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Applications of system identification methods to the prediction of helicopter stability, control and handling characteristicsA set of results on rotorcraft system identification is described. Flight measurements collected on an experimental Puma helicopter are reviewed and some notable characteristics highlighted. Following a brief review of previous work in rotorcraft system identification, the results of state estimation and model structure estimation processes applied to the Puma data are presented. The results, which were obtained using NASA developed software, are compared with theoretical predictions of roll, yaw and pitching moment derivatives for a 6 degree of freedom model structure. Anomalies are reported. The theoretical methods used are described. A framework for reduced order modelling is outlined.
Document ID
19820015356
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Padfield, G. D.
(RAE Bedford, United Kingdom)
Duval, R. K.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 10, 2013
Publication Date
April 1, 1982
Publication Information
Publication: Helicopter Handling Qualities
Subject Category
Air Transportation And Safety
Accession Number
82N23230
Distribution Limits
Public
Copyright
Public Use Permitted.
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