Rotor dynamic state and parameter identification from simulated forward flight transients, part 1.

Author: Banerjee, D.
Published: Jun 1, 1976.
Physical Description: 1 electronic document
Additional Creators: Yin, S. K. and Hohenemser, K. H.

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Summary

State and parameter identifications from simulated forward flight blade flapping measurements are presented. The transients were excited by progressing cyclic pitch stirring or by hub stirring with constant stirring acceleration. Rotor dynamic inflow models of varying degree of sophistication were used from a one parameter inflow model (equivalent Lock number) to an eight parameter inflow model. The maximum likelihood method with assumed fixed measurement error covariance matrix was applied. The rotor system equations for both fixed hub and tilting hub are given. The identified models were verified by comparing true responses with predicted responses. An optimum utilization of the simulated measurement data can be defined. From the numerical results it can be anticipated that brief periods of either accelerated cyclic pitch stirring or of hub stirring are sufficient to extract with adequate accuracy up to 8 rotor dynamic inflow parameters plus the blade Lock number from the transients.

Other Subject(s)

AERODYNAMICS

Collection

NASA Technical Reports Server (NTRS) Collection.

Note

Document ID: 19770003061.
Accession ID: 77N10003.
REPT-3.
NASA-CR-137963.

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