초록 ▼

A method of designing the operations and controls of a aircraft gas turbine engine includes generating an operations model for the gas turbine include at least one objective function, defining operations and control constraints for the operations model of the gas turbine, and providing an online dyn

A method of designing the operations and controls of a aircraft gas turbine engine includes generating an operations model for the gas turbine include at least one objective function, defining operations and control constraints for the operations model of the gas turbine, and providing an online dynamic optimizer/controller that dynamically optimizes and controls operation of the gas turbine using model predictive control based on the operations model and the operations and control constraints using an Extended Kalman Filter for estimation.

대표청구항 ▼

1. A method of designing the operations and controls of a aircraft gas turbine engine, said method comprising:generating an operations model for the gas turbine including at least one objective function;defining operations and control constraints for the operations model of the gas turbine; andprovi

1. A method of designing the operations and controls of a aircraft gas turbine engine, said method comprising:generating an operations model for the gas turbine including at least one objective function;defining operations and control constraints for the operations model of the gas turbine; andproviding an online dynamic optimizer/controller that dynamically optimizes and controls operation of the aircraft gas turbine engine using model predictive control based on the operations model and the operations and control constraints using an Extended Kalman Filter for estimation. 2. A method according to claim 1, wherein the optimizer/controller performs following steps in a loop: (A) estimating the current engine state and applicable constraints; (B) for a given control/simulation time period, determining a control action by optimizing an objective function based on the operation model while respecting the applicable constraints; (C) executing the control action determined in step (B). 3. A method according to claim 1 further comprising defining an objective J in accordance with: 4. A method in accordance with claim 3 further comprising computing a gradient of J. 5. A method in accordance with claim 4 further comprising taking steps in a negative gradient direction until J is minimized. 6. A method in accordance with claim 4 further comprising taking steps in a negative gradient direction until the number of steps equals a predetermined number. 7. A method in accordance with claim 4 further comprising taking steps in a negative gradient direction until an elapsed time exceeds a predetermined time interval. 8. A system for designing the operations and controls of an aircraft gas turbine engine, said system comprising:a computing unit with an input unit for generating an operations model for the aircraft gas turbine engine to include at least one objective function and for defining operations and controls constraints for the operations model of the aircraft gas turbine engine; anda dynamic online optimizer/controller configured to dynamically optimize and control operation of the gas turbine using model predictive control based on the operations model and the operations and control constraints using an Extended Kalman Filter for estimation. 9. A system according to claim 8, wherein said optimizer/controller is configured to perform the following steps in a loop: (A) estimating the current engine state and applicable constraints; (B) for a given control/simulation time period, determining a control action by optimizing an objective function based on the operation model while respecting the applicable constraints; (C) executing the control action determined in step (B). 10. A system in accordance with claim 8 wherein said optimizer/controller is configured to compute the gradient of J wherein: 11. A system in accordance with claim 10 wherein said optimizer/controller is configured to traverse the gradient in a negative direction until a number of steps equals a predetermined number. 12. A system in accordance with claim 10 wherein said optimizer/controller is configured to traverse the gradient in a negative direction until J is minimized. 13. A system in accordance with claim 10 wherein said optimizer/controller is configured to traverse the gradient in a negative direction until an elapsed time exceeds a predetermined time interval. 14. A non-linear model-based control method for controlling propulsion in a aircraft gas turbine engine, the method comprising:a) obtaining information about the current state of the engine using an Extended Kalman Filter;b) updating model data information about the engine in an model-based control system to reflect the current state of the engine;c) comparing the information about the current state of the engine with the model data information about the engine in the model;d) determining the optimal corrective action to take given the current state of the engine, the objective function, and the constrai nts of the engine;e) outputting a control command to implement the optimal corrective action; andf) repeating steps a)-e) as necessary to ensure the performance of the engine is optimized at all times. 15. A method in accordance with claim 14 wherein said obtaining current information comprises defining an objective J in accordance with: 16. A method in accordance with claim 15 further comprising computing a gradient of J. 17. A method in accordance with claim 16 further comprising taking steps in a negative gradient direction until J is minimized. 18. A method in accordance with claim 16 further comprising taking steps in a negative gradient direction until the number of steps equals a predetermined number. 19. A method in accordance with claim 16 further comprising taking steps in a negative gradient direction until an elapsed time exceeds a predetermined time interval. 20. A method in accordance with claim 16 further comprising taking steps in a negative gradient direction until a first to occur of:J is minimized;the number of steps equals a predetermined number; andan elapsed time exceeds a predetermined time interval.