Abstract: The present disclosure relates to an apparatus (e.g., a data processing apparatus) for planning a route of a vehicle. The apparatus is configured to: determine a trajectory solution TS1, TS2 for the vehicle based on: one or more objective parameters; at least one scenario SN, S1, S2 defined by one or more constraint parameters relating to the vehicle and/or to a journey the vehicle is to make; and at least one situation N, ET, ER which the vehicle could experience while making the journey. The present disclosure also relates to a computer-implemented method for planning a route of a vehicle.

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 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: 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: 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: 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.