Abstract: A control system for an in-flight engine restart system of a rotorcraft includes an engine control unit that controls and detects status of an engine. The control system also includes a flight control computer that communicates with the engine control unit, an engine operation control system, and a pilot interface including pilot controls. The engine operation control system includes a processor that initiates a health check of the in-flight engine restart system to determine an in-flight engine restart system status. The engine operation control system processes engine mode of operation commands to establish an engine mode of operation, and delivers commands to aspects of the in-flight engine restart system including the engine control unit based on processing of the engine mode of operation commands. The engine operation control system reports the in-flight engine restart system status and results of the engine mode of operation commands to the flight control computer.

Abstract: Embodiments are directed to selecting, by a computing device comprising a processor, the size of at least one prime mover associated with an aircraft to satisfy a baseline power requirement for operation of the aircraft during a steady state load condition, selecting at least one power source configuration to supplement power provided by the at least one prime mover during a transient load condition associated with the operation of the aircraft, and selecting, by the computing device, a parameter of the at least one power source configuration to provide a total power in an amount that is greater than a threshold during the transient condition.

Abstract: An electrified propulsion system for a rotary wing aircraft includes a flight control computer that receives a signal indicative of a power demand on an engine; an engine control system that is in communication with the engine and is configured to control operation of the engine at a selected operating point; a generator that is in mechanical communication with the engine and is configured to receive mechanical power from the engine and convert the mechanical power to electrical power; an electric motor that is in electrical communication with the generator and is configured to receive the electric power; and a rotor that is in mechanical communication with the electric motor; wherein the electric motor is configured to control rotation and provide the mechanical power demand of the rotor at the selected operating point in response to the received signal.

Abstract: A control system for an in-flight engine restart system of a rotorcraft includes an engine control unit that controls and detects status of an engine. The control system also includes a flight control computer that communicates with the engine control unit, an engine operation control system, and a pilot interface including pilot controls. The engine operation control system includes a processor that initiates a health check of the in-flight engine restart system to determine an in-flight engine restart system status. The engine operation control system processes engine mode of operation commands to establish an engine mode of operation, and delivers commands to aspects of the in-flight engine restart system including the engine control unit based on processing of the engine mode of operation commands. The engine operation control system reports the in-flight engine restart system status and results of the engine mode of operation commands to the flight control computer.

Abstract: A torque converter for converting torque between an input shaft and an output shaft includes an impeller operably connected to the input shaft and rotatable therewith. The torque converter further includes a turbine operably connected to the output shaft and rotatable therewith. A fluid flow system directs a flow of motive fluid through the impeller and through the turbine to drive rotation of the output shaft relative to the input shaft. A lockup mechanism is engageable to urge rotation of the output shaft at an output shaft rotational speed identical to an input shaft rotational speed. A switching module controls an actuation system to urge engagement of the lockup mechanism.

Abstract: An aircraft is provided and includes a propeller to generate aircraft thrust, a prop-nacelle housing and supporting the propeller, a wing supporting the prop nacelle and including first coupling elements. The first coupling elements are each configured to selectively couple with a second set of coupling elements associated with a group of interchangeable fuselages.

Abstract: An individual blade control system (IBCS) for a rotor system having a rotor hub is provided including a plurality of blade cuffs mounted to the rotor hub. Each blade cuff is configured to receive a rotor blade and rotate about a blade axis. A plurality of electrical actuators is mounted to the rotor hub adjacent at least one of the plurality of blade cuffs. Each electrical actuator is configured to rotate about an actuator axis. The plurality of blade axes and the plurality of actuator axes are arranged in a plane. Each electrical actuator is coupled to an adjacent blade cuff such that rotation of one of the plurality of electrical actuators causes a proportional rotation of one of the blade cuffs.

Abstract: A fluid cooled system includes a first heat generating component. A first airflow pathway directs a first flow of air across a first heat exchanger. A second airflow pathway directs a second flow of air across a second heat exchanger. A first working fluid is flowed from the first heat generating component, through the first heat exchanger and through the second heat exchanger and returned to the first heat generating component.

Abstract: An engine starting system for a rotary wing aircraft includes a controller that receives a signal indicative of a start command for an engine, a transmission input module that is mechanically coupled to a transmission system and an accessory gearbox and a starter motor that is mechanically coupled to a compressor drive shaft of the engine. Also, a method for restarting an engine in flight includes receiving by a controller a signal indicative of a start command for the engine, determining by the controller that an overrunning clutch is coupled to the engine, transmitting by a transmission system motive power to the engine in response to the determining that the overrunning clutch is coupled to the engine and driving via a compressor drive shaft a compressor section of the engine according to a design speed.

Abstract: An electrified propulsion system for a rotary wing aircraft includes a flight control computer that receives a signal indicative of a power demand on an engine; an engine control system that is in communication with the engine and is configured to control operation of the engine at a selected operating point; a generator that is in mechanical communication with the engine and is configured to receive mechanical power from the engine and convert the mechanical power to electrical power; an electric motor that is in electrical communication with the generator and is configured to receive the electric power; and a rotor that is in mechanical communication with the electric motor; wherein the electric motor is configured to control rotation and provide the mechanical power demand of the rotor at the selected operating point in response to the received signal.

Abstract: Embodiments are directed to selecting, by a computing device comprising a processor, the size of at least one prime mover associated with an aircraft to satisfy a baseline power requirement for operation of the aircraft during a steady state load condition, selecting at least one power source configuration to supplement power provided by the at least one prime mover during a transient load condition associated with the operation of the aircraft, and selecting, by the computing device, a parameter of the at least one power source configuration to provide a total power in an amount that is greater than a threshold during the transient condition.

Abstract: An electrified propulsion system for a rotary wing aircraft includes a flight control computer that receives a signal indicative of a power demand on an engine; an engine control system that is in communication with the engine and is configured to control operation of the engine at a selected operating point; a generator that is in mechanical communication with the engine and is configured to receive mechanical power from the engine and convert the mechanical power to electrical power; an electric motor that is in electrical communication with the generator and is configured to receive the electric power; and a rotor that is in mechanical communication with the electric motor; wherein the electric motor is configured to control rotation and provide the mechanical power demand of the rotor at the selected operating point in response to the received signal.

Abstract: An engine starting system for a rotary wing aircraft includes a controller that receives a signal indicative of a start command for an engine, a transmission input module that is mechanically coupled to a transmission system and an accessory gearbox and a starter motor that is mechanically coupled to a compressor drive shaft of the engine. Also, a method for restarting an engine in flight includes receiving by a controller a signal indicative of a start command for the engine, determining by the controller that an overrunning clutch is coupled to the engine, transmitting by a transmission system motive power to the engine in response to the determining that the overrunning clutch is coupled to the engine and driving via a compressor drive shaft a compressor section of the engine according to a design speed.

Abstract: An electrified propulsion system for a rotary wing aircraft includes a flight control computer that receives a signal indicative of a power demand on an engine; an engine control system that is in communication with the engine and is configured to control operation of the engine at a selected operating point; a generator that is in mechanical communication with the engine and is configured to receive mechanical power from the engine and convert the mechanical power to electrical power; an electric motor that is in electrical communication with the generator and is configured to receive the electric power; and a rotor that is in mechanical communication with the electric motor; wherein the electric motor is configured to control rotation and provide the mechanical power demand of the rotor at the selected operating point in response to the received signal.

Abstract: A torque converter for converting torque between an input shaft and an output shaft includes an impeller operably connected to the input shaft and rotatable therewith. The torque converter further includes a turbine operably connected to the output shaft and rotatable therewith. A fluid flow system directs a flow of motive fluid through the impeller and through the turbine to drive rotation of the output shaft relative to the input shaft. A lockup mechanism is engageable to urge rotation of the output shaft at an output shaft rotational speed identical to an input shaft rotational speed. A switching module controls an actuation system to urge engagement of the lockup mechanism.

Abstract: An individual blade control system (IBCS) for a rotor system having a rotor hub is provided including a plurality of blade cuffs mounted to the rotor hub. Each blade cuff is configured to receive a rotor blade and rotate about a blade axis. A plurality of electrical actuators is mounted to the rotor hub adjacent at least one of the plurality of blade cuffs. Each electrical actuator is configured to rotate about an actuator axis. The plurality of blade axes and the plurality of actuator axes are arranged in a plane. Each electrical actuator is coupled to an adjacent blade cuff such that rotation of one of the plurality of electrical actuators causes a proportional rotation of one of the blade cuffs.

Abstract: A fluid cooled system includes a first heat generating component. A first airflow pathway directs a first flow of air across a first heat exchanger. A second airflow pathway directs a second flow of air across a second heat exchanger. A first working fluid is flowed from the first heat generating component, through the first heat exchanger and through the second heat exchanger and returned to the first heat generating component.