Abstract: Various implementations directed to an aircraft thermal management system are provided. In one implementation, an aircraft may include a fuselage having one or more fuselage sections. The aircraft may also include one or more electric motors configured to drive one or more propulsion systems of the aircraft, where the one or more electric motors are configured to generate thermal energy. The aircraft may further include an aircraft thermal management system configured to transfer the thermal energy generated by the one or more electric motors to the one or more fuselage sections.

Abstract: An architecture for an electric distributed propulsion system includes one or more generators connected to a gearbox, a first and a second plurality of motors connected to the one or more generators, each motor of the plurality of motors connected to a blade to provide thrust, a first and a second power bus electrically connected between the one or more generators and the first and the second plurality of motors, each power bus independent of the other power bus, a first and a second controller independently connected to each of the first and second plurality of motors, each of the first and second controllers serving as a primary and a backup controller, and dual channels in communication between pilot input sensors and the first and the second controllers, and the dual channels including an additional channel to provide redundant communication to the first and second controllers.

Abstract: A yaw control system coupled to a tailboom of a helicopter includes tail rotors. The tail rotors include a clockwise tail rotor and a counterclockwise tail rotor. The clockwise tail rotor is configured to rotate in a first rotational direction. The counterclockwise tail rotor is configured to rotate in a second rotational direction, the second rotational direction opposite of the first rotational direction.

Abstract: An electrically distributed yaw control system for a helicopter having a tailboom includes a plurality of tail rotors rotatably coupled to the tailboom and a flight control computer implementing a tail rotor balancing module. The tail rotor balancing module includes a tail rotor balancing monitoring module configured to monitor one or more parameters of the helicopter and identify a first set of one or more tail rotors in the plurality of tail rotors based on the one or more parameters. The tail rotor balancing module also includes a tail rotor balancing command module configured to modify one or more operating parameters of the first set of tail rotors.

Abstract: Various implementations directed to an aircraft thermal management system are provided. In one implementation, an aircraft may include a fuselage having one or more fuselage sections. The aircraft may also include one or more electric motors configured to drive one or more propulsion systems of the aircraft, where the one or more electric motors are configured to generate thermal energy. The aircraft may further include an aircraft thermal management system configured to transfer the thermal energy generated by the one or more electric motors to the one or more fuselage sections.

Abstract: An electrically distributed yaw control system for a helicopter having a tailboom includes a plurality of tail rotors rotatably coupled to the tailboom and a flight control computer implementing a tail rotor balancing module. The tail rotor balancing module includes a tail rotor balancing monitoring module configured to monitor one or more parameters of the helicopter and identify a first set of one or more tail rotors in the plurality of tail rotors based on the one or more parameters. The tail rotor balancing module also includes a tail rotor balancing command module configured to modify one or more operating parameters of the first set of tail rotors.

Abstract: A yaw control system coupled to a tailboom of a helicopter includes tail rotors. The tail rotors include a clockwise tail rotor and a counterclockwise tail rotor. The clockwise tail rotor is configured to rotate in a first rotational direction. The counterclockwise tail rotor is configured to rotate in a second rotational direction, the second rotational direction opposite of the first rotational direction.

Abstract: An anti-torque assembly for a helicopter includes a plurality of fans pivotably mountable to a tail boom. The fans have fan blades rotatable about a fan axis. One or more of the fans is pivotable relative to the tail boom to a first configuration. The fan axes in the first configuration have an upright orientation and the fans are operable to one or both of pitch and roll the helicopter. Different fans are operable to generate thrust to provide anti-torque to the helicopter. A method of providing anti-torque and method of changing an attitude of a helicopter are also provided.

Abstract: An architecture for an electric distributed propulsion system includes one or more generators connected to a gearbox, a first and a second plurality of motors connected to the one or more generators, each motor of the plurality of motors connected to a blade to provide thrust, a first and a second power bus electrically connected between the one or more generators and the first and the second plurality of motors, each power bus independent of the other power bus, a first and a second controller independently connected to each of the first and second plurality of motors, each of the first and second controllers serving as a primary and a backup controller to provide redundant control to both the first and the second plurality of motors, and dual channels in communication between pilot input sensors and the first and the second controllers, each channel of the dual channels independent of the other channels, and the dual channels including an additional channel to provide redundant communication to the first an

Abstract: An exemplary distributed propulsion system with thermal management includes two or more rotors individually controlled by associated motors and an input control connected to the associated motors to demand the associated motors produce a demanded thrust, wherein a motor power output of each motor of the associated motors is independently controlled to produce the demanded thrust and to control a motor temperature of one or more of the associated motors.

Abstract: An anti-torque assembly for a helicopter includes a plurality of fans pivotably mountable to a tail boom. The fans have fan blades rotatable about a fan axis. One or more of the fans is pivotable relative to the tail boom to a first configuration. The fan axes in the first configuration have an upright orientation and the fans are operable to one or both of pitch and roll the helicopter. Different fans are operable to generate thrust to provide anti-torque to the helicopter. A method of providing anti-torque and method of changing an attitude of a helicopter are also provided.