Abstract: A throttle quadrant system for an aircraft includes: a first throttle handle to control a first engine of the aircraft, the first throttle handle having a first activatable visual indicator integrated therein; a second throttle handle to control a second engine of the aircraft, the second throttle handle comprising a second activatable visual indicator integrated therein; and at least one controller to control activation and operation of the first activatable visual indicator and the second activatable visual indicator. The at least one controller responds to first engine data related to operating status of the first engine to selectively activate the first activatable visual indicator. The at least one controller also responds to second engine data related to operating status of the second engine to selectively activate the second activatable visual indicator.

Abstract: The disclosed embodiments describe cover detection systems, controllers, and aircraft. The aircraft includes the controller and parts of the cover detection systems. A cover detection system includes an engine, a first sensor, a second sensor, an engine cover, and a controller. The engine has moving parts and defines a fluid opening. The fluid opening exposes the moving parts to an ambient environment. The first sensor component is located proximate to the engine and the second sensor component is configured to interact with the first sensor component. The engine cover assembly includes an engine cover and a second sensor. The engine cover is configured to cover the fluid opening. The controller is configured to determine whether the engine cover is installed on the engine based on an interaction between the first sensor component and the second sensor component.

Abstract: The disclosed embodiments describe cover detection systems, controllers, and aircraft. The aircraft includes the controller and parts of the cover detection systems. A cover detection system includes an engine, a first sensor, a second sensor, an engine cover, and a controller. The engine has moving parts and defines a fluid opening. The fluid opening exposes the moving parts to an ambient environment. The first sensor component is located proximate to the engine and the second sensor component is configured to interact with the first sensor component. The engine cover assembly includes an engine cover and a second sensor. The engine cover is configured to cover the fluid opening. The controller is configured to determine whether the engine cover is installed on the engine based on an interaction between the first sensor component and the second sensor component.

Abstract: A throttle quadrant system for an aircraft includes: a first throttle handle to control a first engine of the aircraft, the first throttle handle having a first activatable visual indicator integrated therein; a second throttle handle to control a second engine of the aircraft, the second throttle handle comprising a second activatable visual indicator integrated therein; and at least one controller to control activation and operation of the first activatable visual indicator and the second activatable visual indicator. The at least one controller responds to first engine data related to operating status of the first engine to selectively activate the first activatable visual indicator. The at least one controller also responds to second engine data related to operating status of the second engine to selectively activate the second activatable visual indicator.

Abstract: Control system and method for controlling power flow in dual active bridge converters. The control system comprises a compensator, a feedback unit, and a modulator. An outer loop provides a reference signal. The output of the compensator are the control parameters for the modulator. The feedback unit samples the transformer current once every half switching cycle to thereby determine a power level. The power level is used to determine a modulation technique to apply. The modulation technique is one of phase-shift modulation (PSM), variable duty cycle modulation (VDM), or triangular current mode modulation (TCM).

Abstract: Embodiments provide an aeromedical bio-containment module for use in a cargo plane. The aeromedical bio-containment module includes a fully integrated pallet system allowing for the module to roll onto the cargo plane. An integrated set of lugs allows the module to be locked into the cargo plane floor without the use of chains or other pallets. The aeromedical bio-containment module features a ward area for safe treatment of patients, an anteroom, and an office area for personnel. The aeromedical bio-containment module operates under a negative pressure system, and includes a full air filtration system to remove pathogens, particulates, and other airborne contaminants.

Abstract: A temperature assessment system aligns and analyzes optical sensor data and thermal sensor data to perform temperature assessments in a physical environment. The temperature assessment system may include facial detection and distance verification components, using a combination of machine learning and heuristics-based techniques to generate bounding boxes and perform individual assessments for multiple different people within the environment. Assessments may include temperature assessments, thermal uniformity assessments, and mask detection, and the results of the assessments may be used to transmit outputs to monitoring systems, provide alert notifications, and control various output devices based on the assessment status of the individual.

Abstract: An aircraft includes an engine, a thrust reverser, landing gear, a brake system, a pilot input device, and a control system. The engine is configured to generate thrust directed to move the aircraft in a forward direction. The landing gear includes wheels. The brake system is configured to generate a braking force on the wheels. The pilot input device is positioned for use by a pilot of the aircraft. The control system is programmed to: determine whether the taxi operations are allowed; receive a request to achieve and hold a taxi speed at a desired taxi speed from the pilot input device; and command the engine, the thrust reverser, and the brake system to achieve and maintain the desired taxi speed in response to receiving the request to hold taxi speed only when the taxi operations are allowed.

Abstract: A multi-modal diamond abrasive package or slurry is disclosed for polishing hard substrates. The multi-modal diamond abrasive package or slurry generally includes a plurality of diamond abrasives. Each one of the diamond abrasives of the plurality of diamond abrasives has a particle size. Wherein, the multi-modal diamond abrasive package or slurry includes a first diamond abrasive and a second diamond abrasive. The first diamond abrasive has a first particle size, and the second diamond abrasive has a second particle size. Where, the first particle size of the first diamond abrasive is smaller than the second particle size of the second diamond abrasive.

Abstract: Control system and method for controlling power flow in dual active bridge converters. The control system comprises a compensator, a feedback unit, and a modulator. An outer loop provides a reference signal. The output of the compensator are the control parameters for the modulator. The feedback unit samples the transformer current once every half switching cycle to thereby determine a power level. The power level is used to determine a modulation technique to apply. The modulation technique is one of phase-shift modulation (PSM), variable duty cycle modulation (VDM), or triangular current mode modulation (TCM).

Abstract: A method and apparatus are provided for determining the orientation of an object relative to a platform likely to be exposed to buffeting. The object may be a helmet worn by a pilot in which orientation of the helmet relative the aircraft while in flight may usefully be known, in particular when determining the position of space-stabilised symbols being displayed in an associated helmet-mounted digital display system. According to the method, not only may orientation of an object may be predicted at some time ahead of a time point of validity of source sensor data, but the prediction may be dynamically configured to according to a detected severity of buffeting to reduce the effects of the buffeting upon the quality of data output by the system. The method includes measuring the severity of any buffeting using the same source data as used to determine orientation of the object.

Abstract: An aircraft, a control surface arrangement, and a method of assembling an aircraft are disclosed herein. In an exemplary embodiment, the aircraft includes, but is not limited to, an airframe, a control surface, and a rotary actuator. The rotary actuator rotatably mounts the control surface to the airframe. The rotary actuator supports the control surface on the airframe and is configured to rotate the control surface with respect to the airframe when the rotary actuator is actuated. The rotary actuator is further configured to deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator.

Abstract: A method is provided for determining corrections to rate data output by inertial sensors of a type typically used in tracking changes in orientation of an object. The present invention also extends to a tracker system incorporating the correction functionality of the present invention. The method makes use of rate data output by inertial sensors associated with the object being tracked and rate data derived from measures of orientation supplied by a non-inertial tracker system also associated with the object being tracked and comprises determining from those rate data corrections for errors due to misalignment in rate data output by inertial sensors, by calculating a mapping between vectors linking points in inertial sensor rate space represented by a sample set of received rate data from the inertial sensors and vectors linking points in a derived object orientation rate space represented by a corresponding and synchronised sample set of derived rate data.

Abstract: An aircraft includes an engine, a thrust reverser, landing gear, a brake system, a pilot input device, and a control system. The engine is configured to generate thrust directed to move the aircraft in a forward direction. The landing gear includes wheels. The brake system is configured to generate a braking force on the wheels. The pilot input device is positioned for use by a pilot of the aircraft. The control system is programmed to: determine whether the taxi operations are allowed; receive a request to achieve and hold a taxi speed at a desired taxi speed from the pilot input device; and command the engine, the thrust reverser, and the brake system to achieve and maintain the desired taxi speed in response to receiving the request to hold taxi speed only when the taxi operations are allowed.

Abstract: A ceramic matrix composite (“CMC”) center body may be positioned around an austenitic nickel-chromium-based superalloy attachment ring. The attachment ring may be integrally formed with a turbine engine case. The attachment ring may have a greater coefficient of thermal expansion than the center body. A plurality of pins may be inserted through apertures in the center body and coupled to the attachment ring. The pins may slide within the apertures, allowing the attachment ring to expand without applying a load on the center body.

Abstract: An aircraft seat assembly for supporting a seat occupant, and a method for fabricating an aircraft seat assembly for supporting a seat occupant are provided. In one non-limiting example, the aircraft seat assembly includes a seat cushion supported by the seat structure. A vibration producing apparatus configured to produce vibrations conducive for inducing drowsiness. The vibration producing apparatus is disposed adjacent to or within the seat structure for transferring the vibrations to the seat occupant.

Abstract: A multi-modal diamond abrasive package or slurry is disclosed for polishing hard substrates. The multi-modal diamond abrasive package or slurry generally includes a plurality of diamond abrasives. Each one of the diamond abrasives of the plurality of diamond abrasives has a particle size. Wherein, the multi-modal diamond abrasive package or slurry includes a first diamond abrasive and a second diamond abrasive. The first diamond abrasive has a first particle size, and the second diamond abrasive has a second particle size. Where, the first particle size of the first diamond abrasive is smaller than the second particle size of the second diamond abrasive.

Abstract: A method and apparatus are provided for determining the orientation of an object relative to fixed, moving or moveable platform likely to be exposed to buffeting or similar effects. The object may for example be a helmet worn by a pilot of an aircraft in which orientation of the helmet relative the aircraft while in flight may usefully be known, in particular when determining the position of space-stabilised symbols being displayed in an associated helmet-mounted digital display system. According to the method, not only may orientation of an object may be predicted at some time ahead of a time point of validity of source sensor data—a useful feature for digital display systems—but the functionality carrying out the prediction may be dynamically configured to according to a detected severity of buffeting upon the object and upon the tracker system sensors to reduce the effects of the buffeting upon the quality of data output by the tracker system.

Abstract: An aircraft seat assembly for supporting a seat occupant, and a method for fabricating an aircraft seat assembly for supporting a seat occupant are provided. In one non-limiting example, the aircraft seat assembly includes a seat structure and a seat cushion that is supported by the seat structure. A vibration mitigating apparatus is operatively coupled to the seat structure to prevent or reduce vibrations from transferring to the seat occupant.

Abstract: An induction machine with integrated magnetic gears is disclosed. The machine comprises two rotors and two stators. An outer stator has ferromagnetic material, producing a rotating magnetic field with a defined number of pole pairs synchronized with a supply frequency. A high speed rotor has ferromagnetic material and a combination of rotor bars and permanent magnet pole pieces selected so that the permanent magnet pole pieces do not interact with the outer stator magnetic field. The high speed rotor rotation is asynchronously coupled to the outer stator magnetic field. An inner stator has ferromagnetic steel segments that modulate the field produced by the high speed rotor permanent magnets. A low speed inner rotor has ferromagnetic material and permanent magnet pole pieces, the low speed inner rotor counter-rotating to the high speed rotor. The low speed inner rotor is synchronously coupled to the high speed rotor using modulation harmonics.