Abstract: An electric power supply system for a Hall effect electric thruster. The Hall effect electric thruster includes an anode, a cathode, a heater for the cathode and an igniter. The electric power supply system includes a first power supply source to power the anode, a second power supply source to power the heater and a power supply unit to electrically supply the igniter. The power supply unit includes a third power supply source and a passive electric circuit. The third power supply source powers the passive electric circuit and is configured to generate a voltage in the form of at least one pulse.

Abstract: The flexible sheet-like material comprises a textile layer, which is coated at least on one side with a functional layer which is permeable to gas but impermeable to the matrix material, acting as a barrier layer for the matrix material, and is produced by coating the textile layer directly with a foam or a paste.

Abstract: A service satellite for providing station keeping services to a host satellite is disclosed. The service satellite may have a body, and a gripping mechanism attached to the body. The gripping mechanism may be adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring may form an interconnected unit having a combined center of mass. The service satellite may have at least two thrusters and at least one controller. The at least one controller may maintain the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters avoid passing through the combined center of mass, and are each offset from the combined center of mass.

Abstract: Gas migration rate(s) are determined using gas measurements from gas migration measurement devices. In response to the gas migration rate increasing, at least one of: air ionization measurements are collected from air ionization measurement device(s), and meteorological measurements collected from air temperature sensor(s), relative humidity sensor(s), and air pressure sensor(s). A latent heat energy release rate is determined using at least two of: the air ionization measurements, the meteorological measurements, and a numerical assimilation model. In response to the latent heat energy release rate increasing, at least one transient outgoing long wave radiation (OLR) anomaly is looked for using atmospheric measurements. In response to observing the transient OLR, at least one ionospheric anomaly is looked for using ionosphere measurements. In response to observing the at least one ionospheric anomaly, a forecast alert that an earthquake is likely to occur within one to four days is generated.

Abstract: Described are energy storage devices employing a gas storage structure, which can accommodate or store gas evolved from the energy storage device. The energy storage device comprises an electrochemical cell with electrodes comprising metal-containing compositions, like metal oxides, metal nitrides, or metal hydrides, and a solid state electrolyte.

Abstract: A device for determining a region of impact of an aircraft on the surface of the Earth in the event of an emergency is configured to compare weather forecasts from the past with the weather conditions that are actually occurring and to determine therefrom an uncertainty of the weather forecasts using statistical means. This uncertainty of the weather forecasts is used in addition to position data and state information of the aircraft in order to determine a probable region of impact of the aircraft.

Abstract: Innovative new systems and method of operating the systems, wherein the system comprises an airborne platform comprising an unmanned balloon comprising a gas enclosure; a geographic locator or tracking system configured to determine geographical coordinates of the unmanned balloon; a payload comprising a transceiver, wherein the transceiver is capable of communicating with communication devices that are separate from the unmanned balloon; first and second flight-termination devices each configured to cause termination of a flight of the unmanned balloon; and at least two power sources each configured to provide power to at least one of the first and second flight-termination devices.

Abstract: A method of fabricating parts out of metallic, intermetallic, ceramic, ceramic matrix composite, or metal matrix composite material with discontinuous reinforcement, includes melting or sintering powder particles by means of a high-energy beam. The powder used is a single powder of particles that present sphericity lying in the range 0.8 to 1.0 and of form factor lying in the range 1 to ?2, each powder particle presenting substantially identical mean composition, and the grain size distribution of the particles of the powder is narrowed around the mean diameter value d50% in such a manner that: (d90%?d50%)/d50%?0.66; and (d50%?d10%)/d50%?0.33; with a “span”: (d90%?d10%)/d50%?1.00.

Abstract: A method for detecting surface impurities on a surface of a component by X-ray fluorescence analysis uses a hand spectroscope for application to the surface of a component. The hand spectroscope comprises an X-ray source, a fluorescent radiation detector, an analyzer and a display. The method comprises irradiating the surface of the component with X-rays using the X-ray source; detecting fluorescent radiation, which is emitted by the surface of the component as a result of the irradiation with the X-rays, using the fluorescent radiation detector; measuring a radiation spectrum of the detected fluorescent radiation; generating an evaluation result by analyzing the measured radiation spectrum using the analyzer, the evaluation result comprising a quantitative measure of the surface impurity of the surface due to predetermined characteristic substances; and outputting the generated evaluation result on the display.

Abstract: A manufacturing system including catalog database for retaining a plurality of three-dimensional content for use to at least one of create a produced object and repair an existing object with at least one additive manufacturing process, one or more user interfaces to access the catalog database at least one of simultaneously and at different times, a communication infrastructure to provide for real-time communication between the catalog database and the one or more user interfaces, and a manufacturing system comprising at least one user interface to apply the at least one additive manufacturing process to at least one of create the produced object and to repair the existing object. Methods are also disclosed.

Abstract: Described herein is a satellite communications system that includes: two or more satellites using laser communications, and a communications relay aircraft adapted for flying at altitudes above clouds. The communications relay aircraft includes: a laser communications module to communicate with the satellite using laser communication and a Radio Frequency (RF) communications module to communicate with RF equipment at or near ground level using cloud-penetrating RF communications. The RF communications module is configured to take data received as laser communication and generate a corresponding RF transmission containing the data. The laser communications module is configured to take data received as RF communication and to generate a corresponding laser transmission containing the data.

Abstract: The present invention relates to attitude control and, in particular, to control of the attitude of a space platform. The space platform may take the form of or be part of a satellite and/or a spacecraft. An aspect of the present invention concerns the use, in an attitude control system, of several control moment gyroscopes with limited gimbal revolutions. Another aspect of the present invention concerns an improved logic for controlling a control moment gyroscope assembly of an attitude control system.

Abstract: In order to enhance sliding movement and reconfiguration of vehicle seats while using a simple construction, a seat fastening device is provided for fastening vehicle seats in a vehicle. The seat fastening device comprises a seat rail with a T-shaped profile portion and a carriage enclosing an upper part of the T-shaped profile portion. The carriage includes a seat fixation device for fixing a vehicle seat, wherein the carriage includes a clamp arrangement for clamping the carriage onto the T-shaped profile portion. The carriage has a base body and first and second bracket clamps so that the carriage has a C-shaped channel section receiving the T-shaped profile portion. The height of the C-shaped channel section can be adjusted by at least one screw in order to clamp the carriage onto the T-shaped profile portion.

Abstract: A vehicle ramp assembly as disclosed includes a ramp for supporting one or more wheels of a vehicle and providing a bridge over stepped terrain on which the wheels of the vehicle can travel. The ramp can move among a first configuration where the ramp is stowed in the ramp assembly, a second configuration where the ramp extends from the ramp assembly, and a third configuration where the ramp is supports the vehicle wheels as it travels over stepped terrain. A drive mechanism for the ramp, and a carriage coupling the drive mechanism to the ramp enable rotation of the ramp. A secondary actuation system enables linear movement of the carriage along the ramp. A control module can drive the carriage around a curvilinear loop, such that the ramp is driven in a cycle from the first configuration to the second configuration to the third configuration to the first configuration.

Abstract: A menu-type design method based on optimized information fusion applied to a GEO satellite control system is provided, which includes: configuring four long-life inertial attitude sensor gyroscopes for a long-life GEO satellite control system; configuring sensors capable of measuring three-axis attitude according to a menu-type design requirement on hardware, where the long-life inertial attitude sensor gyroscopes and the sensors capable of measuring three-axis attitude are combined to form three types of Kalman filters; autonomously sorting, by the satellite-borne computer application software, the Kalman filters; and in a case where an FDIR module detects a fault, autonomously generating, by the FDIR module, an alarm corresponding to the fault, and autonomously performing, by a currently selected Kalman filter, reduced-order filtering, and in a case where the fault is not eliminated within a set time period, issuing, by the FDIR module, a macro instruction sequence to perform autonomous reorganization.

Abstract: A method and system for separating and releasing component parts of a payload of a floating platform in response to a high collision probability is disclosed. The method includes, determining if an in-flight aircraft is within at least a safety zone associated with a floating platform, wherein the floating platform comprises releasably-coupled component parts; and activating, responsive to a determination that the in-flight aircraft is within at least the safety zone, a release mechanism, wherein the release mechanism is configured to uncouple the component parts.

Abstract: A device for providing power or thrust to an aerospace vehicle with a control system providing two different mechanical power outputs deriving their power from one common mechanical power source unit includes: a common mechanical power source unit an adjustable mechanical load unit driven by the common mechanical power source unit, an electrical machine unit with a mechanical power interface connected to the common mechanical power source unit and configured to receive mechanical power from the common mechanical power source unit to provide electrical power at an electrical power interface, and a control system configured to receive a mechanical power or thrust demand and standard air data from the aerospace vehicle. Only based on the mechanical power or thrust demand and standard air data, the control system is configured to control the device to provide mechanical power or thrust as well as electrical power to the aerospace vehicle.

Abstract: An apparatus and method are described for processing a global navigation satellite system (GNSS) signal, the GNSS comprising multiple satellites, wherein each satellite transmits a respective navigation signal containing a spreading code. The method comprises receiving an incoming signal at a receiver, wherein the incoming signal may contain navigation signals from one or more satellites; encrypting the incoming signal at the receiver using a homomorphic encryption scheme to form an encrypted signal; and transmitting the encrypted signal from the receiver to a remote server.

Abstract: A method for operating an unmanned aerial vehicle, which is flight-controlled by a flight control unit to follow a given trajectory, includes an optimization of the trajectory based on a simulation model of the unmanned aerial vehicle and a communication link to a ground station to form a trajectory along which a certain connection quality to the ground station can be maintained.

Abstract: This invention is directed to improving communication among people at remote locations, accomplished at low cost, by communication schemes involving “portal” structures, “channels” and “phonos.” The portal structures are mobile and easily deployed to the remote locations, for quick assembly and use, creating an audio-visual immersive communication experience for its users. A portal network architecture includes a plurality of portals located in different remote locations, configured to provide identical spaces that facilitate audio-video, immersive conferencing among users at the various portal sites. The portal interiors include favorable lighting and camera configurations to facilitate display of life-size, realistic, and planar images of the users while maintaining eye contact between them.