Methods and systems for operating an engine are provided. An engine core temperature is monitored. When the engine core temperature is below an engine thermal limit adjusted for a level of deterioration of the engine, an output power of the engine is set in accordance with a reference power based on non-thermal limits of the engine. When the engine core temperature is near or above the engine thermal limit adjusted for the level of deterioration of the engine, the output power of the engine is set to a value lower than the reference power based on non-thermal limits of the engine to reduce the engine core temperature.

A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member A control method is further included.

A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member A control method is further included.

An actuation system for an aircraft can include an actuator and a plurality of clutches connected to and structured to be moved by the actuator. The actuation system can include a plurality of control levers connected to the plurality of clutches and structured to be moved by the plurality of clutches when the plurality of clutches are moved by the actuator. The actuation system can include a processor connected to the actuator and to the plurality of clutches. The processor can identify one or more clutches connected to one or more control levers of the plurality of control levers for controlling an operation of the aircraft, and cause the one or more clutches connected to the one or more control levers to be in an engaged stat. The processor can activate the actuator to cause movement of the one or more control levers via the one or more clutches.

A load fluctuation detection unit that detects a load fluctuation of an aircraft, and an operating point control unit that controls a power operating point defined by a torque and rotation speed based on a flight state. The operating point control unit sets a target power operating point (62) for coping with a load with respect to an initial power operating point (61) in an operating point map (40) when the load has fluctuated. The operating point control unit moves the power operating point from the initial power operating point (61) on a first operating line (41) to the target power operating point (62) on a second operating line (42), to a return power operating point (63) on the first operating line (41) while keeping a torque T constant, and then to the initial power operating point (61) along the first operating line (41).

An autothrottle system to be interfaced with a full-authority digital engine control (FADEC) system having a command input that receives sensed power-control input (PCL) position signaling indicative of a manual throttle setting for an aircraft. The autothrottle system generates automated power command signaling that is synthesized to virtualize electrical characteristics of the sensed PCL position signaling such that the automated power command signaling is recognized by the FADEC system as sensed PCL position signaling.

An autothrottle system to be interfaced with a full-authority digital engine control (FADEC) system having a command input that receives sensed power-control input (PCL) position signaling indicative of a manual throttle setting for an aircraft. The autothrottle system generates automated power command signaling that is synthesized to virtualize electrical characteristics of the sensed PCL position signaling such that the automated power command signaling is recognized by the FADEC system as sensed PCL position signaling.

A vehicle control method of starting and shutting down an engine, in which a processor receives a blockchain update comprising a first transaction with instructions to perform an engine startup or shutdown; the blockchain update is validated; an engine startup or shutdown is performed based on the validated blockchain update; where the engine startup or shutdown is delayed based on validating a predetermined number of subsequent blockchain updates, including a second transaction with instructions to perform the engine startup or shutdown.

A vehicle control method of starting and shutting down an engine, in which a processor receives a blockchain update comprising a first transaction with instructions to perform an engine startup or shutdown; the blockchain update is validated; an engine startup or shutdown is performed based on the validated blockchain update; where the engine startup or shutdown is delayed based on validating a predetermined number of subsequent blockchain updates, including a second transaction with instructions to perform the engine startup or shutdown.

Systems and methods are described for governing the speed of a propeller on a propeller-based engine in an aircraft. The method comprises obtaining a synthesized or estimated blade angle for the propeller of the engine, determining one or more gain for a controller of the propeller based on the synthesized or estimated blade angle and one or more engine or aircraft parameter, determining a difference between a reference propeller speed and an actual propeller speed, applying the one or more gain to the difference via the controller in order to generate a command signal for controlling the propeller, and governing the propeller of the engine using the command signal.