A hybrid electric propulsion system for an aerial vehicle, the hybrid electric propulsion system comprising: an engine; a first electric machine mechanically coupled with the engine and configured to generate electrical power when driven by the engine; one or more power consuming loads electrically coupled with the first electric machine and configured to receive electrical power from the first electric machine, the one or more power consuming loads comprising a second electric machine; a propulsion assembly mechanically coupled with the second electric machine and configured to produce thrust when driven by the second electric machine; one or more sensing devices positionable onboard the aerial vehicle for detecting one or more performance indicators indicative of an electrical load on the engine; one or more controllers communicatively coupled with the one or more sensors, the one or more controllers configured to: receive, from the one or more sensing devices, the one or more performance indicators indicative of the electrical load on the engine; determine whether an electrical load change is present based at least in part on the one or more performance indicators; and generate, if the electrical load change is present, a control action in response to the electrical load change; a physical braking system mechanically coupled with the engine, and wherein if the electrical load change is a load decrease on the engine, in generating the control action the one or more controllers are configured to: activate the physical braking system to reduce a torque output of the engine. an engine; a first electric machine mechanically coupled with the engine and configured to generate electrical power when driven by the engine; one or more power consuming loads electrically coupled with the first electric machine and configured to receive electrical power from the first electric machine, the one or more power consuming loads comprising a second electric machine; a propulsion assembly mechanically coupled with the second electric machine and configured to produce thrust when driven by the second electric machine; one or more sensing devices positionable onboard the aerial vehicle for detecting one or more performance indicators indicative of an electrical load on the engine; one or more controllers communicatively coupled with the one or more sensors, the one or more controllers configured to: receive, from the one or more sensing devices, the one or more performance indicators indicative of the electrical load on the engine; determine whether an electrical load change is present based at least in part on the one or more performance indicators; and generate, if the electrical load change is present, a control action in response to the electrical load change; receive, from the one or more sensing devices, the one or more performance indicators indicative of the electrical load on the engine; determine whether an electrical load change is present based at least in part on the one or more performance indicators; and generate, if the electrical load change is present, a control action in response to the electrical load change; a physical braking system mechanically coupled with the engine, and wherein if the electrical load change is a load decrease on the engine, in generating the control action the one or more controllers are configured to: activate the physical braking system to reduce a torque output of the engine.