A method of determining the position and orientation of a moveable object includes a) connecting a plurality of targets to the object at known points on the object such that the targets will move with the object; b) scanning the surface of the object and at least some of the plurality of targets to obtain target data; c) comparing the scanned target data to at least one known dimension of one of the plurality of targets; and d) if scanned target data matches the at least one known dimension of one of the plurality of targets, mapping known object model data according to the target data to determine the position and orientation of the object.

An advisory system of a vessel that monitors variables of a vessel system inclusive of systems and subsystems that are used to operate the vessel. The advisory system may use machine-learning to learn from an operator (i) whether or not two variables are related to one another, and (ii) likelihood that a variable will reach a threshold, and, optionally, time until reaching the threshold. The system may receive operator feedback (i) to indicate whether the two variables are related to one another, and (ii) whether a behavior of the variable is normal or not normal. Thereafter, if a determination that the same two variables are related to one another and behaving in a similar manner, provide notification to the operator of the behavior. In response to determining that the variable is behaving (e.g., trending) in a similar manner that is not normal, providing a notification to the operator.

A pressure bulkhead assembly for an aircraft includes an aft pressure bulkhead and a plurality of splice angles. The aft pressure bulkhead includes a bulkhead interface surface and aft-pressure-bulkhead holes, pre-drilled through the bulkhead interface surface. The plurality of splice angles is configured to be coupled to the aft pressure bulkhead. Each one of the plurality of splice angles includes a flange surface, configured to mate with the bulkhead interface surface. Each one of the plurality of splice angles also includes splice-angle holes, drilled through the flange surface. Each one of the plurality of splice angles further includes a splice surface, extending from the flange surface. With the splice-angle holes aligned with the aft-pressure-bulkhead holes, a plurality of splice surfaces forms a circumferential splice surface with an optimized shape.

A method and system for processing parameter values from a redundant sensor configured to sense a parameter used in the control of an aircraft engine is provided. The method includes: a) receiving a plurality of parameter values from a redundant sensor by sensing the same parameter at the same time; b) identifying mismatched parameter values; c) producing a predicted parameter value using an artificial intelligence (AI) model having a database of parameter values representative of the sensed parameter; d) providing the predicted parameter value to a control unit; and e) operating the control unit to select a first parameter value or a second parameter value using the predicted parameter for use in the control of the aircraft engine.

Computer-implemented methods for automatically generating an environmental control system health report of an aircraft. One method comprises receiving, automatically over an electronic network, flight data recorded during a flight, the flight data comprising a plurality of parameters of data collected from the aircraft during the flight; isolating a subset of the plurality of parameters of the flight data that relate to an environmental control system of the aircraft; analyzing the subset of the plurality of parameters of the flight data to identify a time window in which a pattern in the subset of the plurality of parameters of the flight data matches a known pattern of flight data corresponding to a flight condition; extracting, from within the identified time window, a sample of the subset of the plurality of parameters of the flight data; and generating an environmental control system health report for the aircraft based on the extracted sample of the subset of the plurality of parameters of the flight data.

The invention relates to an electronic assembly for peripheral devices such as sensors of an aircraft, comprising three generic interfaces differing from one another for coupling the assembly to at least one peripheral device and at least one digital evaluation unit, in particular arranged downstream, wherein the assembly is couplable to the peripheral device via at least one interface.

A platform assembly includes a work platform including a platform floor and a safety rail extending from the platform floor to a rail height, and a primary sensor unit secured to the work platform and positioned adjacent one of the platform floor and the safety rail. The primary sensor unit is configured to monitor an area from the platform floor or from the safety rail to a space above the rail height and forward and aft of the work platform. The platform assembly enhances protection for an operator from sustained involuntary operation resulting in an impact with an obstruction or structure.

Methods and systems for depicting avionics data anomalies in an aircraft. Time series data is received from the avionics data source, a future time is predicted when a first anomaly threshold will be crossed based on the time series data, and the future time when the first anomaly threshold will be crossed is depicted on a display device associated with the aircraft.

Systems and methods are provided for retrieving values from a data bus of a vehicle. One illustrative method includes applying values from sensors at a vehicle to addresses of a data bus at the vehicle, retrieving values from the addresses of the data bus based on an operational state of the vehicle, and determining that the vehicle has entered another operational state. The method further includes loading a second sampling scheme corresponding with the other operational state, and retrieving values from an address of the data bus at a new rate corresponding with the other operational state.

A method and 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.