OPTIMAL THRUST CONTROL OF AN AIRCRAFT ENGINE

摘要

A control system (40) for a gas turbine engine (10), a method for controlling a gas turbine engine (10), and a gas turbine engine (10) are disclosed. The control system (40) may include a nozzle scheduler (52) for determining an exhaust nozzle position goal (A8 GOAL) based on a nozzle schedule of exhaust nozzle positions related to flight conditions. The control system (40) may further include a control module (60) for determining a control command for the gas turbine engine (10). The control command may include, at least, a fuel flow command and an exhaust nozzle position command and the control command may be based on, at least, the exhaust nozzle position goal (A8 GOAL) and an estimated thrust value. The control system may further include an actuator (34) for controlling the gas turbine engine (10) based on the control command.