Abstract: The present disclosure relates to propulsion system for an aircraft. The propulsion system comprises a motor, a battery bank, a thermal management system, and a controller. The motor being configured to rotate a rotor via a rotor shaft and to drive the thermal management system. The thermal management system configured to urge fluid through a fluid pathway defined by the battery bank. The controller configured to drive the motor and/or control charge and discharge of the battery bank.

Abstract: A thrust assembly motor is described, which can be used in a distributed electric propulsion system. The thrust assembly motor may include a revolved-wedge shaped ring on a leading edge of a motor stator, with a row of axial stator blades extending therefrom. The revolved-wedge shaped ring provides a mounting surface for the axial stator blade row while also controlling the ratio of airflow mass entering the outer gap versus the inner gap. The axial stator blade row, mounted to the revolved-wedge shaped ring, is configured to convert tangential kinetic energy (i.e., associated with a velocity component of the airflow) in the cooling airflow aft of the cooling fan rotors into static pressure rise after interaction with the axial stator blade row, during flight of the hybrid-propulsion aircraft.

Abstract: A thrust assembly motor is described, which can be used in a distributed electric propulsion system. The thrust assembly motor may include a revolved-wedge shaped ring on a leading edge of a motor stator, with a row of axial stator blades extending therefrom. The revolved-wedge shaped ring provides a mounting surface for the axial stator blade row while also controlling the ratio of airflow mass entering the outer gap versus the inner gap. The axial stator blade row, mounted to the revolved-wedge shaped ring, is configured to convert tangential kinetic energy (i.e., associated with a velocity component of the airflow) in the cooling airflow aft of the cooling fan rotors into static pressure rise after interaction with the axial stator blade row, during flight of the hybrid-propulsion aircraft.