Abstract: A computer-implemented method of enabling optimisation of derate for a propulsion system of a vehicle, the method comprising: determining a derate for the propulsion system of the vehicle using: an algorithm; a vehicle model defining path constraints for the vehicle through space; a propulsion system model defining parameters of the propulsion system; an objective function defining one or more objectives; and controlling output of the determined derate.

Abstract: A system and a method for determining a high oil consumption in a gas turbine engine of an aircraft are provided. The method includes determining one or more engine and aircraft conditions. The one or more engine and aircraft conditions includes at least one of an oil quantity, an oil temperature, an oil pressure, an engine speed, an aircraft altitude, and an aircraft attitude. The method further includes determining a trend in oil conditions based on at least the one or more engine and aircraft conditions. The trend in oil conditions provides at least one of a rate of consumption of oil or a time duration of remaining oil. The method further includes determining the high oil consumption based on a comparison of the trend in oil conditions with a threshold or a comparison model.

Abstract: A computer-implemented method of enabling optimisation of trajectory for a vehicle, the method comprising: determining a trajectory for the vehicle using: an algorithm; a vehicle model defining path constraints for the vehicle through space; a propulsion system model defining parameters of a propulsion system of the vehicle; an objective function defining one or more objectives; and controlling output of the determined trajectory.

Abstract: A computer-implemented method of enabling optimisation of derate for a propulsion system of a vehicle, the method comprising: determining a derate for the propulsion system of the vehicle using: an algorithm; a vehicle model defining path constraints for the vehicle through space; a propulsion system model defining parameters of the propulsion system; an objective function defining one or more objectives; and controlling output of the determined derate.

Abstract: A computer-implemented method for indicating damage to an aircraft, the computer-implemented method comprising: receiving data indicating an occurrence of damage to an aircraft and severity of the damage; determining information to present to an operator of the aircraft using the received data, the information being dependent on the severity of the damage; and controlling an output device to provide the determined information indicating the occurrence of damage to an operator of the aircraft.

Abstract: A computer-implemented method for determining damage to an aircraft, the computer-implemented method comprising: (i) receiving first data from a first sensor, the first data comprising values for a first parameter of an aircraft; (ii) determining whether damage has occurred to the aircraft using the values of the first data; (iii) receiving second data from a second sensor, the second data comprising values for a second parameter of the aircraft; (iv) determining whether damage has occurred to the aircraft using the values of the second data; and (v) controlling output of a signal comprising data indicating the occurrence of damage to the aircraft using an occurrence of damage determined at step (ii) and/or an occurrence of damage determined at step (iv).

Abstract: Computer-implemented methods for controlling the operation of aircraft, particularly electric or hybrid electric aircraft, are described. One such method, implemented on a Flight Management System (FMS) of an aircraft, comprises: receiving, by the FMS, weather data indicative of weather conditions around the aircraft; and selecting, by the FMS, based on the received weather data, one of a plurality of different pre-defined FMS profiles, each FMS profile corresponding to a different range of weather conditions and defining a different set of aircraft operating parameters. The aircraft may be flown under the control of the FMS using the selected FMS profile.

Abstract: Computer-implemented methods for controlling the operation of aircraft, particularly electric or hybrid electric aircraft, are described. One such method, which may be implemented on a Flight Management System of the aircraft, comprises: receiving weather data indicative of weather conditions between a flight origin and a flight destination of the aircraft; and determining, using a constrained optimization method and a weather data dependent aircraft energy usage model, a three-dimensional flight path for the aircraft from the origin to the destination. The constrained optimization method may determine a flight path constrained by, amongst other things the energy required by an Environmental Control System of the aircraft.

Abstract: Computer-implemented methods for controlling the operation of aircraft, particularly electric or hybrid electric aircraft, are described. One such method, which may be implemented on a Flight Management System (FMS) of the aircraft, comprises: obtaining flight path data for the aircraft, the flight path defining a three-dimensional path from an origin to a destination; receiving weather data indicative of weather conditions along the flight path; and determining an amount of energy required to fly the aircraft along the flight path. The determination uses an aircraft energy usage model whose inputs include the flight path data and the weather data. Based on the determination and a comparison with an amount of stored energy available to the aircraft, the FMS may validate the flight path for flight or reject the flight path.

Abstract: A system and a method for determining a high oil consumption in a gas turbine engine of an aircraft are provided. The method includes determining one or more engine and aircraft conditions. The one or more engine and aircraft conditions includes at least one of an oil quantity, an oil temperature, an oil pressure, an engine speed, an aircraft altitude, and an aircraft attitude. The method further includes determining a trend in oil conditions based on at least the one or more engine and aircraft conditions. The trend in oil conditions provides at least one of a rate of consumption of oil or a time duration of remaining oil. The method further includes determining the high oil consumption based on a comparison of the trend in oil conditions with a threshold or a comparison model.

Abstract: A vehicle simulator including: a base; a plurality of moveable components; and one or more physical and/or power connectors for coupling the components to the base. The components are positionable on the base with the connectors coupling the components to the base in a first arrangement to simulate a first vehicle type. The components are moveable to and positionable on the base with the connectors coupling the components to the base in a second arrangement different to the first arrangement to simulate a second vehicle type.

Abstract: The present disclosure relates to a compressor assembly for a gas turbine engine. The compressor assembly comprises a compressor having a compressor stage with a plurality of rotor blades mounted on the rim of a rotor disc within a core air flow path. There is a purge channel extending from a radially inner purge gas source to at least one radially outer outlet at the rim of the compressor stage. The purge channel comprises at least one swirl element and/or at least one orifice for swirling/deflecting a purge gas flowing within the purge channel. In use, a flow of purge gas exits the outlet(s) at least partly in the direction of the core air flow path.