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Robust integrated flight/propulsion control design for a STOVL aircraft using H-infinity control design techniquesResults are presented from an application of H-infinity control design methodology to a centralized integrated flight/propulsion control (IFPC) system design for a supersonic STOVL fighter aircraft in transition flight. The emphasis is on formulating the H-infinity optimal control synthesis problem such that the critical requirements for the flight and propulsion systems are adequately reflected within the linear, centralized control problem formulation and the resulting controller provides robustness to modeling uncertainties and model parameter variations with flight condition. Detailed evaluation results are presented for a reduced order controller obtained from the improved H-infinity control design showing that the control design meets the specified nominal performance objective as well as provides stability robustness for variations in plant system dynamics with changes in aircraft trim speed within the transition flight envelope.
Document ID
19930042435
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Garg, Sanjay
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: Automatica
Volume: 29
Issue: 1
ISSN: 0005-1098
Subject Category
Aircraft Stability And Control
Accession Number
93A26432
Distribution Limits
Public
Copyright
Other

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