Aircraft engine takeoff and climb thrust control

A method of operating engines of an aircraft, the method comprising:

• controlling operations of one or more engines of the aircraft during a mission including a takeoff phase, a climb phase, and a cruise phase, the climb phase including a top of climb (ToC) period prior to transitioning to the cruise phase, wherein the ToC period ends at an altitude above 28,000 ft;
• controlling the one or more engines to output a takeoff thrust during the takeoff phase, the takeoff thrust corresponding to a maximum thrust during the takeoff phase;
• and
• controlling the one or more engines to output a ToC thrust during the ToC period, the ToC thrust corresponding to an average thrust during the ToC period;
• wherein the one or more engines is controlled such that a thrust ratio is between 1.1 to 1.6, the thrust ratio being defined as a ratio of the ToC thrust as normalized by a ToC ambient static pressure to the takeoff thrust as normalized by a takeoff ambient static pressure.

A non-transitory computer-readable storage medium having stored thereon instructions that, when executed by a processor, cause the processor to perform a method for controlling operation of one or more engines in an aircraft, the method including:

• controlling the operations of one or more engines during a mission, which includes a takeoff phase, a climb phase, and a cruise phase, where the climb phase includes a top of climb (ToC) period prior to transitioning to the cruise phase;
• controlling the one or more engines to output a takeoff thrust during the takeoff phase, where the takeoff thrust corresponds to a maximum thrust during the takeoff phase;
• controlling the one or more engines to output a ToC thrust during the ToC period, where the ToC thrust corresponds to an average thrust during the ToC period;
• and
• controlling the one or more engines to cause the aircraft to cruise at 0.5 Mach or above;
• wherein the instructions control the one or more engines such that a thrust ratio is maintained between 1.1 to 1.6, the thrust ratio being defined as a ratio of the ToC thrust normalized by a ToC ambient static pressure to the takeoff thrust normalized by a takeoff ambient static pressure.