Abstract: Sensors, including time-of-flight sensors, may be used to detect objects in an environment. In an example, a vehicle may include a time-of-flight sensor that images objects around the vehicle, e.g., so the vehicle can navigate relative to the objects. Sensor data generated by the time-of-flight sensor can include returns associated with highly reflective objects that cause glare. In some examples, a depth of a sensed surface is determined from the sensor data and additional pixels at the same depth are identified. The subset of pixels at the depth are filtered by comparing a measured intensity value to a threshold intensity value for the depth. Other threshold intensity values can be applied to subsets of pixels at different depths.

Abstract: Approaches for fabricating one-dimensional metallization for solar cells, and the resulting solar cells, are described. In an example, a solar cell includes a substrate having a back surface and an opposing light-receiving surface. A plurality of alternating N-type and P-type semiconductor regions is disposed in or above the back surface of the substrate and parallel along a first direction to form a one-dimensional layout of emitter regions for the solar cell. A conductive contact structure is disposed on the plurality of alternating N-type and P-type semiconductor regions. The conductive contact structure includes a plurality of metal lines corresponding to the plurality of alternating N-type and P-type semiconductor regions. The plurality of metal lines is parallel along the first direction to form a one-dimensional layout of a metallization layer for the solar cell.

Abstract: A rotatable engine component, coating and method of coating the rotatable component includes a substrate, a transitional zone applied to the substrate, and an abradable zone applied to the transitional zone. During operation of an engine in a turbine, the abradable zone is consumed upon contact with a static portion of the engine preventing damage to the rotatable component.

Abstract: The method and the apparatus are concerned exclusively with dynamic processes that can be represented dominantly by discrete-event processes and for the dynamics of which it is not the time but rather the logical order of the symbols that is critical. The method and the apparatus cater to the specifics of discrete-event problems. The technical apparatus for designing and realizing automated reactions to the failure of actuators and sensors in discrete automation-engineering installations ensures that the effects of said failures on the process remain at a minimum, and also a method that allows said faults to be systematically integrated into discrete-event models in order to take this as a basis for carrying out formal design of fault-tolerant discrete-event controllers.

Abstract: A rotatable engine component, coating and method of coating the rotatable component includes a substrate, a transitional zone applied to the substrate, and an abradable zone applied to the transitional zone. During operation of an engine in a turbine, the abradable zone is consumed upon contact with a static portion of the engine preventing damage to the rotatable component.

Abstract: A coating system and process capable of providing erosion and corrosion-resistance to a component, particularly a steel compressor blade of an industrial gas turbine. The coating system includes a metallic sacrificial undercoat on a surface of the component substrate, and a ceramic topcoat deposited by thermal spray on the undercoat. The undercoat contains a metal or metal alloy that is more active in the galvanic series than iron, and electrically contacts the surface of the substrate. The ceramic topcoat consists essentially of a ceramic material chosen from the group consisting of mixtures of alumina and titania, mixtures of chromia and silica, mixtures of chromia and titania, mixtures of chromia, silica, and titania, and mixtures of zirconia, titania, and yttria.

Abstract: A multi-part cast component for a turbine engine includes a first component section having a main body portion including at least one cooling flow passage section, and a second component section having a main body including at least one cooling flow passage section. The first and second component sections are joined along a parting line to form a turbine engine component with the at least one cooling flow passage section of the first component section aligning with the at least one cooling flow passage of the second component section to form a cooling flow channel.