Abstract: Disclosed are devices and methods, among which is a device peripheral to a controller device that is used to provide memory access to the controller device. In some embodiments, the device may determine and provide a response of the device to requests from the separate device.

Abstract: Disclosed are methods and devices, among which is a device that uses a memory map to identify whether functionality of the device should be implemented. The device may be coupled to a separate device, and, in some embodiments, the device may determine and provide a response of the device to requests from the separate device.

Abstract: Disclosed are methods and devices, among which is a device that uses a memory map to identify whether functionality of the device should be implemented. The device may be coupled to a separate device, and, in some embodiments, the device may determine and provide a response of the device to requests from the separate device.

Abstract: A method of determining a fuel delivery fault in a gas turbine engine is provided, the engine having a combustor, a combustor fuel system for delivering fuel to the combustor, and a turbine which is driven by hot gas from the combustor. The method includes comparing a measured turbine gas temperature profile against a predicted turbine gas temperature profile. The method further includes comparing a measured fuel delivery flow number of the combustor fuel system against a predicted fuel delivery flow number of the combustor fuel system. The method further includes indicating that a fuel delivery fault in the combustor fuel system has been detected when both the measured turbine gas temperature profile and the measured fuel delivery flow number differ from their predicted values by more than respective predetermined thresholds.

Abstract: A method of determining a fuel delivery fault in a gas turbine engine is provided, the engine having a combustor, a combustor fuel system for delivering fuel to the combustor, and a turbine which is driven by hot gas from the combustor. The method includes comparing a measured turbine gas temperature profile against a predicted turbine gas temperature profile. The method further includes comparing a measured combustor instability against a predicted combustor instability. The method further includes indicating that a fuel delivery fault in the combustor fuel system has been detected when both the measured turbine gas temperature profile and the measured combustor instability differ from their predicted values by more than respective predetermined thresholds.

Abstract: Disclosed are methods and devices, among which is a device including a self-selecting bus decoder. In some embodiments, the device may be coupled to a microcontroller, and the self-selecting bus decoder may determine a response of the peripheral device to requests from the microcontroller.

Abstract: Disclosed are methods and devices, among which is a device including a self-selecting bus decoder. In some embodiments, the device may be coupled to a microcontroller, and the self-selecting bus decoder may determine a response of the peripheral device to requests from the microcontroller. In another embodiment, the device may include a bus translator and a self-selecting bus decoder. The bus translator may be configured to translate between signals from a selected one of a plurality of different types of buses. A microcontroller may be coupled to a selected one of the plurality of different types of buses of the bus translator.

Abstract: An asset operational health monitoring system, in which a plurality of sensors are arranged to determine values of asset operation parameters pertaining to an instance of asset operation. One or more processing unit receives data corresponding to said asset operation values and determine a plurality of asset locations at a corresponding plurality of points in time. The one or more processing unit is arranged to receive data indicative of the location of a region of adverse environmental conditions which may impact on the operation of the asset and to compare the determined locations of the asset with the location of said region so as to determine whether one or more of said asset locations fall within said region. An indicator of operational risk associated with the presence of said asset in said region is output which can drive asset operation or maintenance decision making. The system may be used for ash cloud impact monitoring for aircraft, a fleet of aircraft or aircraft engines.

Abstract: An asset operational health monitoring system, in which a plurality of sensors are arranged to determine values of asset operation parameters pertaining to an instance of asset operation. One or more processing unit receives data corresponding to said asset operation values and determine a plurality of asset locations at a corresponding plurality of points in time. The one or more processing unit is arranged to receive data indicative of the location of a region of adverse environmental conditions which may impact on the operation of the asset and to compare the determined locations of the asset with the location of said region so as to determine whether one or more of said asset locations fall within said region. An indicator of operational risk associated with the presence of said asset in said region is output which can drive asset operation or maintenance decision making. The system may be used for ash cloud impact monitoring for aircraft, a fleet of aircraft or aircraft engines.

Abstract: A method and apparatus for detecting an abnormality in e.g. in operating characteristics or function of a machine, apparatus or system, the method including providing a data sample set comprising n values of a measured physical parameter associated with the apparatus or system generated by repeating a measurement of the physical parameter n times. An extremal measured parameter value is selected from amongst the data sample set, determining a probability of observing the selected parameter value (e.g. of observing a value not exceeding the selected parameter value) by applying the selected parameter value to an extreme value probability distribution function having a location parameter and a scale parameter. The value of the location parameter and the value of the scale parameter are each constructed using an integer value m (e.g. notionally representing the size of a sub-sample data set comprising m of said measured parameter values) in which m is less than n (i.e. m<n).

Abstract: A method and apparatus for detecting an abnormality in e.g. in operating characteristics or function of a machine, apparatus or system, the method including providing a data sample set comprising n values of a measured physical parameter associated with the apparatus or system generated by repeating a measurement of the physical parameter n times. An extremal measured parameter value is selected from amongst the data sample set, determining a probability of observing the selected parameter value (e.g. of observing a value not exceeding the selected parameter value) by applying the selected parameter value to an extreme value probability distribution function having a location parameter and a scale parameter. The value of the location parameter and the value of the scale parameter are each constructed using an integer value m (e.g. notionally representing the size of a sub-sample data set comprising m of said measured parameter values) in which m is less than n (i.e. m<n).

Abstract: This invention relates to a method and apparatus for reducing vibration of a helicopter fuselage. The apparatus comprises a plurality of actuators interconnecting parts of the helicopter structure capable of relative motion at an exciting frequency, means to continuously oscillate the actuators at a frequency corresponding to the exciting frequency, a plurality of accelerometers attached to the fuselage for generating signals representative of fuselage dynamic accelerations, and processing means for processing said signals and providing output signals for controlling the phase and magnitude of operation of the actuators. In a described embodiment, one of the relatively movable parts comprises a raft structure carrying the gearbox and engines and attached to the fuselage by a resilient attachment adjacent each of its four corners.

Abstract: A vibration absorber for a helicopter rotor includes a hub portion, a mass portion encircling the hub portion and a plurality of resilient arms extending in a spaced-apart spiral pattern between the hub and the mass. In operation, the hub portion of the vibration absorber is mounted on a helicopter rotor so as to be rotated with the rotor about an axis of rotation of the rotor, the resilient arms ensuring that the mass is capable of equal resilient deflection in any direction within its plane of rotation whereby the vibration absorber simultaneously reduces in-plane vibration forces of different frequencies.

Abstract: A vibration absorber includes a hub arranged for rotation during operation about an aixs, a mass encircling the hub and a plurality of resilient arms extending in a spaced-apart spiral pattern between the hub and the mass so that the mass rotates with the hub in a plane of rotation perpendicular to the axis and is capable of equal resilient deflection in any direction within its plane of rotation. In operation the absorber operates as a spring mass device and finds particular application in damping vibrations in a helicopter rotor due to the facility to simultaneously cancel vibration forces of different frequencies.