A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the hybrid turbo electric aero-propulsion system. The control subsystems may include, for example, a propulsion control optimization subsystem and a power plant control optimization subsystem. The optimizations may be based on a system model, which is developed and updated during the operation of the hybrid turbo electric aero-propulsion system.

A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the hybrid turbo electric aero-propulsion system. The control subsystems may include, for example, a propulsion control optimization subsystem and a power plant control optimization subsystem. The optimizations may be based on a system model, which is developed and updated during the operation of the hybrid turbo electric aero-propulsion system.

A slider assembly configured to transfer excess load from a first section of a structure to a second section of a structure. The slider assembly includes a bracket and fasteners that are movably connected to the bracket. The fasteners are configured to move through the bracket when a load applied to the first section is below a threshold to maintain a gap between the bracket and the first section to permit the transfer of load from the first section to the second section without loading the slider assembly. The fasteners are further configured to move through the bracket a greater amount when the load applied to the first section is above the threshold to eliminate the gap to transfer at least a portion of the load from the first section to the second section via the slider assembly.

A slider assembly configured to transfer excess load from a first section of a structure to a second section of a structure. The slider assembly includes a bracket and fasteners that are movably connected to the bracket. The fasteners are configured to move through the bracket when a load applied to the first section is below a threshold to maintain a gap between the bracket and the first section to permit the transfer of load from the first section to the second section without loading the slider assembly. The fasteners are further configured to move through the bracket a greater amount when the load applied to the first section is above the threshold to eliminate the gap to transfer at least a portion of the load from the first section to the second section via the slider assembly.

An aircraft gas turbine engine includes a fan that in operation moves air through both a core airflow path and a bypass airflow path of the gas turbine engine. The core airflow path and the bypass airflow path converge at a jet nozzle of the gas turbine engine. A method of controlling the gas turbine engine includes detecting, at a controller of the gas turbine engine, a cruise operating condition of the gas turbine engine, and in response to detecting the cruise operating condition, operating a mechanism of the gas turbine engine to decrease an effective area of the jet nozzle.

A gas turbine engine for an aircraft includes an outer bypass section wall, and a jet nozzle including at least one inflatable diaphragm. The at least one inflatable diaphragm is disposed along the outer bypass section wall. The gas turbine engine also includes a fluid pressure sensor configured to measure a fluid pressure within the at least one inflatable diaphragm, an inlet valve configured to control a pressurized flow of a fluid into the at least one inflatable diaphragm in response to a command from a controller, and a release valve configured to control a release of the fluid from within the at least one inflatable diaphragm in response to a command from the controller.