Helicopter Dynamic Model Identification by Conditional Attitude Hold Logic조건부 자세제어 로직을 이용한 헬리콥터 운동모델 식별

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A parameter identification method was proposed for flight vehicles with dynamic models that are difficult to identify due to their highly coupled characteristics. The existing off-axis noise input method, which is used for reducing the correlation between the primary and secondary inputs, has a difficult-to-obtain convergence condition under the hold trim state. In addition, the existing method cannot easily identify high frequency dynamics due to the off-axis input noise. On the other hand, the proposed identification method relied on a computer-generated sweep in the frequency-domain, which could produce a more accurate model than the existing perturbation model. Moreover, the proposed conditional attitude hold logic described the actual pilot's motion by activating the controller when the Euler angle measurements exceeded a pre-defined angle. The proposed method was used with the Bo-105 helicopter nonlinear simulation model, and the identified coupled rotor/fuselage nine-degree-of-freedom results were reliable and comparable to those obtained with the existing perturbation model.
Publisher
American Institute of Aeronautics and Astronautics
Issue Date
2017-01-11
Language
English
Citation

AIAA Science and Technology Forum and Exposition (SciTech) 2017, pp.1 - 6

URI
http://hdl.handle.net/10203/216140
Appears in Collection
EE-Conference Papers(학술회의논문)
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