Abstract: A system of an aircraft includes a thrust reverser control configured to control deployment of one or more thrust reversers of the aircraft, a brake control configured to control operation of one or more brakes of the aircraft, and a controller. The controller is configured to detect a landing condition of the aircraft, determine one or more thrust reverser deployment and brake control parameters for one or more current conditions at a target location of the aircraft, and control the one or more thrust reversers and the one or more brakes upon landing at the target location based on the one or more thrust reverser deployment and brake control parameters. The controller can modify one or more control parameters of the aircraft based on detecting a change in the one or more current conditions at the target location or a fault condition of the aircraft.

Abstract: An engine system of an aircraft includes a gas turbine engine comprising at least one spool and at least one electric machine operably coupled with the at least one spool. A controller is configured to detect if the at least one spool of the gas turbine engine is in or is approaching an overspeed condition and apply a load to the at least one spool via the at least one electric machine.

Abstract: A system of an aircraft includes one or more gas turbine engines and a controller. The controller is configured to detect a pre-takeoff condition of the aircraft and determine one or more control parameters for one or more current conditions at a target location of the aircraft. The controller is further configured to determine a final takeoff speed of the one or more gas turbine engines based on the one or more control parameters. At least one of the one or more gas turbine engines is controlled to accelerate to the final takeoff speed after transitioning from the pre-takeoff condition to a takeoff condition.

Abstract: A hybrid electric engine of an aircraft includes a compressor, a turbine operably connected to the compressor via a variable gear ratio gearbox and a combustor configured to drive the turbine via a flow of combustion products. An electric motor is operably connected to the variable gear ratio rear box and configured to input rotational energy into the gearbox. The input of rotational energy into the gearbox from the electric motor changes a rotational speed of one of the compressor or the turbine relative to the other of the compressor or the turbine.

Abstract: An engine system of an aircraft includes a gas turbine engine comprising at least one spool and at least one electric machine operably coupled with the at least one spool. A controller is configured to detect if the at least one spool of the gas turbine engine is in or is approaching an overspeed condition and apply a load to the at least one spool via the at least one electric machine.

Abstract: Examples described herein provide a computer-implemented method for managing battery usage for a hybrid electric engine of an aircraft. The method includes receiving a flight plan comprising flight plan data for a flight of an aircraft. The method further includes receiving battery data about a battery system of the aircraft. The method further includes determining waypoints for when to apply electric power from the battery system based at least in part on the flight plan data and the battery data. The method further includes controlling, based at least in part on the waypoints, an electric motor while the flight plan is executed. The method further includes updating, while the flight plan is executed, the waypoints based at least in part on data received during the flight.