Abstract: Various aspects of the subject technology relate to systems, methods, and machine-readable media for extracting information from videos. The method includes annotating portions of interest within screen captures. The method also includes receiving at least a first set of videos for a video game. The method also includes training a first machine-learning model to identify the portions of interest within the first set of videos. The method also includes generating validation data based on results of the first machine-learning model. The method also includes extracting information based on the portions of interest identified in the first set of videos.

Abstract: A finished floor assembly covers a floor area of an aircraft and includes a subfloor, a padding assembly, and a finish flooring layer. Noise radiates from the subfloor due to vibrations transmitted by an aircraft structure. The padding assembly attenuates the noise and includes a first pad layer, a second pad layer, and a plurality of discontinuous couplings. The first pad layer abuts the subfloor. The second pad layer is adjacent to the first pad layer. The plurality of discontinuous couplings are laterally separated from each other along the floor area by void portions. The discontinuous couplings secure the first pad layer to the second pad layer and the first pad layer and the second pad layer are in contact at the void portions. The finish flooring layer disposed overtop the padding assembly.

Abstract: A finished floor assembly covers a floor area of an aircraft and includes a subfloor, a padding assembly, and a finish flooring layer. Noise radiates from the subfloor due to vibrations transmitted by an aircraft structure. The padding assembly attenuates the noise and includes a first pad layer, a second pad layer, and a plurality of discontinuous couplings. The first pad layer abuts the subfloor. The second pad layer is adjacent to the first pad layer. The plurality of discontinuous couplings are laterally separated from each other along the floor area by void portions. The discontinuous couplings secure the first pad layer to the second pad layer and the first pad layer and the second pad layer are in contact at the void portions. The finish flooring layer disposed overtop the padding assembly.

Abstract: A method of repairing an over-frame blanket assembly in an aircraft includes identifying an aperture in an over-frame blanket piece having an exposed sound barrier layer. The method further includes cutting an acoustic barrier patch to a size that is larger than the aperture. The method includes adhering a sound barrier layer of the acoustic barrier patch to the exposed sound barrier layer of the over-frame blanket piece around the aperture to cover the aperture.

Abstract: An aircraft includes a turbine engine, a vibration sensor, and a processor. The vibration sensor is attached to the turbine engine and is configured to output a vibration sensor signal. The processor is programmed to determine whether the vibration sensor signal indicates that fan case liner damage has occurred due to icing conditions. The processor is further programmed to indicate that a fan case inspection should be conducted in response to the vibration sensor signal indicating that fan case liner damage has occurred.

Abstract: Aircraft and air scoop systems are provided. An aircraft includes an interior compartment, an outer skin, an air scoop, a movable element, and a passive pneumatic actuator. The interior compartment encloses a substantially constant interior air mass at a cabin pressure during flight and the outer skin at least partially defines a ventilated cavity. The air scoop is disposed on the outer skin and communicates air between the ventilated cavity and an external environment in which the aircraft is located. The movable element is movable between an open position and a closed position over the air scoop to define an air flow area through the air scoop. The passive pneumatic actuator is operatively coupled with the movable element and moves the movable element towards the closed position in response to an increasing altitude of the aircraft based on a differential pressure between the interior air mass and the external environment.

Abstract: A ventilation system for ventilating a passenger compartment of an aircraft, an aircraft, and a method of operating the ventilation system are disclosed herein. The ventilation system includes, but is not limited to, a bezel, a fluid vent, an electronic sensor, and a valve. The bezel defines a bezel aperture and the fluid vent defines an axis that passes through the bezel aperture to direct a stream of air through the bezel into the passenger compartment. The electronic sensor is associated with the bezel and is configured to generate a bezel position signal. The valve is configured to vary a flow rate of the stream of air through the fluid vent based on the bezel position signal.

Abstract: An acoustic barrier assembly includes a first wall that is gas impermeable. The acoustic barrier assembly further includes a second wall that is gas impermeable. The second wall is disposed opposite the first wall. The acoustic barrier assembly further includes a periphery wall coupling the first wall with the second wall in a manner that forms a pocket between the first wall and the second wall. The periphery wall is flexible, and the pocket is fluid-tight. The acoustic barrier assembly further includes a gas disposed in the pocket. The gas has a first molecular weight that is lower than a second molecular weight of air. The acoustic barrier assembly still further includes a biasing member that is disposed within the pocket. The biasing member is coupled with both the first wall and the second wall.

Abstract: Exemplary embodiments of a decorative hard flooring system for an aircraft are disclosed herein. The hard flooring system includes a plurality of decorative hard floor assemblies at least some of which include a decorative hard flooring layer and a metallic substrate layer having at least one aperture formed therein to receive a warming element. The flooring system further includes, a power supply coupled to the warming element and a controller coupled to the power supply to control the power supplied to the warming element. An ambient temperature sensor coupled to the controller to provide an indication of ambient temperature so that the controller controls the power supply to power the warming elements to warm the decorative hard floor assemblies to be substantially at the ambient temperature.

Abstract: A finished floor assembly covers a floor area of an aircraft and includes a subfloor, a padding assembly, and a finish flooring layer. Noise radiates from the subfloor due to vibrations transmitted by an aircraft structure. The padding assembly attenuates the noise and includes a first pad layer, a second pad layer, and a plurality of discontinuous couplings. The first pad layer abuts the subfloor. The second pad layer is adjacent to the first pad layer. The plurality of discontinuous couplings are laterally separated from each other along the floor area by void portions. The discontinuous couplings secure the first pad layer to the second pad layer and the first pad layer and the second pad layer are in contact at the void portions. The finish flooring layer disposed overtop the padding assembly.

Abstract: An acoustic barrier assembly including a first wall composed of a first material. The first material is substantially gas impermeable. The assembly further includes a second wall composed of a second material. The second material is substantially gas impermeable. The second wall is disposed opposite the first wall and coupled to the first wall in a manner that forms a pocket between the first wall and the second wall. The assembly further includes a valve in fluid communication with the pocket. The valve is configured to be selectively opened and closed to control the passage of fluid into and out of the pocket. The valve, when closed, cooperates with the first wall and the second wall to maintain the pocket in a fluid-tight configuration. The assembly still further includes a gas disposed in the pocket. The gas has a molecular weight that is lower than the molecular weight of air.

Abstract: A turbofan engine assembly includes a fan, a fan case, and a fan case liner. A fan blade has a fan blade tip at the distal end of the fan blade. The fan case liner is spaced apart from the fan blade tip by a clearance distance, is disposed between the fan case and the fan blade tip, and includes an abradable base layer and an abradable indicator layer. The abradable base layer is in closest proximity to the fan and has a first visual characteristic and a depth matching a clearance threshold allowable value. The abradable indicator layer is disposed between the abradable base layer and the fan case. The abradable indicator layer has a second visual characteristic that is visually distinguishable from the first visual characteristic to indicate when the abradable base layer has worn away such that the clearance distance has exceeded the clearance threshold allowable value.

Abstract: An aircraft includes a turbine engine, a vibration sensor, and a processor. The vibration sensor is attached to the turbine engine and is configured to output a vibration sensor signal. The processor is programmed to determine whether the vibration sensor signal indicates that fan case liner damage has occurred due to icing conditions. The processor is further programmed to indicate that a fan case inspection should be conducted in response to the vibration sensor signal indicating that fan case liner damage has occurred.

Abstract: A method of repairing an over-frame blanket assembly in an aircraft includes identifying an aperture in an over-frame blanket piece having an exposed sound barrier layer. The method further includes cutting an acoustic barrier patch to a size that is larger than the aperture. The method includes adhering a sound barrier layer of the acoustic barrier patch to the exposed sound barrier layer of the over-frame blanket piece around the aperture to cover the aperture.

Abstract: Fuselage assemblies, over-frame blanket assemblies, and methods of installing over-frame blanket assemblies are provided. A fuselage assembly for an aircraft includes a fuselage skin, a cabin liner, and an over-frame blanket assembly. The cabin liner has an outer side facing the fuselage skin. The over-frame blanket assembly is disposed between the fuselage skin and the cabin liner and has a first blanket piece. The first blanket piece includes a first sound barrier layer that defines a first outer surface of the over-frame blanket assembly and a first sound absorbing layer that defines a second outer surface of the over-frame blanket assembly facing the fuselage skin. A method of installing the over-frame blanket assembly includes positioning the first blanket piece in an orientation such that the first sound barrier layer is directly adjacent the cabin liner.

Abstract: Fuselage assemblies, over-frame blanket assemblies, and methods of installing over-frame blanket assemblies are provided. A fuselage assembly for an aircraft includes a fuselage skin, a cabin liner, and an over-frame blanket assembly. The cabin liner has an outer side facing the fuselage skin. The over-frame blanket assembly is disposed between the fuselage skin and the cabin liner and has a first blanket piece. The first blanket piece includes a first sound barrier layer that defines a first outer surface of the over-frame blanket assembly and a first sound absorbing layer that defines a second outer surface of the over-frame blanket assembly facing the fuselage skin. A method of installing the over-frame blanket assembly includes positioning the first blanket piece in an orientation such that the first sound barrier layer is directly adjacent the cabin liner.

Abstract: Aircraft and air scoop systems are provided. An aircraft includes an interior compartment, an outer skin, an air scoop, a movable element, and a passive pneumatic actuator. The interior compartment encloses a substantially constant interior air mass at a cabin pressure during flight and the outer skin at least partially defines a ventilated cavity. The air scoop is disposed on the outer skin and communicates air between the ventilated cavity and an external environment in which the aircraft is located. The movable element is movable between an open position and a closed position over the air scoop to define an air flow area through the air scoop. The passive pneumatic actuator is operatively coupled with the movable element and moves the movable element towards the closed position in response to an increasing altitude of the aircraft based on a differential pressure between the interior air mass and the external environment.

Abstract: Fuselage assemblies, over-frame blanket assemblies, and methods of installing over-frame blanket assemblies are provided. A fuselage assembly for an aircraft includes a fuselage skin, a cabin liner, and an over-frame blanket assembly. The cabin liner has an outer side facing the fuselage skin. The over-frame blanket assembly is disposed between the fuselage skin and the cabin liner and has a first blanket piece. The first blanket piece includes a first sound barrier layer that defines a first outer surface of the over-frame blanket assembly and a first sound absorbing layer that defines a second outer surface of the over-frame blanket assembly facing the fuselage skin. A method of installing the over-frame blanket assembly includes positioning the first blanket piece in an orientation such that the first sound barrier layer is directly adjacent the cabin liner.

Abstract: Aircraft and air scoop systems are provided. An aircraft includes an interior compartment, an outer skin, an air scoop, it movable element, and a passive pneumatic actuator. The interior compartment encloses a substantially constant interior air mass at a cabin pressure during flight and the outer skin at least partially defines a ventilated cavity. The air scoop is disposed on the outer skin and communicates air between the ventilated cavity and an external environment in which the aircraft is located. The movable element is movable between an open position and a closed position over the air scoop to define an air flow area through the air scoop. The passive pneumatic actuator is operatively coupled with the movable element and moves the movable element towards the closed position in response to an increasing altitude of the aircraft based on a differential pressure between the interior air mass and the external environment.

Abstract: A ventilation system for ventilating a passenger compartment of an aircraft, an aircraft, and a method of operating the ventilation system are disclosed herein. The ventilation system includes, but is not limited to, a bezel, a fluid vent, an electronic sensor, and a valve. The bezel defines a bezel aperture and the fluid vent defines an axis that passes through the bezel aperture to direct a stream of air through the bezel into the passenger compartment. The electronic sensor is associated with the bezel and is configured to generate a bezel position signal. The valve is configured to vary a flow rate of the stream of air through the fluid vent based on the bezel position signal.