An actuator system can include a first actuator, a second actuator, a first actuator control device configured to control the first actuator, a second actuator control device configured to control the second actuator, a shared redundant actuator control device, and at least one transfer device operatively connected to the first, second, and shared redundant actuator control devices. The at least one transfer device can be configured to be operated to select between a first control mode where the first actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator, a second control mode where the shared redundant actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator, and a third control mode where the first actuator control device is operatively connected to the first actuator to control the first actuator and the shared redundant actuator control device is operatively connected to the second actuator to control the second actuator.

An actuator system can include a first actuator, a second actuator, a first actuator control device configured to control the first actuator, a second actuator control device configured to control the second actuator, a shared redundant actuator control device, and at least one transfer device operatively connected to the first, second, and shared redundant actuator control devices. The at least one transfer device can be configured to be operated to select between a first control mode where the first actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator, a second control mode where the shared redundant actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator, and a third control mode where the first actuator control device is operatively connected to the first actuator to control the first actuator and the shared redundant actuator control device is operatively connected to the second actuator to control the second actuator.

A hybrid-electric propulsion system for an aircraft includes a turbomachine, the turbomachine including a first spool and a second spool. A method for operating the hybrid electric propulsion system includes operating, by one or more computing devices, the turbomachine such that the first spool mechanically drives a prime propulsor of the hybrid-electric propulsion system; and modifying, by the one or more computing devices, a speed relationship parameter defined between the first spool and second spool by providing electrical power to, or drawing electrical power from, an electric machine mechanically coupled to the first spool, the second spool, or both.

An aspect includes a method for motoring control for multiple engines of an aircraft is provided. A controller can determine a motoring time of a first engine starting system to cool a first engine. The controller can compare the motoring time of the first engine starting system with a motoring time of one or more other engine starting systems of one or more other engines of the aircraft. The motoring time of the first engine starting system can be controlled relative to a tolerance of the motoring time of the one or more other engine starting systems by adjusting the motoring time of the first engine starting system relative to the one or more other engine starting systems in a motoring sequence based on comparing the motoring time of the first engine starting system with the motoring time of the one or more other engine starting systems.

An aspect includes a method for motoring control for multiple engines of an aircraft is provided. A controller can determine a motoring time of a first engine starting system to cool a first engine. The controller can compare the motoring time of the first engine starting system with a motoring time of one or more other engine starting systems of one or more other engines of the aircraft. The motoring time of the first engine starting system can be controlled relative to a tolerance of the motoring time of the one or more other engine starting systems by adjusting the motoring time of the first engine starting system relative to the one or more other engine starting systems in a motoring sequence based on comparing the motoring time of the first engine starting system with the motoring time of the one or more other engine starting systems.

A method includes controlling an electric motor of a hybrid-electric powerplant for an aircraft using an EPC (electric powertrain controller) and controlling a heat engine of the hybrid-electric powerplant using an ECU (engine control unit). The method includes performing at least one of the following to protect the hybrid-electric powerplant: using the ECU to power down the electric motor, and/or using the EPC to power down the heat engine.

A method includes controlling an electric motor of a hybrid-electric powerplant for an aircraft using an EPC (electric powertrain controller) and controlling a heat engine of the hybrid-electric powerplant using an ECU (engine control unit). The method includes performing at least one of the following to protect the hybrid-electric powerplant: using the ECU to power down the electric motor, and/or using the EPC to power down the heat engine.

A system and a method are disclosed for a vehicle control and interface system configured to facilitate control of different vehicles through universal mechanisms. The vehicle control and interface system can be integrated with different types of vehicles (e.g., rotorcraft, fixed-wing aircraft, motor vehicles, watercraft, etc.) in order to facilitate operation of the different vehicles using universal vehicle control inputs. In particular, the vehicle control and interface system converts universal vehicle control inputs describing a requested trajectory of a vehicle received from one or more universal vehicle control interfaces into commands for specific actuators of the vehicle configured to adjust a current trajectory of the vehicle to the requested trajectory. In order to convert the universal vehicle control inputs to actuator commands the vehicle control and interface system processes the universal vehicle control inputs using a universal vehicle control router.

Flight control systems, flight control methods, and aircraft are provided. An aircraft including an electric propulsion engine, a combustion turbine engine, a flight controller for generating a first control signal indicative of a climb request, a second control signal indicative of a cruise request and a third control signal indicative of a descent request, and an aircraft propulsion controller operative to engage the electric propulsion engine and the combustion turbine engine in response to the first control signal and disengage the electric propulsion engine in response to the second control signal and wherein the electric propulsion engine may be engaged in a regenerative mode to charge a battery in response to the third control signal

Flight control systems, flight control methods, and aircraft are provided. An aircraft including an electric propulsion engine, a combustion turbine engine, a flight controller for generating a first control signal indicative of a climb request, a second control signal indicative of a cruise request and a third control signal indicative of a descent request, and an aircraft propulsion controller operative to engage the electric propulsion engine and the combustion turbine engine in response to the first control signal and disengage the electric propulsion engine in response to the second control signal and wherein the electric propulsion engine may be engaged in a regenerative mode to charge a battery in response to the third control signal