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The effect of dynamics of induced flow through the main rotor is often cited as a cause of control-power deficiency relative to that predicted by simple simulation models of the type which are at present widely used in the design of flight control systems for helicopters. In addition, rotor dynamics themselves pose bandwidth restraint problems for control system design. The validation of models incorporating rotor dynamics and induced flow dynamics is therefore of considerable importance. System identification techniques provide one approach to the development and validation of improved rotor models. This paper prsents a general methodology for the identification of rotor models, principally based upon frequency-domain output-error methods. Strategies are presented involving a number of different forms of model structure involving induced-flow models based on either momentum or vortex theory. Preliminary results are presented for flight data provide by RAE (Bedford) which involve kinematic and flapping data of high quality. An assessment is made of the value of the available identification tools and some conclusions are reached concerning the importance of induced-flow effects for the flight data sets used.
|Keywords:||system identification, helicopter, rotor, induced flow|
|Glasgow Author(s) Enlighten ID:||Murray-Smith, Professor David|
|Authors:||Bradley, R., Black, C.G., and Murray-Smith, D.J.|
|Subjects:||T Technology > TJ Mechanical engineering and machinery|
T Technology > TK Electrical engineering. Electronics Nuclear engineering
T Technology > TL Motor vehicles. Aeronautics. Astronautics
|College/School:||College of Science and Engineering > School of Engineering > Systems Power and Energy|