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Rate-Based Model Predictive Control of Turbofan Engine ClearanceAn innovative model predictive control strategy is developed for control of nonlinear aircraft propulsion systems and sub-systems. At the heart of the controller is a rate-based linear parameter-varying model that propagates the state derivatives across the prediction horizon, extending prediction fidelity to transient regimes where conventional models begin to lose validity. The new control law is applied to a demanding active clearance control application, where the objectives are to tightly regulate blade tip clearances and also anticipate and avoid detrimental blade-shroud rub occurrences by optimally maintaining a predefined minimum clearance. Simulation results verify that the rate-based controller is capable of satisfying the objectives during realistic flight scenarios where both a conventional Jacobian-based model predictive control law and an unconstrained linear-quadratic optimal controller are incapable of doing so. The controller is evaluated using a variety of different actuators, illustrating the efficacy and versatility of the control approach. It is concluded that the new strategy has promise for this and other nonlinear aerospace applications that place high importance on the attainment of control objectives during transient regimes.
Document ID
20060056313
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
DeCastro, Jonathan A. (QSS Group, Inc. Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
November 1, 2006
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/CR-2006-214419
E-15692
Meeting Information
Meeting: 42nd AIAA Joint Propulsion Conference and Exhibit
Location: Sacramento, CA
Country: United States
Start Date: July 9, 2006
End Date: July 12, 2006
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NAS3-00145
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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