Disclosed is a method of producing an assembly tool for assembling a first system comprising one or more components. The method comprises: for each component, determining, when the first system is attached to a second system, a position and orientation of that component relative to the second system and positions and orientations relative to the second system at which that component is to be supported; providing a frame; attaching, to the frame, a reference structure; providing a plurality of pickup devices each having a receiving element for receiving a component; and securing each pickup device to the frame such that a position and orientation relative to the reference structure of each receiving element is the same as a position and orientation at which a component is to be supported.

A control assembly for an aircraft system according to an example of the present disclosure includes a multi-core processor that has a plurality of cores coupled to a communications module and to an arbitration module. The communications module is operable to communicate information between the plurality of cores and one or more aircraft modules. The plurality of cores include first and second cores operable to concurrently execute a first discrete set of software instructions to generate respective instances of an output. The arbitration module is operable to communicate each and every one of the respective instances to control the one or more aircraft modules. A method of operating an aircraft system is also disclosed.

A fault detection circuit includes a system controller and a fault detection controller. The system controller includes at least one memory device to control at least one electrical system. The fault detection controller communicates with the system controller to detect at least one fault of the system controller and to control operation of the system controller based on comparison between a frequency of detected faults corresponding to the system controller and at least one frequency threshold value.

The invention relates to a method for controlling the restitution of alert(s) and/or of system(s) reconfiguration procedure(s), including the surveillance of device(s) of a vehicle and the determination of alert(s) and/or of associated reconfiguration procedure(s) to be restituted for the crew, the vehicle operating according to a mission carried out by using at least one operational capacity, and further including, for a current mission: obtaining a list of operational capacities required by said current mission; from said required operational capacities and at least one piece of information from an accessible database, controlling the restitution of alert(s) and/or of system(s) reconfiguration procedure(s) by: modifying the associated level of alert(s) and/or of procedure(s), and sequencing the restitution of alert(s) and/or of procedure(s) based on said level, and/or filtering said alert(s) and/or reconfiguration procedure(s) before restitution.

A method for designing a material for an aircraft component includes training a neural network to correlate microstructural features of an alloy with material properties of the alloy by at least providing a set of images of the alloy to the neural network. Each of the images in the set of images has varied constituent compositions. The method further includes providing the neural network with a set of determined material properties corresponding to each image, associating the microstructural features of each image with the set of empirically determined data corresponding to the image, and determining non-linear relationships between the microstructural features and corresponding empirically determined material properties via a machine learning algorithm, receiving a set of desired material properties of the alloy for aircraft component, and determining a set of microstructural features capable of achieving the desired material properties of the alloy based on the determined non-linear relationships.

In an example, a method for identifying associated events in an aircraft is described. The method includes obtaining sensor data, obtaining fault code data, generating a set of events, where each event occurs over a time interval over which either (i) the sensor data indicates an anomalous measurement or (ii) a fault code associated with a particular aircraft subsystem of the aircraft was signaled, calculating a value of statistical dependence between the set, based on the value exceeding a threshold, constructing a network representing the set as a sequence of related events and further representing a temporal order in which the sequence occurred, indexing, in a summary table stored in memory and separate from the sensor data and the fault code data, the sequence and the value, and controlling a display device to display the summary table and a visual representation of the network.

A robotic end effector includes a line painting system and a spray painting system for painting features on a surface. The line painting system includes a flexible wick for flowing lines onto the surface.

A vehicle management system includes an onboard vehicle system and a ground system. The onboard vehicle system includes a compressor exit temperature sensor configured to determine an ECS compressor exit temperature; a data acquisition unit coupled to receive the compressor exit temperature, an altitude of the first vehicle, and an ambient temperature and configured to generate a data report; and a communications system coupled to receive and transmit the data report. The ground system includes a ground data server coupled to receive the data report and determine a fouling condition of an environmental conditioning element of the ECS based on at least the compressor exit temperature, the altitude, and the ambient temperature; and a mobile application module coupled to receive the fouling condition from the ground data server and configured to provide an interface for displaying the fouling condition to a user on a mobile device.

A method for coupling a number of utilities between a first system and a second system is provided. A first interface that couples the number of utilities between the first system and the second system is created between the first system and a utilities unit. The first interface is activated. A second interface between the second system and the utilities unit is deactivated, while the first interface remains activated.

An apparatus for accessing an interior of a fuselage assembly. A tower having a number of platform levels may be driven into a selected tower position within an assembly area. The interior of the fuselage assembly may be accessed using the number of platform levels.