Patent ID: 7721524

Claim:
An engine assembly comprising: a gas-turbine engine having a tailcone portion and a bypass duct; a rocket engine combustion assembly located at the tailcone portion of the gas-turbine engine; a movable nozzle segment subassembly that is selectively engageable with the gas-turbine engine bypass duct in an open position and with the rocket engine combustion assembly in a closed position, wherein the movable nozzle segment subassembly comprises a plurality of movable nozzle segments; and an aft strut subassembly that includes a plurality of struts each connected to the rocket engine combustion assembly, wherein a drive actuator assembly is positioned adjacent to each of the struts and each drive actuator assembly is operatively engaged with one of the nozzle segments, each drive actuator assembly including a motor and a flexible drive shaft, the flexible drive shaft extending along the corresponding strut in a generally radial direction and configured to operatively engage a corresponding one of the plurality of movable nozzle segments.