Abstract: A cargo handling system that utilizes a distributed antenna system for a cargo bay or compartment is disclosed. A cargo deck within the cargo bay may incorporate a plurality of power drive units. A mobile cargo controller may wirelessly communicate with the distributed antenna system to control movement of a ULD into/out of/within the cargo bay. A base station may be operatively interconnected with both the distributed antenna system and the plurality of power drive units (e.g., directly or indirectly via a control system, such as a control panel).

Abstract: A cable tensioning capstan assembly comprises a capstan drum and at least a first traction flange. The capstan drum may be configured to support a cable (e.g., a cable is configured to wrap around the capstan drum), and the capstan drum may be configured to rotate about an output axis. The first traction flange may be disposed adjacent the first axial end of the capstan drum and configured to rotate about the output axis. In various embodiments, the first traction flange is independently rotatable relative to the capstan drum. A clutch assembly between an input shaft and the first traction flange may facilitate the independent rotatability of the first traction flange.

Abstract: A biasing system for an actuator. The system includes a lock sleeve, a lock shaft, a tine having a tine finger extending along a longitudinal axis, a biasing member and a biasing spring. The biasing member and biasing spring are configured to maintain a position of the tine finger away from the longitudinal axis in the direction of the lock sleeve when the lock shaft and the lock sleeve are deployed, in use, such that, when the lock sleeve is returned, the tine finger is biased against the lock sleeve to prevent the lock sleeve from returning to a locked position before the lock shaft is able to return to a locked position.

Abstract: A cargo restraint system comprises a plurality of cargo restraint assemblies. Each cargo restraint assembly in the plurality of cargo restraint assemblies may be removably coupled to a cargo deck in various configurations. The plurality of cargo restraint assemblies may be reconfigurable based on a size of a plurality of unit load devices (ULDs) to be loaded and restrained. Each cargo restraint assembly may restrain four or fewer corners of respective ULDs simultaneously.

Abstract: A method is provided for monitoring a health of gasket sealing between components. The method includes determining, by a controller, an effective resistance value for a gasket between two components. The method further includes, responsive to the effective resistance value being greater than a first resistive value range of and a second resistive value range, transmitting, by the controller, an indication that the gasket needs to be replaced.

Abstract: A method is disclosed here. The method includes receiving an input from an aircraft, determining a towing status of the aircraft based on the input, and sending a message to a transmitter to transmit the towing status of the aircraft. Also disclosed herein is a system including an aircraft including a nose landing gear, a first controller, and a transmitter, wherein the first controller is configured to determine a towing status of the aircraft based on a number of sensor signals received from the aircraft, and the transmitter is configured to transmit the towing status and a tow truck configured to tow the aircraft, the tow truck including a second controller and a receiver, wherein the receiver is configured to receive the towing status from the transmitter, and the second controller is configured to provide an indication of the towing status of the aircraft.

Abstract: A bushing for use in an aircraft includes a hollow cylindrical shaft having a first end and a second end opposite the first end, a radially outwardly extending flange disposed at the first end of the hollow cylindrical shaft, an entry way disposed along the radially outwardly extending flange, and a lubrication passageway fluidly coupled to the entry way. The lubrication passageway extends between the first end and the second end.

Abstract: A method for estimating the brake wear of a brake installed in a vehicle is described herein, comprising acquiring an initial mass of the brake; quantifying the amount of energy that is being dissipated by the brake over a first time period, measuring a temperature increase of the brake over the first time period; estimating the brake mass based on the amount of dissipated energy and the temperature increase; and comparing the initial mass of the brake with the estimated brake mass and estimating the brake wear based on this comparison. The method for brake wear estimation may use indirect or direct methods for quantifying the amount of energy that is dissipated. A system for estimating brake wear and performing this method is also described.

Abstract: A heated floor panel may comprise a base assembly and a heating element located on a first surface of the base assembly. A panel skin may be located over the heating element and the first surface of the base assembly. The panel skin may extend from the first surface of the base assembly to a second surface of the base assembly opposite the first surface of the base assembly.

Abstract: A system for extracting energy for landing gear retraction may comprise a wheel pump rotationally coupled to a wheel via a pinion gear. A landing gear control valve assembly may be fluidly coupled to an output of the wheel pump. A secondary pump may be fluidly coupled to the landing gear control valve assembly, and an electric motor may be operationally coupled to the secondary pump.

Abstract: An actuator system includes a motor and an actuator positioning member to be driven by the motor from a start position to an actuated position. The system also includes a harmonic drive assembly between the motor and the actuator positioning member arranged to transfer torque from the motor to the actuator positioning member at a gear ratio of greater than 1:1. The system further includes means for disconnecting the harmonic drive assembly in response to failure of the motor and/or torque transfer such as to allow the positioning member to return to the start position.

Abstract: An autonomous search light system for being mounted to an aircraft includes a search light for emitting an adjustable light output; an RF receiver with at least two RF antennas for receiving RF signals emitted by an RF transmitter; and a controller for determining a position of the RF transmitter in relation to the search light from the received RF signals and for controlling the search light based on the determined position of the RF transmitter.

Abstract: Systems and methods for casting solid propellants include a mandrel for forming geometric features in a perforation of a propellant grain. In various embodiments, the mandrel includes a frangible portion that is removed from the propellant grain after the propellant grain has cured around the mandrel. A second portion of the mandrel may be left behind in the propellant grain. The mandrel may include a support structured disposed in the through hole of the mandrel. The support structure may include a plurality of longitudinal channels for directed exhaust gasses through the mandrel upon ignition of the propellant grain.

Abstract: A de-icing assembly for a surface of an aircraft includes: a carcass with a first layer, a second layer, and a carcass centerline and a plurality of seams sewn into the carcass, wherein the plurality of seams join the first and second layers of the carcass together. The assembly includes a plurality of inflation passages formed by the plurality of seams and disposed between the first and second layers of the carcass. The system also includes a manifold fluidly connected to and disposed beneath the carcass, the manifold comprising a width and a manifold centerline oriented approximately perpendicular or parallel to the carcass centerline. The seams are sown by a stitchline formed of carbon nanotube yarn.

Abstract: An ice protection system may comprise an electrical heating mat of an electrically resistive material, wherein the electrically resistive material defines at a first spanwise zone and a first chordwise zone, wherein at least one of the first spanwise zone or the first chordwise zone include a first busbar portion contiguous with the electrically resistive material.

Abstract: A torque transfer assembly comprising a drive shaft and a driven shaft and a dielectric insert arranged to be positioned between the drive shaft and the driven shaft, the insert assembly comprising a body of dielectric material shaped to form an insulating layer and configured to engage, respectively, with a first shaped engagement feature on the drive shaft and a second shaped engagement feature on the driven shaft, in torque transfer engagement, the insulating layer providing a dielectric barrier between the drive shaft and the driven shaft.

Abstract: An aircraft passenger cabin light. The light has: an elongated shape having a longitudinal direction (L) comprises: a cabin wall illumination assembly, which extends along the longitudinal direction (L) of the aircraft passenger cabin light and which is configured for illuminating a portion of a wall of an aircraft passenger cabin; and a plurality of personal reading light units for providing personal reading light illumination to passengers. The plurality of personal reading light units are arranged in an array extending along the longitudinal direction (L) of the aircraft passenger cabin light Said array is arranged along the cabin wall illumination assembly.

Abstract: A system for repositioning rails in a cargo bay of an aircraft. The system includes a base configured to be coupled to a structure in the cargo bay and having a first side and a second side. The system further includes a cradle for receiving a rail for restricting movement of a unit load device (ULD) in at least one direction, the cradle configured to position the rail between a first position and a second position in which the rail is closer to the second side of the base than when the rail is in the second position.

Abstract: A method for controlling brake assemblies of a vehicle is provided. Responsive to identifying a locked wheel protection event for a first wheel of a paired set of wheels on the vehicle, where the paired set of wheels is the first wheel on one side of the vehicle and a second wheel on an opposite side of the vehicle, a first brake pressure to a first brake assembly associated with the first wheel is released to zero pounds per square inch (PSI) and a second brake pressure to a second brake assembly associated with the second wheel of the paired set of wheels is reduced by a predetermined amount thereby reducing a yaw effect to the vehicle.

Abstract: Systems and methods for antiskid brake control include a brake control unit (BCU) configured to generate a brake command signal adjusted for a wide range of brake coefficient of friction based upon a real-time aircraft kinetic energy value. A method for antiskid brake control includes receiving, by a BCU, an aircraft mass and a wheel speed signal. The BCU determines an aircraft speed based upon the wheel speed signal and calculates the aircraft kinetic energy using the aircraft speed and aircraft mass. One or more antiskid parameters (e.g., proportional gain, a derivative gain, and/or deceleration target value) are adjusted based upon the aircraft kinetic energy to generate, by the brake control unit, an optimal antiskid brake command signal.