Abstract: Described herein is a ground based subsystem for inclusion in an optical gateway and for use in transmitting an optical feeder uplink beam to a satellite. The subsystem can include a wavelength-division multiplexing (WDM) multiplexer configured to receive optical data signals from optical network(s) external to the ground based optical gateway, and configured to combine the optical data signals into a wavelength division multiplexed optical signal. The subsystem can also include an optical amplifier to amplify the wavelength division multiplexed optical signal, and transmitter optics to receive the amplified wavelength division multiplexed optical signal and transmit an optical feeder uplink beam to the satellite in dependence thereon. In certain embodiments, the ground based optical gateway does not perform any modulation or demodulation of the optical data signals received from the optical network(s) external to the ground based optical gateway before they are provided to the WDM multiplexer.