Ge Aviation Systems Limited

General Electric Company

Tod Alexander Gilbert

Steven Bonnett

Timothy Robert North

Techniques for employing a smart sensor device that has a primary sensing function for sensing a state of a physical component and can concurrently enable one or more backup functions for sensing one or more states of one or more other physicals components in response to one or more other smart sensor devices not being able to perform their primary function of sensing and/or reporting on the one or more states of the one or more other physical components.

Method and system for enabling component monitoring redundancy in a digital network of intelligent sensing devices

Techniques for employing a smart sensor device () that has a primary sensing function for sensing a state of a physical component and can concurrently enable one or more backup functions for sensing one or more states of one or more other physicals components in response to one or more other smart sensor devices (and/or) not being able to perform their primary function of sensing and/or reporting on the one or more states of the one or more other physical components.

Systems and techniques to facilitate generating and/or encoding rotational data associated with a mechanical element are presented. A sensor system can measure rotational speed data and phase data associated with a mechanical element that rotates. The sensor system can also encode the rotational speed data and phase data into a digital data packet. Furthermore, the sensor system can transmit the digital data packet associated with the rotational speed data and phase data to one or more sensor devices in communication with the sensor system.

Generating and/or encoding rotational data for a mechanical element over a digital network

Methods, apparatus, and articles of manufacture to identify and configure sensors are disclosed. Certain examples provide an apparatus including a processor and a communication interface. The example processor is configured to broadcast, using the communication interface, a request for sensor identification in a detection mode. The example processor is configured to receive, using the communication interface, sensor identification information. The example processor is configured to instruct, based on the sensor identification information, sensors to enter a monitoring mode to await a stimulus. The example processor is configured to receive, in response to a first stimulus applied to a first location, a first sensor response to the first stimulus from a first sensor. The example processor is configured to evaluate the first sensor response with respect to an expected sensor response. The example processor is configured to when the first sensor response satisfies a criterion, associate the first sensor with the first location.

Methods and systems to identify smart sensor locations by the application of physical stimulus

Systems and methods for determining aircraft component phase position are provided. In one embodiment, a method can include receiving a set of data from a data acquisition system associated with a component. The method can include identifying a plurality of phase reference points based, at least in part, on the set of data. Each phase reference point can be indicative of a phase position of the component relative to the data acquisition system at a respective point in time. The method can include generating a model based, at least in part, on the plurality of phase reference points. The model can be indicative of the phase position of the component relative to the data acquisition system at a plurality of times. The method can include determining the phase position of the component at one or more points in time based, at least in part, on the model.

Aircraft component monitoring system

Systems and methods for providing time reference synchronization for an aircraft are provided. In one embodiment, a method can include receiving, by one or more computing devices associated with a data acquisition system of an aircraft, a signal comprising time synchronization information, wherein the signal comprises a first signal portion and a second signal portion. The method can include filtering, by the one or more computing devices, the signal comprising the time synchronization information to distinguish the first signal portion and the second signal portion from noise associated with the signal. The method can include determining, by the one or more computing devices, the time synchronization information based at least in part on the first signal portion and the second signal portion. The method can include synchronizing, by the one or more computing devices, a set of data acquired by the data acquisition system with the time synchronization information.

Aircraft time synchronization system

A method of component monitoring for machinery having multiple rotating elements, which are rotated at different rotational speeds, the method including sampling data from the vibration sensor at a sampling frequency at least as great as the fastest rotational speed of the multiple rotating elements to form a data set and determining an actual rotational frequency for at least some of the rotating elements during the sampling of the data.

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Marlborough, United Kingdom

Tod Alexander Gilbert