Parallel hybrid electric vertical takeoff and landing aircraft

A vertical takeoff and landing aircraft, comprising:

• a main rotor system;
• a gearbox mechanically connected to the main rotor system;
• a first gas turbine engine mechanically connected to the gearbox;
• a first electrical motor-generator mechanically connected to the first gas turbine engine and mechanically connected to the gearbox;
• a second electrical motor-generator mechanically connected to the gearbox;
• a third electrical motor electrically connected to the second electrical motor-generator and mechanically connected to an anti-torque device, the third electrical motor configured to provide mechanical power to the anti-torque device, wherein the third electrical motor is not mechanically connected to the gearbox;
• and
• a plurality of power-controller interface units, wherein the plurality of power-controller interface units are configured to:
• in a first operational mode associated with a first phase of flight, control the first gas turbine engine and the first electrical motor-generator to provide mechanical power to the gearbox, and control the second electrical motor-generator to provide electrical power to the third electrical motor.