Distributed control and monitoring system for multiple platforms

An aircraft comprising:

• an aircraft engine;
• and
• a control system comprising:
• a first processor located within the aircraft engine and operably coupled to a first network interface device;
• at least one sensor located within the aircraft engine and provides signals to the first processor based on sensed conditions of the gas turbine engine;
• at least one actuator located within the aircraft engine that is controlled by the first processor, wherein an operating environment of the gas turbine engine is harsh;
• a second processor located outside the aircraft engine that has higher processing power than the first processor, wherein an operating environment outside of the gas turbine engine is benign;
• and
• a second network interface device located outside the aircraft engine and operably coupled to the second processor, wherein the second network interface device and the first network interface device provide a communication network between the first processor and the second processor, wherein the second processor is operable to receive sensor readings of the at least one sensor from the first processor, and transmit commands to the first processor for controlling the at least one actuator, wherein the second processor executes aircraft engine safety functions.

A method for controlling a gas turbine engine wherein an operating environment of the gas turbine engine is harsh and an operating environment outside of the gas turbine engine is benign, the gas turbine engine, comprising:

• receiving, by a first processor located within the harsh operating environment of the gas turbine engine from at least one sensor operably coupled to the first processor, signals based on sensed conditions of the gas turbine engine;
• transmitting, by the first processor to a second processor positioned outside the gas turbine engine in the benign operating environment, sensor data based on the received signals;
• transmitting, by the second processor to the first processor, actuator commands to control at least one actuator operably coupled to first processor, wherein the second processor has higher processing power than the first processor;
• and
• controlling, by the first processor, the at least one actuator based on the actuator commands, wherein the second processor executes aircraft engine safety functions.