Dynamic Stiffness Transfer Function of an Electromechanical Actuator Using System Identification

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In the aeroelastic analysis of flight vehicles with electromechanical actuators (EMAs), an accurate prediction of flutter requires dynamic stiffness characteristics of the EMA. The dynamic stiffness transfer function of the EMA with brushless direct current (BLDC) motor can be obtained by conducting complicated mathematical calculations of control algorithms and mechanical/electrical nonlinearities using linearization techniques. Thus, system identification approaches using experimental data, as an alternative, have considerable advantages. However, the test setup for system identification is expensive and complex, and experimental procedures for data collection are time-consuming tasks. To obtain the dynamic stiffness transfer function, this paper proposes a linear system identification method that uses information obtained from a reliable dynamic stiffness model with a control algorithm and nonlinearities. The results of this study show that the system identification procedure is compact, and the transfer function is able to describe the dynamic stiffness characteristics of the EMA. In addition, to verify the validity of the system identification method, the simulation results of the dynamic stiffness transfer function and the dynamic stiffness model were compared with the experimental data for various external loads. © 2018, The Korean Society for Aeronautical & Space Sciences and Springer Nature Singapore Pte Ltd.
Publisher
SPRINGER
Issue Date
2018-03
Language
English
Article Type
Article
Citation

INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES, v.19, no.1, pp.208 - 216

ISSN
2093-274X
DOI
10.1007/s42405-018-0005-7
URI
http://hdl.handle.net/10203/248784
Appears in Collection
AE-Journal Papers(저널논문)
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