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

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: 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: 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: 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: 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.

Abstract: A compartment for a space vehicle includes a pressurized structure having a structural wall, the structural wall having interior surfaces facing an interior of the compartment and exterior surfaces exposed to an external environment. An internal mounting structure for mounting a component is provided within the compartment, and mounting features support the internal mounting structure from the pressurized structure. The internal mounting structure is spaced away from the interior surfaces of the pressurized structure, and a thermal fluid is provided in the pressurized structure. The thermal fluid enables convective heat transfer between the component mounted on the internal mounting structure and the interior surfaces of the pressurized structure.

Abstract: This disclosure provides systems, methods and apparatus for a flexible radio frequency (RF) converter. In one aspect, a subsystem of a spacecraft can include a flexible RF converter having a printed circuit board (PCB), and a synthesizer and controller disposed on the PCB. The PCB can be placed within a chassis. The controller can communicate with the synthesizer to adjust a frequency of a synthesizer signal generated by the synthesizer, which is used to adjust a frequency of an input RF signal.

Abstract: A double-fed oscillating linear alternator is provided that includes two concentric Halbach type arrays, one stationary and one movable, that do not require magnets or iron laminations to create a strong magnetic field between the two arrays where the movable array oscillates in a linear motion with respect to the stationary array. The two arrays are manufactured from magnet-less and iron-less conductive material using additive manufacturing techniques.

Abstract: Various automation units for a premises include a sensor, at least two resolvers, and a plurality of models of the data of the sensor. Each resolver has its associated models which define how the resolver uses the data of the sensor. The various resolvers are an alarm resolver, a presence resolver, a climate resolver and a voice resolver. Other automation units are cognitive or proactive, and include a data base to store at least recorded events per controlled equipment, an event analyzer to analyze recorded events to find patterns of activation of the equipment, and either a cognitive module to modify the associated scenario of a piece of equipment if the patterns do not match the scenario or a proactive module to create a new scenario for a piece of equipment based on the analysis.

Abstract: A light receiving unit having a first energy source made up of two sub sources. A first terminal contact is formed at the upper face of the first sub source and a second terminal contact is formed at the lower face of the second sub source. The sub source has at least one semiconductor diode that has an absorption edge adapted to a first wavelength of light and the second semiconductor diode has an absorption edge adapted to a second wavelength of light which is different from the first wavelength of light, such that the first sub source generates electric voltage upon being irradiated with the first wavelength of light and the second sub source generates electric voltage upon being irradiated with the second wavelength of light.