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An Optimized Integrator Windup Protection Technique Applied to a Turbofan Engine ControlThis paper introduces a new technique for providing memoryless integrator windup protection which utilizes readily available optimization software tools. This integrator windup protection synthesis provides a concise methodology for creating integrator windup protection for each actuation system loop independently while assuring both controller and closed loop system stability. The individual actuation system loops' integrator windup protection can then be combined to provide integrator windup protection for the entire system. This technique is applied to an H(exp infinity) based multivariable control designed for a linear model of an advanced afterburning turbofan engine. The resulting transient characteristics are examined for the integrated system while encountering single and multiple actuation limits.
Document ID
19960008161
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Watts, Stephen R.
(United Technologies Corp. West Palm Beach, FL., United States)
Garg, Sanjay
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1995
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-9855
NIPS-95-06274
NAS 1.15:107035
NASA-TM-107035
Report Number: E-9855
Report Number: NIPS-95-06274
Report Number: NAS 1.15:107035
Report Number: NASA-TM-107035
Accession Number
96N15327
Funding Number(s)
CONTRACT_GRANT: NAS3-26618
PROJECT: RTOP 505-62-50
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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