Integrated cooling structures and methods for aerial vehicle propulsion mechanisms

Abstract

Integrated cooling structures and methods may comprise a motor, a propeller, and a component having at least one structural feature configured to receive or channel airflow to generate a positive pressure region at a first end of the motor. During operation of the motor and propeller, a negative pressure region may be generated at a second end of the motor proximate the propeller. The positive and negative pressure regions may generate a pressure differential or gradient between ends of the motor, such that a cooling airflow may be generated that flows through an interior of the motor from the positive pressure region to the negative pressure region. The cooling airflow may increase cooling of internal components of the motor, and consequently improve various operational capabilities, performance, and reliability of the motor and associated vehicle, machine, or system.