A control system for a gas turbine engine, the control system comprising: a nozzle scheduler for determining an exhaust nozzle position goal (A8 GOAL) based on a nozzle schedule of exhaust nozzle positions related to flight conditions, the exhaust nozzle changing positions to change dimensions of an exhaust section with respect to a tail cone; a plurality of system sensors for determining sensor signals; an engine model for estimating synthesis signals using the sensor signals; a goal generator module for determining auxiliary goals and actuator goals; the auxiliary goals based on engine states that are related to engine thrust during transient engine operations; and the actuator goals based on positions for high pressure compressor stator vanes (HPCSV), low pressure compressor stator vanes (LPCSV) and/or engine stability bleeds; a control module, being a hybrid model predictive control (HMPC), electronically receiving information, including: the exhaust nozzle position goal (A8 GOAL); the sensor signals; the synthesis signals; and the auxiliary and actuator goals; based on the received information, the control module determining and outputting a control command for the gas turbine engine, the control command including: a fuel flow command; a stability bleeds position command; an exhaust nozzle position command; a high pressure compressor stator vanes (HPCSV) position command; and a low pressure compressor stator vanes (LPCSV) position command; and actuators for controlling the gas turbine engine based on the control command, including controlling: the fuel flow; the stability bleeds position; the exhaust nozzle position; the high pressure compressor stator vanes (HPCSV) position; and the low pressure compressor stator vanes (LPCSV) position. a nozzle scheduler for determining an exhaust nozzle position goal (A8 GOAL) based on a nozzle schedule of exhaust nozzle positions related to flight conditions, the exhaust nozzle changing positions to change dimensions of an exhaust section with respect to a tail cone; a plurality of system sensors for determining sensor signals; an engine model for estimating synthesis signals using the sensor signals; a goal generator module for determining auxiliary goals and actuator goals; the auxiliary goals based on engine states that are related to engine thrust during transient engine operations; and the actuator goals based on positions for high pressure compressor stator vanes (HPCSV), low pressure compressor stator vanes (LPCSV) and/or engine stability bleeds; the auxiliary goals based on engine states that are related to engine thrust during transient engine operations; and the actuator goals based on positions for high pressure compressor stator vanes (HPCSV), low pressure compressor stator vanes (LPCSV) and/or engine stability bleeds; a control module, being a hybrid model predictive control (HMPC), electronically receiving information, including: the exhaust nozzle position goal (A8 GOAL); the sensor signals; the synthesis signals; and the auxiliary and actuator goals; the exhaust nozzle position goal (A8 GOAL); the sensor signals; the synthesis signals; and the auxiliary and actuator goals; based on the received information, the control module determining and outputting a control command for the gas turbine engine, the control command including: a fuel flow command; a stability bleeds position command; an exhaust nozzle position command; a high pressure compressor stator vanes (HPCSV) position command; and a low pressure compressor stator vanes (LPCSV) position command; and actuators for controlling the gas turbine engine based on the control command, including controlling: the fuel flow; the stability bleeds position; the exhaust nozzle position; the high pressure compressor stator vanes (HPCSV) position; and the low pressure compressor stator vanes (LPCSV) position. a fuel flow command; a stability bleeds position command; an exhaust nozzle position command; a high pressure compressor stator vanes (HPCSV) position command; and a low pressure compressor stator vanes (LPCSV) position command; and actuators for controlling the gas turbine engine based on the control command, including controlling: the fuel flow; the stability bleeds position; the exhaust nozzle position; the high pressure compressor stator vanes (HPCSV) position; and the low pressure compressor stator vanes (LPCSV) position. the fuel flow; the stability bleeds position; the exhaust nozzle position; the high pressure compressor stator vanes (HPCSV) position; and the low pressure compressor stator vanes (LPCSV) position.