A wheel assembly includes a wheel portion comprises a web having an inboard surface. The web may define a torque bar retention slot that extends from the inboard surface of the web. The wheel assembly may also include a bushing disposed in the torque bar retention slot, wherein the bushing comprises an open end and a closed end. Still further, the wheel assembly may include a torque bar coupled to the wheel, and the torque bar may include a boss extending into the bushing through the open end of the bushing such that the boss of the torque bar is at least partially disposed within the torque bar retention slot of the wheel portion.

Systems and methods are disclosed for predicting a hot spot. One method comprises receiving, by a hot spot prediction system, vehicle characteristics associated with a vehicle and traffic data. Then the hot spot prediction system determines a hot spot and an estimated arrival time at the hot spot based on the vehicle characteristics and the traffic data. Following the determination, an auto brake application system receives the hot spot and the estimated arrival time and determines a safe stop time based on the vehicle characteristics, the hot spot and the estimated arrival time. The auto brake application system then sends a notification to the vehicle based on determining that the vehicle can stop within the safe stop time, and performs an action in response to receiving a confirmation from the vehicle.

A rim for a braked aircraft wheel includes an outer circular portion whose ends are terminated flanges for receiving a tire. The outer circular portion is connected by a wheel disk to a hub for fitting on an undercarriage axle in order to rotate about an axis of rotation coinciding with a central axis of the rim. The rim is designed to receive the tire on the outside of the outer circular portion and a brake on the inside of the outer circular portion, the outer circular portion presenting on one side of the wheel disk that is to receive the brake, in a plane containing the central axis of the wheel, a profile that has two slopes forming non-zero angles with the central axis, the two slopes extending in the continuation of one another from the wheel disk to the corresponding flange and flaring towards said corresponding flange.

Systems and method for an electrical system on an aircraft are provided. In example embodiments, the electrical system can be for an aircraft having a turbine engine. The turbine engine having a high pressure (HP) spool and a low pressure (LP) spool. The HP spool can be configured to drive a first generator to provide a first electrical output. The LP spool can be configured to drive a second generator to provide a second electrical output. The first generator and the second generator can be coupled to an electrical power distribution bus that provides electrical power to a load. A hybrid electric propulsion system and a secondary aircraft systems bus can both be coupled to the electrical power distribution bus. The electrical system can further include a control system configured to allocate power among the first generator, the second generator, and the hybrid electric propulsion system, and the secondary aircraft systems bus.

A voltage controlled aircraft electric propulsion system includes an electric propulsion system. The voltage controlled aircraft electric propulsion system may include electric propulsors providing thrust for the aircraft. In hybrid systems, a gas turbine engine may also be included. The electric propulsion system may include at least one electric generator power source, at least one propulsor motor load, and at least one stored energy power source, such as a battery. The propulsor motor load may be supplied power from a power supply bus. The voltage of the power supply bus may be adjusted according to an altitude of the aircraft while maintaining a substantially constant current flow to the propulsor motor load. Due to the adjustment to lower voltages at increased altitude, insulations levels may be lower.

A lighting system of an aircraft cabin includes a plurality of light units disposed at a plurality of locations within the aircraft cabin, wherein each of the plurality of light units includes at least one infrared light source, with an emission of infrared light across the aircraft cabin resulting from an operation of the at least one infrared light source of the plurality of light units.

A system and method of controlling operation of a host device in real-time, the host device operatively connected to an optical device and a radar device. The optical device is configured to obtain visual data of at least one object. The object is located at an incline, relative to the host device, the incline being characterized by an elevation angle () and an azimuth angle (). The radar device is configured to obtain radar data, including a radial distance (r) of the object from the host device, the azimuth angle (), and a range rate (dr/dt). The controller is programmed to determine a time-to-contact for the host device and the object based at least partially on a 3-D position and 3-D velocity vector. The operation of the host device is controlled based at least partially on the time-to-contact.

A lighting device is provided that has a light source arrangement with a plurality of semiconductor-based light sources in the form of light-emitting diodes. The light sources are bundled or collimated such that they each emit light in differently directed light cones with adjacent light cones overlapping. The lighting device has an adjusting device for adjustment of the direction of illumination and an actuating circuit connected to the adjusting device. The adjusting device adjusts intermediate stages for which the light-emitting diodes of adjacent and overlapping light cones operate and with varying light intensity in such a way the focal point of the light field produced by the light-emitting diodes lies between the focal points of adjacent light cones.

An electric propulsion system includes at least one generator. The electric propulsion system also includes at least one drive engine coupled to the at least one generator. The electric propulsion system further includes at least one electrical device. The electric propulsion system also includes at least one battery integrated isolated power converter (BIIC), where the at least one generator and at least one of the at least one BIIC and the at least one electrical device are coupled, and where the at least one BIIC and the at least one electrical device are coupled.

A system method for detecting taillight signals of a vehicle using a convolutional neural network is disclosed. A particular embodiment includes: receiving a plurality of images from one or more image-generating devices; generating a frame for each of the plurality of images; generating a ground truth, wherein the ground truth includes a labeled image with one of the following taillight status conditions for a right or left taillight signal of the vehicle: (1) an invisible right or left taillight signal, (2) a visible but not illuminated right or left taillight signal, and (3) a visible and illuminated right or left taillight signal; creating a first dataset including the labeled images corresponding to the plurality of images, the labeled images including one or more of the taillight status conditions of the right or left taillight signal; and creating a second dataset including at least one pair of portions of the plurality of images, wherein the at least one pair of portions of the plurality of the images are in temporal succession.