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An Innovative Feedback Controls Design Approach for Aero EnginesThe paper describes a feedback controls design approach for a generic regional jet turbofan engine, which can be adapted to aero engines in general. To demonstrate this approach, linear models for control design are generated at different operating conditions from a full envelope nonlinear simulation created with the NASA Glenn Research Center-developed Toolbox for the Modeling and Analysis of Thermodynamic Systems. The primary objective is to design a single feedback controller that achieves good performance, without the need of developing scheduled control designs to cover the engine operating envelope. An additional objective is to progressively design more robust controllers that can perform under large variations in plant dynamics to also cover control for engine limits and potentially for some off nominal or even damaged conditions.
Document ID
20200000352
Document Type
Technical Memorandum (TM)
Authors
Kopasakis, George
(NASA Glenn Research Center Cleveland, OH, United States)
Norin, Scott B.
(Vantage Partners, LLC Brook Park, OH, United States)
Date Acquired
January 16, 2020
Publication Date
November 1, 2019
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
GRC-E-DAA-TN73199
E-19750
NASA/TM-2019-220361
Funding Number(s)
WBS: 340428.04.90.03.09
CONTRACT_GRANT: NNC12BA01B
Distribution Limits
Public
Copyright
Public Use Permitted.
Technical Review
NASA Technical Management
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