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Verifiable Adaptive Control with Analytical Stability Margins by Optimal Control ModificationThis paper presents a verifiable model-reference adaptive control method based on an optimal control formulation for linear uncertain systems. A predictor model is formulated to enable a parameter estimation of the system parametric uncertainty. The adaptation is based on both the tracking error and predictor error. Using a singular perturbation argument, it can be shown that the closed-loop system tends to a linear time invariant model asymptotically under an assumption of fast adaptation. A stability margin analysis is given to estimate a lower bound of the time delay margin using a matrix measure method. Using this analytical method, the free design parameter n of the optimal control modification adaptive law can be determined to meet a specification of stability margin for verification purposes.
Document ID
20100036789
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Nguyen, Nhan T.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 25, 2013
Publication Date
August 2, 2010
Subject Category
Aircraft Stability And Control
Report/Patent Number
ARC-E-DAA-TN1962
Report Number: ARC-E-DAA-TN1962
Meeting Information
Meeting: 2010 AIAA Guidance, Navigation, and Control Conference
Location: Toronto, Ontario, Canada
Country: Canada
Start Date: August 2, 2010
End Date: August 5, 2010
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 457280.02.07.01.02.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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