This paper addresses the problem of determining helicopter rotor mode damping from a state-space model of rotor, fuselage, and inflow in which some of the elements of the system matrices are calculated directly using frequency domain system identification techniques. Simulated flight test data are used to study the fundamental features of a direct state-space matrix identification process including the sensitivity to output noise and the sensitivity to the initial guess of each matrix element to be identified. An improved formulation of the frequency response matching problem is discussed that substantially reduces the computational cost of the solution. The results indicate that the identification procedure is accurate and robust.
Determination of helicopter rotor damping from simulated data using frequency domain system identification
Ermittlung der Hubschrauberrotordämpfung aus Simulationsdaten mit Einsatz der Systemidentifizierung im Frequenzbereich
1995
15 Seiten, 16 Bilder, 19 Quellen
Aufsatz (Konferenz)
Englisch
British Library Conference Proceedings | 1995
|Time domain damping identification in helicopter rotor systems
Tema Archiv | 2001
|AIAA-2001-1536 Time Domain Damping Identification in Helicopter Rotor Systems
British Library Conference Proceedings | 2001
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