Boeing

Reversible metal deposition devices are presented. A reversible metal deposition device comprises a transparent conductive electrode, a counter electrode, an electrolyte between the transparent conductive electrode and the counter electrode, a stripping additive in the electrolyte, and metal salt in the electrolyte that supplies metal to be reversibly deposited onto the transparent conductive electrode. The electrolyte contains less than 5 atomic percent water. The stripping additive comprises at least one of an acid or a base.

A locking assembly to position one or more arms that are configured to be mounted to a work station to selectively lock a service cart at the work station in a cabin area of an aircraft. The locking assembly has an actuator with a body configured to connect to and move relative to the work station. A visual indicator is mounted to the work station with the visual indicator having a first visual appearance when the actuator is at a first position and a second visual appearance when the actuator is at the second position. A linkage has an elongated shape with a first end section connected to the one or more arms and a second end section connected to the actuator with the linkage configured to transfer force from the rotating actuator to the one or more arms and sized to space the actuator away from the one or more arms.

A regulated power supply system, an integrated system, and a method are disclosed for providing regulated electrical power to an electrical load from a battery group. In an example, the regulated power supply system includes a buck regulator operable to regulate an unregulated voltage provided at an unregulated high-side interface of the battery group to a regulated voltage at a regulated high-side interface to which an electrical load can be connected. The buck regulator is configured to command a high-side driver to pass electrical energy to an inductor via the unregulated high-side interface during an on phase of a duty cycle during which the inductor is charged. The buck regulator is further configured to discontinue passing the electrical energy to the inductor during an off phase of the duty cycle.

There is provided a leading edge protection system for a leading edge of a composite structure of an air vehicle. The leading edge protection system includes an automated brush plating system having a metal electrode plating brush, a wear-resistant metallic plating solution, and a direct current power supply. A leading edge surface has exposed carbon filaments that are conductive. The wear-resistant metallic plating solution is applied to the leading edge surface to obtain a wear-resistant metallic coating on the leading edge surface. The leading edge protection system further includes an automated cold spray system having a cold spray gun with a chamber for a conductive metallic sprayable powder, and having a supersonic spray nozzle. The automated cold spray system further includes an electrically heated process gas, and an electrical power supply. The conductive metallic sprayable powder is sprayed directly over the wear-resistant metallic coating, to obtain a conductive metallic coating.

A nacelle inlet for an engine. The nacelle inlet includes an inner flow surface, an outer flow surface, and a turbulator segment positioned along the inner flow surface. The turbulator segment extends outward beyond the inner flow surface and is configured to transition laminar airflow along the inner flow surface upstream from the turbulator segment to turbulent airflow downstream from the turbulator segment.

Systems and methods of determining taxiing of an aircraft (20) with multiple engines (30). The systems can include a database (52) operational to store collected historical data (61) about conditions that affect one or more engine characteristics with the one or more engine characteristics comprising fuel usage, engine wear, noise, emissions, and effect on related aircraft systems. A computing device (51) is in communication with the database and is operational to: train a machine learning model (53) using the historical data; determine an expected outcome of the engine characteristics for each of the engines; and determine which of the one or more engines to not use during taxiing of the aircraft.

A method for layup and analysis of composite material during fabrication of a composite workpiece includes laying up a layer of the composite material for the composite workpiece based on design data for the layer and detecting as-built data for the layer using a quality detection device. Next, processing the as-built data for the layer to determine as-built fiber volume fill characteristics of the layer. Then, the method includes comparing the as-built fiber volume fill characteristics to as-planned fiber volume fill characteristics based on the design data for the layer to determine projected fiber volume fill ratios for the layer. An automated system for layup and analysis of composite material during fabrication of a composite workpiece includes at least one analytical computing device, a robotic manipulator, a layup mandrel and a quality detection device.

Induction welding monitoring systems and methods of use are presented. The induction welding monitoring system comprises an electromagnetic field (EMF) sensor array extending the length of a weld interface, the EMF sensor array comprising a plurality of sets of sensors, a multichannel oscilloscope, and a switching system connecting the EMF sensor array to the multichannel oscilloscope and configured to switch between sets of sensors of the plurality of sets of sensors.

Methods for layup and analysis of composite materials during fabrication of composite workpieces are disclosed. For example, the method includes: (1) receiving design data for the layup of the composite material, the composite workpiece decomposed into multiple design zones, the design data including localized zone data for the multiple design zones; (2) processing the design data for multiple layers of the composite workpiece to determine as-planned fiber volume fill characteristics for the design zones of each layer individually and for the multiple layers collectively; (3) laying up a layer of the composite material for the composite workpiece based on the localized zone data; and (4) detecting as-built data for the layer using a quality detection device, the as-built data divided into an as-built grid structure that includes as-built grid cells. Automated systems for layup and analysis of composite materials during fabrication of composite workpieces are also disclosed.

A method for aircraft (1110, 1202) management. Image data (1132) is received for areas of an aircraft (1110, 1202) that include deployment zones (1102) for overhead bins (151, 1101) in the aircraft (1110, 1202). The deployment zones (1102) are physical volumes that each overhead bin (1104, 1221, 1222, 1223, 1224) moves through and occupies as the overhead bin (1104, 1221, 1222, 1223, 1224) is opened. At least one of an opening or a closing of the overhead bins (151, 1101) is identified using the image data (1132) to form overhead bin usage data (1171). The overhead bin usage data (1171) is stored in a data collection (1134). The data collection (1134) is analyzed to determine a number of actions (1126) to perform for the aircraft (1110, 1202).