Abstract: A thermoacoustic engine is provided that uses acoustic energy to operate a piston in a double-acting action. The acoustic energy is amplified as a sound wave travels through the thermoacoustic engine. The amplified acoustic energy is extracted and converted into usable electrical energy.

Abstract: A spacecraft includes a 3-D closed truss structure including at least four coupling nodes and at least six strut elements, attached together by a plurality of joints, each coupling node including at least two legs, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes. Each coupling node is attached, at respective ones of the plurality of joints, with at least two strut elements. Each strut element is attached at a first end with a first leg of a first coupling node and is attached at a second end with a second leg of a second coupling node, the first leg being substantially longer than the second leg.

Abstract: A polyamide aerogel and method of making the same is disclosed. The aerogel includes para-substituted monomers without a cross-linking agent.

Abstract: A tunable QCL source that utilizes a full bandwidth of a broadband THz QCL, and produces a significantly large number of frequency channels, is provided. The tunable QCL source includes a grating router configured to receive a terahertz frequency from a tunable quantum cascade laser and generate a plurality of terahertz frequencies. The tunable QCL source also includes a waveguide controller configured to receive the plurality of terahertz frequencies from the grating router, and select a desired terahertz frequency from the plurality of terahertz frequencies to be outputted by a waveguide multiplexer.

Abstract: A constellation of non-geosynchronous satellites are in a common orbit. Each time one of the satellites is at a trigger location, a new rolling wave of handovers is started that includes performing handovers of a group of dependent spot beams between adjacent satellites in sequence for pairs of adjacent satellites in a single direction around the orbit.

Abstract: A system for calibrating a transmitting unit includes an arrangement of at least four transmitting units. A first transmitting unit has stored position data with respect to a setpoint position of the first transmitting unit. The first transmitting unit is designed to emit a first transmission signal to each of the three remaining transmitting units, each of which is designed to receive the first transmission signal and, thereafter, to return a first response signal to the first transmitting unit. The first transmitting unit is designed to determine its relative position data with respect to the three remaining transmitting units on the basis of the first response signals returned and to detect a deviation between the stored position data and the relative position data determined and to carry out a calibration of a transmission parameter of the first transmitting unit on the basis of the detected deviation.

Abstract: The invention concerns a microwave antenna module for use in an antenna system installed on board a space platform. The disclosed microwave antenna module includes a transmit/receive module, which comprises: a first package and a second package, that are hermetically sealed to one another and that are multilayer ceramic substrate packages; and an interposer connector, that is interposed between the first and second packages and comprises a body and connection means provided in the body. First and second electronic circuitries are connected to the connection means of the interposer connector for routing microwave, control and power signals through the connection means. The first electronic circuitry includes a directional coupler in stripline-coplanar configuration.

Abstract: A method for producing a fiber composite laminate, including the steps of applying pressure and/or heat to a first preform, which has one or more dry fiber layers and a thermoplastic elastomer, such that the thermoplastic portion of the thermoplastic elastomer completely impregnates the dry fiber layers of the first preform in at least one first region and only partially impregnates the dry fiber layers in at least one second region and, in a thermosetting polymer matrix, impregnating and curing the fiber layers of the second region of the first preform that are still dry and have not been impregnated with the thermoplastic portion of the thermoplastic elastomer.

Abstract: A method for the common representation of safety-critical and non-safety-critical information on a display unit of a vehicle. The method includes receiving non-safety-critical information and producing at least one graphic presentation of the non-safety-critical information. The method also includes receiving safety-critical information and producing at least one graphic presentation of the safety-critical information. In addition, the method includes representing the presentations of safety-critical and non-safety-critical information on the display unit, the representation having at least two representation planes. The non-safety-critical information is represented on a rear, in the direction of view of the observer, plane of the at least two representation planes, and the safety-critical information is represented on a front representation plane.

Abstract: A launch vehicle includes an upper stage and an integral fairing. In a launch configuration, the integral fairing is configured to enclose, between an aft portion and a forward portion, one or more payloads. The integral fairing includes a mechanical attachment with the upper stage proximal to the aft portion, and a nose cap proximal to the forward portion and a passive venting arrangement that equalizes pressures internal and external to the integral fairing. The integral fairing is configured to permit deployment of at least one payload, while avoiding: (i) separation of the integral fairing into two or more parts, (ii) separation of the integral fairing from the upper stage, and (iii) articulation of the mechanical attachment. The upper stage may provide single stage to orbit capability.

Abstract: A method for determining the relative angular direction ? between a target and a transmitter. A generation of one or more light beams at the transmitter comprises diffracting broadband light in such a way that different optical frequency wavelengths are diffracted differently and a relative angular direction ? is detected by reading the optical frequency wavelength. A system is provided for determining the relative angular direction between a target and a transmitter and a system is provided for determining a relative position between a target and a transmitter in an area, wherein relative position is defined by the parameters: relative angular direction (?1, ?2), and distance.

Abstract: A communication platform (e.g., a flexible satellite) includes electrical to optical converters configured to convert input electrical signals to input optical signals, an optical switching network connected to the electrical to optical converters that choose which input optical signals to route to which output beams, tunable optical filters (connected to the switching network) that are configured to select programmable sub-bands of the input optical signals to create output optical signals, and optical to electrical converters (connected to the tunable optical filters) that are configured to convert the output optical signals to output electrical signals for the output beams.

Abstract: A receiver unit having an optically operated voltage source, the voltage source including a first stack having an upper side and an underside and being formed on an upper side of a non-Si substrate based on III-V semiconductor layers arranged in the shape of a stack, and having a second electrical terminal contact on the upper side of the first stack and a first electrical terminal contact on an underside of the non-Si substrate, a voltage generated with the aid of the incidence of light onto the upper side of the first stack being present between the two terminal contacts, and including a second stack having a MOS transistor structure having III-V semiconductor layers and including a control terminal and a drain terminal and a source terminal. The MOS transistor structure being designed as a depletion field effect transistor.

Abstract: A photovoltaic generator deployable for a satellite stabilized on three axes. The photovoltaic generator includes an assembly of planar panels articulated with respect to each other, and an attachment arm to the structure of the body of the satellite. In a first or launch position of the photovoltaic generator, the planar panels are folded one over the other. In a second or deployed position of the photovoltaic generator, the planar panels are fully deployed with at least a part of the planar panels being photovoltaic panels. At least one planar panel consists of a thermal radiator, with the radiative face thereof being orientated to be opposite the face of the photovoltaic panels carrying the photovoltaic sensors when the photovoltaic generator is in the deployed position. This radiative face is termed the “shade” face, and the face opposite the panel shaped radiator is termed the “sun” face.

Abstract: A carrier system for carrying out interception maneuvers of a loadbearing paraglider which has a glider having a trailing edge for carrying out the maneuver with at least one interception line is fixed to said edge includes at least one carried load unit, which is connected to the carrier system via a first, short load carrier belt and a second, longer load carrier belt. A carried load connected to the carried load unit is carried by way of the first, short load carrier belt. The trailing edge is adjusted to carry out the maneuver by the gravitational force of the carried load, in that the first, short load carrier belt is separated and the carried load is carried by way of the longer, second load carrier belt.

Abstract: This relates to changes in wing profiles. In order to make available an aerodynamic structure that can be variably adjusted and changed with respect to the wing profile, it is provided that an aerodynamic structure for a wing or rudder arrangement of an aircraft comprises a support structure and an outer skin. The support structure comprises a fixed spar in the longitudinal direction, which extends from a root area to an outer end area. The support structure also comprises several adaptive framework segments in the transverse direction, which each consist of a plurality of strung together triangular compartments, which are formed by fixed-length guide elements and adjustable-length guide elements The framework segments are joined to the fixed spar. At least one side of a portion of the triangular compartments comprises one of the adjustable guide elements, so that the shape of the framework segments can be adjusted.

Abstract: The present invention relates to a system for contactless induction of high-frequency vibrations in a volume of molten metal during the manufacturing of a metal component or a metal matrix composite component. The system includes a moveably arranged electromagnetic primary coil, adjustment means for adjusting the position of the primary coil, and a control unit for controlling the position of the primary coil to a predefined distance above, but not in contact with, an upper free surface of the molten metal. The molten metal may be contained in a foundry crucible during manufacturing. The system can be used as an additive manufacturing system, with the primary coil arranged above the melt pool. A secondary low-frequency electromagnetic coil may be arranged around and at a distance from the molten metal to induce flow and/or vibrations in the molten metal.

Abstract: An infrared LED having a monolithic and stacked structure, having an n-doped base substrate, which includes GaAs, a lower cladding layer, an active layer for generating infrared radiation, an upper cladding layer, a current distribution layer and an upper contact layer. The layers being preferably disposed in the specified order. A first tunnel diode is disposed between the upper cladding layer and the current distribution layer, and the current distribution layer predominantly including an n-doped, Ga-containing layer having a Ga content>1%.

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 telecommunications satellite stabilized on three axes includes a set of dissipative equipment constituting a payload of the satellite. The satellite includes support data transmission antennas and is substantially parallelepipedal in shape with the panels forming two opposite faces, east and west faces. The panels form two additional opposite faces, north and south faces, and include radiator surfaces on their external faces. The radiator surfaces are configured to cool the electronic equipment of the satellite. The equipment installed on the north and south panels dissipate thermal power corresponding to less than 25% of the total dissipated power.