Abstract: The present disclosure provides, inter alia, compounds with MASP-2 inhibitory activity, compositions of such compounds and methods of making and using such compounds.

Abstract: IC interconnect structures including subtractively patterned features. Feature ends may be defined through multiple patterning of multiple cap materials for reduced misregistration. Subtractively patterned features may be lines integrated with damascene vias or with subtractively patterned vias, or may be vias integrated with damascene lines or with subtractively patterned lines. Subtractively patterned vias may be deposited as part of a planar metal layer and defined currently with interconnect lines. Subtractively patterned features may be integrated with air gap isolation structures. Subtractively patterned features may be include a barrier material on the bottom, top, or sidewall. A bottom barrier of a subtractively patterned features may be deposited with an area selective technique to be absent from an underlying interconnect feature. A barrier of a subtractively patterned feature may comprise graphene or a chalcogenide of a metal in the feature or in a seed layer.

Abstract: The invention relates to heterocyclic compounds, pharmaceutically acceptable salts thereof, and pharmaceutical preparations thereof. Also described herein are compositions and the use of such compounds in methods of treating diseases and conditions mediated by deficient CFTR activity, in particular cystic fibrosis.

Abstract: A control system and methods for controlling the position of one or more engine-mounting links of an engine-mounting linkage system are provided. In one aspect, an engine-mounting linkage system includes one or more engine-mounting links that each have an adjustable inclination angle. An inclination angle of a link may be adjusted by an actuator of the control system. One or more controllers of the control system can control the actuator and thus the inclination angle of the link by determining a control command based at least in part on an output received from one or more sensors of the control system. The controllers can then cause the actuator to change the inclination angle of the link based at least in part on the determined control command.

Abstract: Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle ? of at least one of the plurality of engine-mounting links.

Abstract: Described herein are devices, systems and methods for monitoring the use of a nebulized medication, such as can be administered using a nebulizer. These can be used for monitoring a patient undergoing treatment for COPD and improve compliance to the recommended therapy. Monitored parameters include flow, humidity and acceleration and provide data as to the quantity and quality of nebulizer use.

Abstract: Described herein are devices, systems and methods for monitoring the use of a nebulized medication, such as can be administered using a nebulizer. These can be used for monitoring a patient undergoing treatment for COPD and improve compliance to the recommended therapy. Monitored parameters include flow, humidity and acceleration and provide data as to the quantity and quality of nebulizer use.

Abstract: An aircraft and propulsion system are provided. The aircraft includes an airframe including one or more of a fuselage, a wing, or an empennage. The aircraft includes an aircraft propulsion system including a front frame and an aft frame. A front mount link is connected to the airframe and the front frame, and the aft frame is selectively connected to the airframe by an aft mount link.

Abstract: Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle ? of at least one of the plurality of engine-mounting links.

Abstract: A control system and methods for controlling the position of one or more engine-mounting links of an engine-mounting linkage system are provided. In one aspect, an engine-mounting linkage system includes one or more engine-mounting links that each have an adjustable inclination angle. An inclination angle of a link may be adjusted by an actuator of the control system. One or more controllers of the control system can control the actuator and thus the inclination angle of the link by determining a control command based at least in part on an output received from one or more sensors of the control system. The controllers can then cause the actuator to change the inclination angle of the link based at least in part on the determined control command.

Abstract: An aircraft and propulsion system are provided. The aircraft includes an airframe including one or more of a fuselage, a wing, or an empennage. The aircraft includes an aircraft propulsion system including a front frame and an aft frame. A front mount link is connected to the airframe and the front frame, and the aft frame is selectively connected to the airframe by an aft mount link.

Abstract: A connection assembly for mounting an engine to a mounting structure. The engine is rotatable about an axis of rotation and defines an axial direction extending along the axis of rotation from a forward end to an aft end. The engine has a center of gravity. The connection assembly includes: an engine coupling piece coupled to the engine; and a connection piece connecting the engine coupling piece and the mounting structure, the connection piece being inclined toward the axial direction. A mounting system including the connection assembly is also described.

Abstract: Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal ci

Abstract: Described herein are devices, systems and methods for monitoring the use of a nebulized medication, such as can be administered using a nebulizer. These can be used for monitoring a patient undergoing treatment for COPD and improve compliance to the recommended therapy. Monitored parameters include flow, humidity and acceleration and provide data as to the quantity and quality of nebulizer use.

Abstract: An overload clutch in a drivetrain having a shaft-hub connection between an input part and an output part is disclosed. The overload clutch includes a press fit including a first contact surface and a second contact surface, wherein at least one of the first contact surface and the second contact surface is coated with a soft metal. For homogenizing a surface pressure of the first and second contact surfaces, an oversize allowance between components forming a shaft and a hub is selected prior to joining the shaft and the hub such that during the joining a yield point of the soft metal is reached or exceeded.

Abstract: A gearwheel arrangement for a drive train of a motor vehicle includes a drive shaft, a gearwheel, and a slipping clutch. The gearwheel is seated on the drive shaft and includes a toothing system. The slipping clutch is disposed at a point on the gearwheel between the toothing system and the drive shaft. The slipping clutch opens if a limit torque to be transmitted between the drive shaft and the toothing system is exceeded. In an example embodiment, the slipping clutch has a shaft/hub connection with a shaft region and a hub region, and the shaft region is seated via a press fit on the hub region.

Abstract: A connection assembly for mounting an engine to a mounting structure. The engine is rotatable about an axis of rotation and defines an axial direction extending along the axis of rotation from a forward end to an aft end. The engine has a center of gravity. The connection assembly includes: an engine coupling piece coupled to the engine; and a connection piece connecting the engine coupling piece and the mounting structure, the connection piece being inclined toward the axial direction. A mounting system including the connection assembly is also described.

Abstract: Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal ci