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 system and method for a reconfigurable aircraft having a fuselage with one or more propellers, at least one tail assembly, a processor, and a memory having instructions stored thereon that, when executed by the processor, cause the system to: determine a safety clearance for the at least one tail assembly; and selectively move the at least one tail assembly upon a determination that the safety clearance is achieved.

Abstract: A rotary-wing aircraft and system for controlling a flight of the rotary-wing aircraft. The aircraft includes a main rotor, a propeller and a variable speed transmission for transferring power from the main rotor to the propeller. A propeller command module controls operation of the variable speed transmission. The propeller command module varies a transfer of power from the main rotor to the propeller.

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 system and method for controlling an altitude loss of an aircraft in response to a power loss event, includes obtaining at least one aircraft condition from at least one sensor, determining a present aircraft energy state of the aircraft from the at least one aircraft condition via an energy analysis unit, wherein the present aircraft energy state includes an aircraft potential energy and at least one of an aircraft kinetic energy and a rotor rotational kinetic energy, calculating a flight path to partially utilize at least one of the aircraft kinetic energy and the rotor rotational kinetic energy to initiate an autorotation state of the aircraft via a flight path controller, wherein the flight path controller minimizes an aircraft potential energy loss associated with the flight path, and initiating the autorotation state of the aircraft via the flight path.

Abstract: A system and method for a reconfigurable aircraft having a fuselage with one or more propellers, at least one tail assembly, a processor, and a memory having instructions stored thereon that, when executed by the processor, cause the system to: determine a safety clearance for the at least one tail assembly; and selectively move the at least one tail assembly upon a determination that the safety clearance is achieved.

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: A rotorcraft engine starting system includes a starting system controller in communication with a flight control computer; an electric engine starter; an electronic engine controller in communication with the electric engine starter; an electrical power distributor; and a plurality of power sources coupled to the electrical power distributor; the starting system controller selecting at least one of the plurality of power sources and instructing the electrical power distributor to use the at least one of the plurality of power sources to power the electric engine starter.

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 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 rotary wing aircraft propulsion system includes an engine, a heat exchanger cooling a fluid from the engine and a thermoelectric generator in thermal communication with the fluid to generate electrical power. The thermoelectric generator provides electrical power to at least one aircraft component.

Abstract: A rotorcraft engine starting system includes a starting system controller in communication with a flight control computer; an electric engine starter; an electronic engine controller in communication with the electric engine starter; an electrical power distributor; and a plurality of power sources coupled to the electrical power distributor; the starting system controller selecting at least one of the plurality of power sources and instructing the electrical power distributor to use the at least one of the plurality of power sources to power the electric engine starter.

Abstract: A rotary wing aircraft propulsion system includes an engine, a heat exchanger cooling a fluid from the engine and a thermoelectric generator in thermal communication with the fluid to generate electrical power. The thermoelectric generator provides electrical power to at least one aircraft component.