Abstract: A method for operating an, at least temporarily, unmanned aircraft or spacecraft wherein a flight procedure of the aircraft or spacecraft is carried out in controlled airspace using a previously cleared flight plan, wherein a C2 link is at least temporarily unavailable, and wherein at least one sensor device of the aircraft or spacecraft identifies a dangerous and/or emergency situation which makes it necessary to deviate from the cleared flight plan. To have available a method which makes it possible for an at least temporarily unmanned aircraft or spacecraft to react independently to particular dangerous and/or emergency situations and to avoid damaging events, a control device of the aircraft or spacecraft independently uses a wireless data link to a supervisory authority in order to agree to a changed flight plan containing at least one change.

Abstract: Described are solid-state energy storage devices and methods of making solid-state energy storage devices in which components of the batteries are truly solid-state and do not comprise a gel. Useful electrodes include metals and metal oxides, and useful electrolytes include amorphous ceramic thin film electrolytes that permit conduction or migration of ions across the electrolyte. Disclosed methods of making solid-state energy storage devices include multi-stage deposition processes, in which an electrode is deposited in a first stage and an electrolyte is deposited in a second stage.

Abstract: Gas migration rate(s) are determined using gas measurements from gas migration measurement devices. In response to the gas migration rate increasing at greater than a first rate: air ionization measurements are collected from: remote sensing air ionization measurement device(s), meteorological measurements collected from air temperature sensor(s) and relative humidity 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 greater than a second rate, transient OLR anomaly are looked for using atmospheric measurements. In response to observing the transient OLR, ionospheric anomal(ies) are looked for using ionosphere measurements collected over a fourth period of time.

Abstract: A motor actuating apparatus includes three phase connections for three motor phase connections, a high-connection for a supply voltage and a low-connection for a reference potential of the supply voltage, three bridge branches having a series connection of a high-switch and a low-switch and a control device for actuating the switches of the bridge branches. The high-switches are connected to the high-connection and the low-switches are connected to the low-connection. Each of the three phase connections is connected to exactly one of the three bridge branches between the high-switch and the low-switch. The control device is adapted for actuating the switches of the bridge branches such that during a first time period a first phase connection is switched to passive and the second phase connection and third phase connection are alternatingly connected to the high-connection and the low-connection in a predeterminable duty cycle if the supply voltage is applied.

Abstract: An optical voltage source and decoupling device is provided, wherein the optical voltage source has a number N of series-connected semiconductor diodes, each having a p-n junction, the semiconductor diodes are monolithically integrated and together form a first stack with an upper side and an underside, and the number N of the semiconductor diodes of the first stack is greater than or equal to two, the decoupling device has a further semiconductor diode. The further semiconductor diode has a pin junction and, the further semiconductor diode is anti-serially connected with the semiconductor diodes of the first stack. An underside of the further semiconductor diode is materially connected with the upper side of the first stack and the further semiconductor diode forms a total stack together with the first stack.

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 directional coupler (100) comprises two hollow bodies (200, 201) forming two waveguide portions. Each hollow body has an open end arranged at a first side (10) of the hollow body and another open end arranged at a second side (20) of the hollow body in opposite to the first side in a longitudinal direction (30) of the hollow body. The hollow body has a first cross section perpendicular to the longitudinal direction. A second cross section along the longitudinal direction defines a first plane of propagation of the electric field. The two waveguide portions have a common wall along the longitudinal direction (30) forming a septum (400) between the two waveguide portions on a second plane orthogonal to the first plane. The septum has an aperture (410) for coupling the two waveguide portions. The aperture has a shape comprising a part (420) slanted with respect to the longitudinal direction.

Abstract: This disclosure relates to a wheel assembly (1) comprising a wheel, the wheel having a hub and a rim concentrically mounted to the hub, a plurality of deformable chambers (6) disposed outwardly of the rim, each chamber extending about a discreet portion of the wheel and containing a transition substance (15), and an actuator (14) configured to transform the transition substance (15) within each chamber (6) between a fluid state in which the deformable chamber (6) can deform into a conformal state as the wheel encounters an obstacle during use, and a rigid state in which the transition substance is rigidified to maintain the deformable chamber (6) in said conformal state to provide increased purchase on said obstacle.

Abstract: A perforated metal honeycomb structure is described. The perforated metal honeycomb structure may include a metal honeycomb structure having a plurality of laser-drilled holes wherein at least some of the plurality of holes are non-uniform in second, shape, and/or spacing between holes. In another embodiment, the perforated metal honeycomb structure may include an array of intercellular holes between hexagonal cells in the honeycomb structure. The array of intercellular holes may include at least a first hole and a second wherein the first and second holes are different from each other.

Abstract: This disclosure relates to a wheel assembly (1) comprising a wheel, a deformable chamber (6) containing a transition substance (15) comprising jamming particles and an interstitial gas, and an actuator (14) configured to transform the transition substance (15) between a fluid state in which the deformable chamber (6) can deform into a conformal state as the wheel encounters an obstacle during use, and a rigid state by evacuation of the interstitial gas in which the transition substance is rigidified to maintain the deformable chamber (6) in said conformal state to provide increased purchase on said obstacle.

Abstract: A system and method of analyzing an engine model is disclosed. The system and method include performing a Dynamic Systems Analysis on the engine model that includes modifying a transient allowance of the engine model to determine an optimal balance between performance and operability and assessing the conservatism level of the engine model.

Abstract: An engineered matrix is provided to blunt and self-heal matrix cracks to reduce oxygen ingress into a fiber reinforced composite.

Abstract: Portable and collapsible enclosures for use in participating in online meetings, such as educational or business meetings are disclosed. In one illustrative embodiment, the enclosure, when erected, may generally be formed as a rectangular cube with four sides, a top and a bottom. Three sides may be completely covered by textile panels, with the fourth side having a large opening. The top side may be closed by a textile material connected to the top sides of the four side panels and extending therebetween. The enclosure may be sized to allow a participant to sit or stand therein, and the interior with the participant viewed using a camera for online meetings. The textile panels may be colored to allow a contrast for better visualization of the participant. In other embodiments, it may be constructed to allow for virtual projection of desired background images around the participant. Methods and processes for using the enclosures are also disclosed.

Abstract: A first spacecraft and a second spacecraft are configured to be disposed together, in a launch configuration, for launch by a single launch vehicle. In the launch configuration, the first spacecraft is mechanically coupled with a primary payload adapter of the launch vehicle, and the second spacecraft is mechanically coupled with the first spacecraft by way of an inter-spacecraft coupling arrangement. The spacecraft are configured to be deployed, following injection into a first orbit by the launch vehicle, by separating the first spacecraft from the primary payload adapter while the second spacecraft is mechanically coupled with the first spacecraft. A first onboard propulsion subsystem of the first spacecraft includes one or more thrusters configured to execute an orbit transfer maneuver from the first orbit to a second orbit. A propellant line arrangement detachably couples the first onboard propulsion subsystem with a second propellant storage arrangement on the second spacecraft.

Abstract: A satellite communication system comprises one or more non-geostationary satellites. Each satellite is configured to provide a plurality of spot beams. The polarizations of the spot beams are laid out on each satellite so that terminals have a constant polarization as the field of regard traverses the terminal location.

Abstract: Aerogels, aerogel composites and methods of making the same are discussed. One example method can include the act of creating a boehmite colloid and adding a hydrolyzed silicon precursor to form a sol. A reinforcement can be infused with the sol and dried to form an aerogel composite. Such a method can also include the acts of performing one or more solvent exchanges and subjecting the gel composite to supercritical drying. Additionally, such a method can include the act of heat treating the aerogel composite. The aerogel composite can be used in high temperature, flexible seals capable of withstanding temperatures, pressures, and compression levels associated with aerodynamic heating generated during flight and in aerospace applications.

Abstract: A product display merchandiser comprising a tray, a spring biased pusher slidable within the tray, and a visual indicator comprising at least one light activated by a switch, the switch configured to be actuated when the pusher is within a predetermined portion of the tray.

Abstract: Space system comprising a structure formed by structure components, an on-board equipment carried by the structure, and a passive device designed to facilitate demise of the space system during re-entry into the Earth's atmosphere. The passive device comprises connecting members designed to stably connect the structure components. The connecting members comprise at least a portion made of a primer material with characteristics such as to decay at re-entry altitudes higher than those at which the current connecting members melt so as to make unstable the connection created by the connecting members to such an extent as to early triggering demise of the structure of the space system during re-entry into the Earth's atmosphere.

Abstract: The invention relates to an interconnection network for forward error correction encoders and decoders, including N input terminals, N output terminals, and M stages. Each stage includes switching elements having input pins and output pins. The input pins of the switching elements of the first stage are connected to the input terminals, and the output pins of the switching elements of the last stage are connected to the output terminals. The input and output pins of the switching elements of immediately successive stages are connected in a hardwired fashion so as to form a plurality of interconnection sub-networks for routing respective input values from respective output pins of the switching elements of the first stage to respective input pins of the switching elements of the last stage.

Abstract: The present invention relates to a liquid crystal compound having a structure as shown by formula I, wherein R is selected from H and alkyl or alkoxy containing 1-12 carbon atoms in which one or more H are unsubstituted or substituted with halogens; A1, A2 and A3 are each independently selected from: a single bond, 1,4-cyclohexylene, 1,4-phenylene, wherein hydrogen in 1,4-phenylene may be each independently substituted with one or more halogens; and Z1 and Z2 are each independently selected from a single bond or —(CH2)2—. The compound of the invention has the characteristics of low rotational viscosity, large dielectric anisotropy, good mutual solubility and stability. The driving voltage of a device can be remarkably reduced after the compound is added to a composition. Thus, the compound of the invention has prosperous applications in LCD industry.