Evaluation of Recursive Least Squares algorithm for parameter estimation in aircraft real time applications

This paper presents results of evaluation of Recursive Least Squares (RLS) algorithm for real time applications in flight control and testing. The RLS proposed here is based on the equation error principle and can start with zero values of the unknown parameters. The technique makes use of only forg...

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Veröffentlicht in:Aerospace science and technology Jg. 15; H. 3; S. 165 - 174
Hauptverfasser: Kamali, C., Pashilkar, A.A., Raol, J.R.
Format: Journal Article
Sprache:Englisch
Veröffentlicht: Issy-les-Moulineaux Elsevier SAS 01.04.2011
Elsevier
Schlagworte:
Aircraft
Algorithms
Applied sciences
Calibrated air data
Calibration
Computer science; control theory; systems
Control theory. Systems
Discrete Fourier transform
Exact sciences and technology
Fault tolerant control
Least squares method
Mathematical analysis
Modelling and identification
Parameter estimation
Post failure model estimation
Real time
Real-time parameter estimation
Recursive
Recursive least squares
Stability margin
Stabilized RLS
Stability margin
Stabilized RLS
Post failure model estimation
Discrete Fourier transform
Calibrated air data
Real-time parameter estimation
Recursive least squares
Fault tolerant control
Parameter estimation
Gain margin
Discrete Fourier transformation
Flight control
Real time
Recursive algorithm
Fault tolerance
Least squares method
Time of flight method
Recursive method
System identification
Phase margin
Roll
Aircraft
Fault tolerant system
Reconfiguration
ISSN:1270-9638, 1626-3219
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Beschreibung
Zusammenfassung:This paper presents results of evaluation of Recursive Least Squares (RLS) algorithm for real time applications in flight control and testing. The RLS proposed here is based on the equation error principle and can start with zero values of the unknown parameters. The technique makes use of only forgetting factor and a stabilizing parameter to achieve better convergence characteristics. In the present study, the RLS technique is applied for parameter estimation in the context of (i) reconfigurable/restructurable control, (ii) estimation of aircraft short period and Dutch roll characteristics in the absence of calibrated air data, and (iii) online stability (gain and phase) margin estimation.
Bibliographie:ObjectType-Article-2
SourceType-Scholarly Journals-1
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content type line 23
ISSN:1270-9638
1626-3219
DOI:10.1016/j.ast.2010.12.007