Abstract: An example implementation provides a computing device including a first computing device portion having one or more electrical components, a first side, a second side, an electromagnetic coil, and a first metal frame having a first through-slot. The computing device also a second computing device portion having one or more other electrical components, a third side, a fourth side and a second metal frame having a second through-slot. A mechanical joint connects the first computing device portion and the second computing device portion such that the first side is positioned to face the third side and the electromagnetic coil overlaps the first through-slot and the second through-slot along an axis running orthogonal to the first computing device portion and the second computing device portion. Control circuitry adjusts matching to compensate different physical configurations, and firmware switches the radiofrequency configuration.

Abstract: A cavity-backed slot antenna is disclosed that includes a stripline. The stripline includes a conductive strip between two ground planes separated by a dielectric. The conductive strip feeds the cavity-backed slot antenna. The stripline also includes a first segment and a second segment. The first segment has a first characteristic impedance. The second segment is proximate the cavity-backed antenna and has a second characteristic impedance different than the first characteristic impedance. The second characteristic impedance provides impedance for matching a load impedance of the cavity-backed slot antenna.

Abstract: The invention relates to a novel group of compounds of Formula (I) or salts thereof: wherein Y, Z1, Z2, R1, R4, R5 and n are as described in the specification, which may be useful in the treatment or prevention of a disease or medical condition mediated through protein kinase B (PKB) such as cancer. The invention also relates to pharmaceutical compositions comprising said compounds, methods of treatment of diseases mediated by PKB using said compounds and methods for preparing compounds of Formula (I).

Abstract: The present invention relates to microbial cells, including but not limited to aerobic bacteria cells and anaerobic bacteria cells, as well as yeast cells, and methods for producing the cells, feed additives and compositions comprising the cells, and uses involving administration of the cells to animals.

Abstract: The invention relates to a novel group of compounds of Formula (I) or salts thereof: wherein Y, Z1, Z2, R1, R4, R5 and n are as described in the specification, which may be useful in the treatment or prevention of a disease or medical condition mediated through protein kinase B (PKB) such as cancer. The invention also relates to pharmaceutical compositions comprising said compounds, methods of treatment of diseases mediated by PKB using said compounds and methods for preparing compounds of Formula (I).

Abstract: The disclosed technology provides an antenna structure located in the metal casing of a computing device. A first open slot radiating structure radiates at a radiating wavelength and is located on a surface of the metal casing of the computing device. A second open slot radiating structure radiates at the radiating wavelength and is located on the surface of the metal casing of the computing device. At least one closed slot radiator element is located between the first open slot radiating structure and the second open slot radiating structure on the surface of the metal casing of the computing device. The closed slot radiator element is approximately half the length of the radiating wavelength.

Abstract: A valve (100) includes a housing (111) and the fluid port (121). A plunger (125) is configured to seal the fluid port (121) in a first position (91) and to unseal the fluid port (121) in a second position and to displace along a displacement direction (259) from its first position (91) towards its second position. The valve (100) also includes at least one shape memory alloy, SMA, actuator (151, 152) extending along the displacement direction (259) for at least 50% of its length and configured to exert an actuation force (155) on the plunger (125) to displace the plunger (125) from the first position (91) towards the second position.

Abstract: Methods for restoring tidal areas adjacent to a tidal water area are provided. The method can comprise: pumping water from the tidal water area; and directing a high-pressure water stream, using the water pumped from the tidal water area, to the bottom surface of the tidal water area during an incoming tide period. The high-pressure water stream impacts the bottom surface of the tidal water area with sufficient force to dislodge sediment from the bottom surface into the tidal water area.

Abstract: An example implementation provides a computing device including a first computing device portion having one or more electrical components, a first side, a second side, an electromagnetic coil, and a first metal frame having a first through-slot. The computing device also a second computing device portion having one or more other electrical components, a third side, a fourth side and a second metal frame having a second through-slot. A mechanical joint connects the first computing device portion and the second computing device portion such that the first side is positioned to face the third side and the electromagnetic coil overlaps the first through-slot and the second through-slot along an axis running orthogonal to the first computing device portion and the second computing device portion. Control circuitry adjusts matching to compensate different physical configurations, and firmware switches the radiofrequency configuration.

Abstract: A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to apply torque to a pinion so the pinion rotates. An engagement command is issued to an actuator at an engagement time, and the actuator operates the actuator in response to the engagement command to move the pinion from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear; then after the initial contact time operating the actuator to move the pinion further to a meshing position where the pinion meshes with the driven gear. A centre-to-centre distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position.

Abstract: The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.

Abstract: A flash redirecting recoil compensator for a firearm includes a compensator body that provides a platform for the rest of the components. The compensator body attaches with a firearm in order to reduce recoil force and redirect the muzzle flash away from the site of the shooter. An attachment chamber and a discharge chamber of the compensator body are positioned through a top portion of the compensator body from a rear face to a front face. The attachment chamber fastens the compensator body into the firearm while the discharge chamber provides space for the discharging bullet. At least two vectoring ports, which are traversed through the compensator body and into the discharge chamber, redirect hot gas and unspent propellants away from the firearm after the bullet is discharged as the redirection of the hot gas and unspent propellants reduce the recoil force and provide a clear shooting sight.

Abstract: A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to rotate a pinion which is moved from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear; then after the initial contact time moving the pinion further to a meshing position where the pinion meshes with the driven gear. A centre-to-centre distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position. The driven gear has Ngear teeth or rollers, the pinion has Npinion teeth or rollers which mesh with the teeth or rollers of the driven gear when the pinion is at the meshing position.

Abstract: A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to apply torque to a pinion so the pinion rotates and moved from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear. After the initial contact time the pinion is moved further to a meshing position where the pinion meshes with the driven gear. A centre-to-centre distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position. The driven gear contacts the pinion in a series of impacts as the pinion moves from the contact position to the meshing position, each impact induces a spike in electromotive force or angular velocity at the motor.

Abstract: A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to apply torque to a pinion so the pinion rotates. An engagement command is issued to an actuator at an engagement time, and the actuator operates the actuator in response to the engagement command to move the pinion from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear; then after the initial contact time operating the actuator to move the pinion further to a meshing position where the pinion meshes with the driven gear. A centre-to-centre distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position.

Abstract: The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.

Abstract: A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to rotate a pinion which is moved from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear; then after the initial contact time moving the pinion further to a meshing position where the pinion meshes with the driven gear. A center-to-center distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position. The driven gear has Ngear teeth or rollers, the pinion has Npinion teeth or rollers which mesh with the teeth or rollers of the driven gear when the pinion is at the meshing position.

Abstract: The invention relates to an aircraft steering system using an aircraft ground taxi drive system whereby electrical power generated by a first motor-generator of a landing gear wheel drive system in a regenerative braking mode is supplied to a second motor-generator of a landing gear wheel drive system in a motorized driving mode.

Abstract: A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to apply torque to a pinion so the pinion rotates and moved from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear. After the initial contact time the pinion is moved further to a meshing position where the pinion meshes with the driven gear. A center-to-center distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position. The driven gear contacts the pinion in a series of impacts as the pinion moves from the contact position to the meshing position, each impact induces a spike in electromotive force or angular velocity at the motor.

Abstract: The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.