A sensor array system includes a skin. The sensor array system includes a lattice network coupled to a portion of the skin. The lattice network includes a plurality of interconnects and a plurality of nodes. The plurality of nodes are respectively defined by an intersection of two or more interconnects of the plurality of interconnects. The sensor array system includes a first sensor electrically connected to the lattice network at a first node of the plurality of nodes.

A control system for a gas turbine engine is disclosed. In embodiments, control system includes a controller and a high speed recorder. The controller obtains a sensor value from a sensor connected to the gas turbine engine and publishes a tag that includes the type of event, the sensor value, and a timestamp. The high speed recorder checks the tag for an overspeed event. If an overspeed event is detected, the high speed recorder records values provided by the tag.

A method and apparatus for processing fuselage sections. The apparatus comprises a cradle system, a metrology system, and a controller. The cradle system holds a first fuselage section and applies forces to the first fuselage section to change a current shape of the first fuselage section. The metrology system makes measurements of the current shape of the first fuselage section. The controller receives the measurements from the metrology system, identifies the forces needed to change the current shape of the first fuselage section towards a desired shape for connecting the first fuselage section to a second fuselage section, and sends commands to the cradle system to apply the forces to change the current shape of the first fuselage section towards the desired shape.

A manufacturing method includes deriving, from statistic data, a representative value of a clearance provided between first and second workpieces, executing a first insertion process, and executing a second insertion process. The statistic data is obtained from measuring the clearance. The executing the first insertion process includes testing insertion of a tolerance shim into the clearance when the representative value is less than a tolerance of the clearance, and testing insertion of a double-tolerance jig into the clearance when the tolerance shim is insertable into the clearance. The executing the second insertion process includes testing insertion of a difference shim into the clearance when the representative value is greater than the tolerance, testing insertion of a representative shim into the clearance when the difference shim is insertable into the clearance, and testing insertion of an addition jig into the clearance when the representative shim is insertable into the clearance.

A clamp installation apparatus includes a robot arm pedestal having a rotary table; a robot arm installed on the rotary table of the robot arm pedestal and having a plurality of arms and a plurality of joints; a robot hand installed to a forefront arm of the plurality of arms; and a control device. The robot hand includes: a clamp holding section configured to hold the clamp; a fastening section configured to fasten an engaging section of the clamp to give a clamp force to a work; and a measuring section configured to collect position data of a predetermined member of the clamp. The clamp can be automatically installed and removed. Also, the heat curing can be carried out in the condition to have installed the clamp.

A method for monitoring a condition of a VTOL-aircraft (1), preferably an electrically propelled, more particularly an autonomous, more particularly a multi-rotor aircraft, with a plurality of spatially distributed actuators (2i, 2o), preferably propulsion units, wherein a primary control (4.1) is used for controlling a flight state of the VTOL-aircraft (1) and at least one secondary control (4.2) is used for controlling the actuators (2i, 2o) of the VTOL-aircraft (1), preferably the propulsion units (2i, 2o); during operation. The primary control (4.1) generates a primary data set, which is subject to a first uncertainty, and is entered into an estimation algorithm, and the secondary control generates a secondary data set, which is subject to a second uncertainty, and is also entered into the estimation algorithm. The estimation algorithm processes the primary and secondary data sets and generates an estimation result that is representative of a condition of the VTOL-aircraft (1), preferably a health status of at least one actuator (2i, 2o), which estimation result is subject to a third uncertainty that is equal to or lower than the first uncertainty and/or the second uncertainty.

This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of a component, such as a battery pack, a motor controller, and/or a motors. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

The present disclosure provides an aircraft engine graphical diagnostic tool, as well as a method and electronic device for operating the same. The graphical diagnostic tool comprises an input element configured for obtaining a data value for a first data dimension, and a visualization element having at least two dimensions. The visualization element is configured for presenting a dataset for at least second and third data dimensions associated with the first data dimension. The dataset presented by the visualization element is selected based on the data value for the first data dimension.

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.

An aircraft vibration detecting device applicable to an aircraft having a moving surface to be driven by an actuator includes a difference calculating unit for calculating a difference between a target value of an angle of the moving surface and an actual measured value of the angle of the moving surface, a threshold value determining unit for determining whether an absolute value of the difference is equal to or greater than a threshold value, and a vibration determining unit for determining that the moving surface is vibrating if the absolute value of the difference is equal to or greater than the threshold value.