Abstract: A torque barrel for use with a brake system may comprise a torque barrel having a cylindrical structure including an inner surface, an outer surface, a first opening at a first end, and a second opening at an opposing second end; and a longitudinal hole disposed through the outer surface of the barrel between a first spline of the plurality of splines and a second spline of the plurality of splines.

Abstract: A landing gear actuation system is disclosed herein. The landing gear actuation system includes an attachment point integral to a movable member, a flexible pull member having a first end coupled to the attachment point, and a motor configured to move the flexible pull member, wherein the movement of the flexible pull member moves the attachment point and the movable member.

Abstract: A method of logging an observation or maintenance request of an aircraft, the method can comprise: scanning, by a personal internet device connected to a network, a machine-readable code; directing the personal internet device to a user interface of an aircraft log database based on the machine-readable code; and transmitting, by the personal internet device, a log entry to the aircraft log database over the network, wherein the log entry comprises a description of the observation. The method can further comprise transmitting an alert notification to an aircraft maintenance system. An aircraft log system can comprise a personal internet device, a machine-readable code disposed on an aircraft, and an aircraft log database. The aircraft log system can further comprise a manufacturer log database.

Abstract: An energy harvesting roller for a cargo handling system may comprise a shaft and a sleeve located on the shaft. A piezoelectric member may be coupled to the sleeve. A shell may be located radially outward of the piezoelectric member and configured to rotate relative to the sleeve. A radially inward surface of the shell may define at least one of a plurality of grooves or a plurality of protrusions.

Abstract: A fiber reinforced composite component may include interleaved fiber layers and ceramic particle layers coated with matrix material. The fiber reinforced composite component may be fabricated by forming a fibrous preform, needling the fibrous preform to form a plurality of z-direction fibers, and densifying the fibrous preform. The fibrous preform may be fabricated by forming a first ceramic particle layer over a first fiber layer, disposing a second fiber layer over the first ceramic particle layer, forming a second ceramic particle layer over the second fiber layer, and disposing a third fiber layer over the second ceramic particle layer.

Abstract: A tie down for a cargo handling system may comprise a carriage. the carriage may include a first sidewall surface, a second sidewall surface opposite the first sidewall surface, a first surface extending from the first sidewall surface to the second sidewall surface, and a second surface opposite the first surface. A first rail interface pin may be configured to extend from the first sidewall surface. A second rail interface pin may be configured to extend from the second sidewall surface. A seat fitting channel may be formed in the carriage and may extend between the first sidewall surface and the second sidewall surface.

Abstract: A system for controlling a power signal for zero voltage switching (ZVS) includes a voltage zero crossing detection module to detect a zero voltage condition in response to an inverter voltage from a resonant inverter crossing zero volts, and a current zero crossing detection module to detect a zero current condition in response to an inverter current from the resonant inverter crossing zero amps. The system further includes a phase detect module to detect actual phase data corresponding to an actual phase angle between the inverter voltage and the inverter current based on the zero voltage and zero current condition. The system further includes a comparator to determine a phase difference between a desired phase between the inverter voltage and the inverter current and the actual phase angle. The system further includes a controller to adjust a property of a resonant inverter to reduce the phase difference.

Abstract: The present disclosure provides a water activated transmitter assembly configured to provide a signal to a wireless light assembly when the water activated transmitter assembly is exposed to water. A water emergency device system is also disclosed, which comprises the water activated transmitter assembly and the wireless light assembly coupled to a water flotation device. A method of manufacture of the water activated transmitter assembly is also disclosed.

Abstract: Ice may form along the leading edge of an aircraft wing or horizontal and vertical stabilizers. A pneumatic deicer system may be configured to inflate and dislodge ice along the leading edge of lift and control surfaces. The pneumatic deicer system may comprise a laser welded deicing boot attached to the leading edge. The compressed air can be directed to the deicing boot, inflating the deicing boot along inflatable tubes formed by laser welds, which can crack and dislodge the ice. A method of manufacturing a laser welded pneumatic deicer boot is also disclosed.

Abstract: An aircraft evacuation slide assembly may be comprised of a plurality of composite textiles. Each composite textile may comprise a fabric substrate, an inner polyurethane coating, and an outer heat reflective coating. The outer heat reflective coating may comprise nanofillers that improve polymer properties, such as mechanical, barrier, thermal, flame retardancy, and electrical properties. Moreover, the outer heat reflective coating may comprise nanofillers that enable hot air welding and radio frequency welding of the plurality composite textiles to form the aircraft evacuation slide assembly.

Abstract: Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly having a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and may decompose the propellant, liberating a compressed gas. The compressed gas may be directed to the deicing boot assembly, inflating the deicing boot, which may crack and dislodge the ice.

Abstract: An aircraft wing may comprise an airfoil having deicing zone, an anti-icing zone, and an ice runback control zone. An aircraft wing may comprise an electro-thermal ice protection system disposed in the aircraft wing. The electro-thermal ice protection system may be disposed along the deicing, anti-icing, and ice runback control zones of the airfoil to improve aerodynamic performance of the aircraft and reduce ice formation along the wings of the aircraft.

Abstract: An explosive cord is disclosed. In various embodiments, the explosive cord includes a tube having a tube inner surface and a tube outer surface, the tube inner surface defining a hollow interior that extends along a length of the tube; a carrier fiber disposed within the hollow interior of the tube, the carrier fiber having a carrier fiber exposed surface area; and a reactive material disposed on the carrier fiber exposed surface area.

Abstract: A control system for a cargo handling system is disclosed. The control system may be configured to advance larger containers at a slower speed than smaller containers. For instance, all containers may be initially advanced by the same first velocity control signal. At the expiration of a certain time period, all containers may thereafter be advanced by a different velocity control signal (from the first velocity control signal) that should least substantially maintain the velocity of the container as it existed at the time of the expiration of the noted time period. The length of the time period (for advancing the container at the first velocity control signal) may be varied based upon the size of the containers such that larger containers are accelerated for a shorter time than smaller containers and which in turn should then advance larger containers at a lower velocity compared to smaller containers.

Abstract: A method for monitoring an aircraft cargo bay using an aircraft interface device may comprise receiving image data of a cargo bay of an aircraft. The method may further comprise detecting movement in the cargo bay, directing a camera to activate in response to that movement, and processing the captured image data. The aircraft interface device may include pre-trained neural network based algorithms configured for event classification. The method may further comprise generating an alarm based on a theft event classification and transmitting the alarm to an aircraft.

Abstract: A wheel and brake assembly comprising: a stator; a rotating assembly mounted around and rotatable relative to the stator about an axis A; a torque tube in fixed engagement with the stator; a stack of brake disks mounted about the torque tube, the stack of brake disks comprising alternate rotor disks and stator disks, the stator disks attached to the torque tube and the rotor disks attached to the rotating assembly; a brake actuator configured to, in response to a brake command, apply a pressing force on the stack of brake disks to cause frictional engagement between the rotor disks and the stator disks such that the stator disks prevent the rotor disks and, hence the rotating assembly, from rotating relative to the torque tube.

Abstract: A component inspection system for monitoring and detecting damage to components of a cargo handling system may comprise a first camera configured to monitor a first detection zone, and an inspection controller configured to analyze image data output by the first camera. The inspection system controller may be configured to identify a component of the cargo handling system in the image data received from the first camera and determine a state of the component. The state of the component may be at least one of a normal state or a damaged state.

Abstract: An anti-icing system may comprise a deicing boot of an elastomeric material comprising a plurality of tubes, wherein the deicing boot comprises a first set of tubes and a second set of tubes, wherein each of the first set of tubes and the second set of tubes have a corresponding end, and wherein the corresponding end is coupled to a continuous dual wrap end closure.

Abstract: A system for monitoring an electrohydraulic servo valve may comprise a brake control unit, a valve monitoring sensor configured to measure a pressure in a conduit fluidly connected to a control port of the electrohydraulic servo valve, and a tangible, non-transitory memory configured to communicate with the brake control unit. The brake control unit may be configured to receive a brake command, output a pressure signal to the electrohydraulic servo valve based on the brake command, receive a sensor signal from the valve monitoring sensor, and determine a health of the electrohydraulic servo valve based on the sensor signal.

Abstract: A stretch senor assembly may comprise a stretch sensor, a first housing and a second housing. The stretch sensor may include a first mounting end, a second mounting end, and a sensing region extending between the first mounting end and the second mounting end. The first housing may define a connector opening and the first mounting end may be located in the first housing. The second housing may be located around the second mounting end.