Method for selection of optimal engine operating conditions for generating linearized models for on-board control and estimation

A method for generating a base point database for use by a full authority digital engine control (FADEC) to control a gas turbine engine during flight, the method comprising:

• performing, by a model generation processor, an initial simulation of the gas turbine engine using a model to determine ranges of sensitivity of desired engine parameters throughout an operating envelope;
• dividing, by the model generation processor, the operating envelope into a multiple regions based on the ranges of sensitivity of the desired engine parameters;
• selecting, by the model generation processor, multiple combinations of base points within each of the multiple regions;
• performing, by the model generation processor, an additional simulation of the gas turbine engine to determine an accuracy of interpolation between each of the multiple combinations of base points for each of the multiple regions;
• and
• selecting, by the model generation processor, final base points from the multiple combinations of base points based on the accuracy.

A system for controlling a gas turbine engine of an aircraft, comprising:

• the gas turbine engine;
• a sensor coupled to the gas turbine engine and configured to detect a first parameter corresponding to the gas turbine engine;
• a full authority digital engine control (FADEC) configured to store a base point database and to control the gas turbine engine based on the first parameter and the base point database;
• and
• an offline model generation device having:
• a memory configured to store a model of the gas turbine engine, and
• a model generation processor coupled to the memory and configured to:
• perform an initial simulation of the gas turbine engine using the model to determine ranges of sensitivity of desired engine parameters throughout an operating envelope,
• divide the operating envelope into a multiple regions based on the ranges of sensitivity of the desired engine parameters,
• select multiple combinations of base points within each of the multiple regions,
• perform an additional simulation of the gas turbine engine to determine an accuracy of interpolation between each of the multiple combinations of base points for each of the multiple regions,
• select final base points from the multiple combinations of base points based on the accuracy, and
• upload the final base points to the FADEC to be stored in the base point database.