POWER EXTRACTION CONTROL FOR DESCENT IN A HYBRID ELECTRIC PROPULSION SYSTEM

A system of a hybrid aircraft includes a first gas turbine engine, a second gas turbine engine, and a controller. The first gas turbine engine includes a first low spool electric machine (12A) and a first high spool electric machine (12B). The second gas turbine engine includes a second low spool electric machine (12A) and a second high spool electric machine (12B). The controller is operable to determine an operating mode of the hybrid aircraft and control power extraction from either or both of the first low spool electric machine (12A) and the first high spool electric machine (12B) while a single engine descent mode is active. Electric power is provided to either or both of the second low spool electric machine (12A) and the second high spool electric machine (12B) while the single engine descent mode is active to balance thrust between the first gas turbine engine and the second gas turbine engine.