Abstract: Systems, methods, and devices for integrated circuit power management. A mode of a power management state is entered, from the power management state, in response to an entry condition of the mode. A device that is otherwise powered off in the power management state is powered on in the mode of the power management state. In some implementations, the device includes a communications path between a second device and a third device. In some implementations, the device is in a power domain that is powered off in the power management state. In some implementations, the power domain is powered off in the mode. In some implementations, the device is powered on in the mode via a power rail that is specific to the mode. In some implementations, the entry condition of the mode includes an amount of data stored for display in a display buffer falling below a threshold amount.

Abstract: The present disclosure provides an apparatus comprising a wire having a first end and a second end opposite the first end. A first portion of the wire including the first end comprises a malleable region that is configured to remain deformed after bending, and a second portion of the wire including the second end comprises a superelastic region that is configured to return to a straight configuration after bending.

Abstract: A hybrid aircraft power plant includes an air mover for propelling an aircraft, a gas turbine engine operable to drive the air mover, a bifurcated exhaust duct conveying combustion gas from the gas turbine engine, and an electric motor mounted to the exhaust duct and operable to drive the air mover. The turbine engine includes a turbine extracting energy from an annular stream of the combustion gas and being rotatable about a rotation axis. The exhaust duct includes a first branch conveying a first portion of the combustion gas toward a first direction away from a rotation axis of the turbine, and a second branch conveying a second portion of the combustion gas toward a second direction away from the rotation axis.

Abstract: Deployable structures, methods and apparatus for deployment of deployable structures, and associated manufacturing methods. Such deployable structures suitably comprise components for space structures, such supports for solar arrays, antennas or other similar systems. The deployable structure comprises a lattice element arrangeable in a stowed configuration and a deployed configuration. The lattice element comprises a pre-stressed strip arranged in a clockwise helix, a pre-stressed strip arranged in an anticlockwise helix, and a plurality of fasteners for rotatably coupling the strips to one another at a plurality of positions distributed along the length of the strips. The fasteners are provided at unequal spacings along the length of the strips such that on deployment the lattice element bends to a curved deployed configuration.

Abstract: Devices and methods for cache prefetching are provided. A device is provided which comprises a quality of service (QOS) component having first assigned registers used to store data to execute a program, a plurality of non-QOS components having second assigned registers used to store data to execute the program and a power management controller, in communication with the QOS component and the non-QOS components. The power management controller is configured to issue fences for the non-QOS components when it is determined that one or more of the non-QOS components are idle, issue a fence for the QOS component when the fences for the non-QOS components are completed and enter a reduced power state when the fences for the non-QOS components and the fence for the QOS component are completed.

Abstract: A spreading apparatus for use with fibre-reinforced composite tapes, and related methods are disclosed. The spreading apparatus comprises an input side to receive an incoming tape to be spread, and an output side from which tape is delivered after spreading. The apparatus further comprises a tape heater (150, 250, 650) to in use apply heat to a tape; and a tape spreader (100, 1, 200, 600) to in use to apply contact pressure to the heated tape to thereby spread the tape.

Abstract: An aircraft system is provided that includes an open propulsor rotor, a gas turbine engine, an electric machine and a drivetrain. The gas turbine engine includes a first rotating assembly, a compressor section, a combustor section, a turbine section and a flowpath extending through the compressor section, the combustor section and the turbine section. The first rotating assembly is coupled to and is configured to drive rotation of the open propulsor rotor. The first rotating assembly includes a first turbine rotor in the turbine section. The electric machine is outside of the gas turbine engine. The electric machine includes an electric machine rotor. The drivetrain couples the electric machine rotor to the first rotating assembly.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a housing, a rotor and a system. The rotor is next to the housing. The system includes a mechanical load, a belt drive, a cradle, a slide and an adjustment link. The mechanical load is operatively coupled to the rotor through the belt drive. The mechanical load is fixed to the cradle. The cradle includes a track and extends laterally between a first side and a second side. The cradle is coupled to the housing through the adjustment link at the first side. The cradle is pivotally coupled to the housing at the second side. The slide is connected to the housing. The slide is mated with and configured to move along the track. The adjustment link is configured to change a distance between the housing and the cradle to adjust a tension of the belt drive.

Abstract: An aircraft system is provided that includes a propulsor rotor, a geartrain, a thermal engine, a drivetrain and an electric machine. The geartrain includes a power output, a first power input and a second power input. The power output is coupled to the propulsor rotor. The thermal engine is configured to drive rotation of the propulsor rotor through the geartrain. The thermal engine is coupled to the first power input. The drivetrain includes a first driveshaft and a second driveshaft. The first driveshaft is coupled to and between the second power input and the second driveshaft. The second driveshaft is angularly offset from the first driveshaft. The electric machine is configured to drive rotation of the propulsor rotor through the drivetrain and the geartrain. The second driveshaft is coupled to and between the first driveshaft and the electric machine.

Abstract: The present disclosure relates to deployable structures, to methods and apparatus for deployment of deployable structures, and to associated manufacturing methods. Such deployable structures suitably comprise components for space structures, such supports for solar arrays, antennas or other similar systems. The deployable structure (500) comprises a first lattice (514) arrangeable in a stowed configuration and a deployed configuration. The deployable structure also comprises a second lattice (516) arrangeable in a stowed configuration and a deployed configuration, wherein with the lattices arranged in the stowed configuration the second lattice (516) nests in the first lattice (514).

Abstract: An aircraft engine comprises a rotor, an engine case having first and second mounting brackets projecting from an exterior surface thereof, an auxiliary engine system. The system includes an electric machine, a belt drive operatively coupled to the rotor, and a gearbox operatively coupled between the belt drive and the electric machine. The gearbox has a gearbox case with a cradle integrated thereto. The gearbox case and the cradle forms a monolithic body. The monolithic body is pivotally mounted to the first and second mounting brackets. A link is provided between the engine case and the monolithic body. A length of the link is adjustable to adjust a tension of the belt drive by setting an angular position of the monolithic body relative to the engine case.

Abstract: The gas turbine engine can have an engine core; a core output shaft drivable by the engine core; a power output shaft; an auxiliary power shaft; and a reduction gearbox having gears, the gears drivingly connecting the core output shaft to the auxiliary power shaft. The gears can include an epicyclic gearing drivingly connecting the core output shaft and the auxiliary power shaft to the power output shaft. The gas turbine engine can further have a second auxiliary power shaft interconnected to the auxiliary power shaft, the power output shaft, and the core output shaft by the gears.

Abstract: Systems, methods, and other embodiments associated with indicating physical progress of a clinician through patient locations are described. In one embodiment, a method includes accessing a workflow of locations of patients within a clinical care environment that a clinician is to visit on a schedule. The method includes sensing that the clinician is at a current location within the clinical care environment using a location sensor carried by the clinician. The method includes detecting that the current location corresponds to one of the locations in the workflow. The method includes, in response to the detection, generating in a display an indication of physical progress of the clinician through the workflow as of the current location.

Abstract: A method for changing the color and texture of ceramic roofing tiles, including the steps of identifying a damaged tile to be replaced, cleaning the damaged tile, optically measuring the damaged tile to yield a color determination, and selecting a replacement tile of the same shape and general color, immersing the replacement tile in a quantity of acid, removing the tile from the acid after a first predetermined length of time has passed to yield an acid-treated replacement tile, rinsing the acid-treated replacement tile to remove remaining acid, measuring the color of the acid-treated replacement tile, and washing the acid-treated replacement tile.

Abstract: The gas turbine engine can have an engine core; a core output shaft drivable by the engine core; a power output shaft; an auxiliary power shaft; and a reduction gearbox having gears, the gears drivingly connecting the core output shaft to the auxiliary power shaft. The gears can include an epicyclic gearing drivingly connecting the core output shaft and the auxiliary power shaft to the power output shaft. The gas turbine engine can further have a second auxiliary power shaft interconnected to the auxiliary power shaft, the power output shaft, and the core output shaft by the gears.

Abstract: Systems and methods for employing virtual environmental augmentation in clinical care environments to enhance a clinician's in-the-moment knowledge, leverage past experiences of the clinician and others, and improve the quality of patient care are provided. Such virtual environmental augmentation may align with prior-established, evidence-based clinical processes and enhance the clinician's in-the-moment knowledge by extracting relevant data from one or more clinical sources and presenting a virtual representation of at least a portion of the extracted data (or a summary, exemplification, or interpretation thereof) in the clinician's field-of-view while the clinician is present in a clinical care environment and is utilizing an environmental augmentation device. Such environmental augmentation additionally may facilitate real-time documentation enabling more complete clinical records and ultimately improving the quality of patient care.

Abstract: The relative position and orientation between an auxiliary gearbox and a casing of an aircraft engine can be set including engaging a localizing feature of the accessory gearbox with a localizing feature of the casing; and a load path between auxiliary gearbox can subsequently be defined including securing at least two brackets between the accessory gearbox and casing.

Abstract: The gas turbine engine can have a casing, a rotor rotatable around a rotation axis relative the casing, the casing extending along and around the rotation axis, a first component mounted externally to the casing by a first mount, the first mount defining a torsion axis extending along a vertical radial orientation normal the rotation axis, the first component having a center of gravity located on a first side relative the torsion axis, a second component mounted externally to the casing on the second side, extending along the vertical radial orientation from a bottom portion to a top portion, a second mount structurally connecting the bottom portion to the casing, and a structure connecting the top portion to the first component on the second side relative the torsion axis.

Abstract: A fluid filter arrangement, with protection against external contamination, the filter arrangement comprising: a fluid circulating system; a filter cartridge having an exterior surface; a housing having an internal fluid chamber surrounding the exterior surface of the filter cartridge, an open end through which the filter cartridge can pass along a housing axis; and a cover sealed over the open end of the housing in a closed position, the cover in an open position exposing the open end of the housing, the cover including a fluid passage in communication with the internal fluid chamber in the closed position, the cover fluid passage being in communication with the fluid circulating system in the closed position and in the open position.

Abstract: A turboprop gas turbine engine mountable to an aircraft has an engine core and a gearbox driving a propeller, the engine core and the gearbox being enclosed within a nacelle. The propeller is located rearward of the gearbox and the engine core relative to a direction of travel of the aircraft. An air intake is disposed within the nacelle and formed to direct ambient air into the engine core. The air intake includes an air inlet duct, having a forward-facing intake inlet receiving the ambient air, with an upstream section and a downstream section. The upstream section is in fluid communication with the intake inlet and extends downstream from the intake inlet. The downstream section fluidly connects to and directs air from the upstream section into the engine air inlet. A second air outlet duct is located within the nacelle and directs air into an air-cooled-oil-cooler (ACOC).