Limit cycle oscillation of missile control fin with structural non-linearity

Non-linear aeroelastic characteristics of a deployable missile control fin with structural non-linearity are investigated. A deployable missile control fin is modelled as a two-dimensional typical section model. Doublet-point method is used for the calculation of supersonic unsteady aerodynamic forces, and aerodynamic forces are approximated by using the minimum-state approximation. For non-linear flutter analysis structural non-linearity is represented by an asymmetric bilinear spring and is linearized by using the describing function method. The linear and non-linear flutter analyses indicate that the flutter characteristics are significantly dependent on the frequency ratio. From the non-linear flutter analysis, various types of limit cycle oscillations are observed in a wide range of air speeds below or above the linear divergent flutter boundary. The non-linear flutter characteristics and the non-linear aeroelastic responses are investigated. (C) 2003 Elsevier Ltd. All rights reserved.
Publisher
ACADEMIC PRESS LTD ELSEVIER SCIENCE LTD
Issue Date
2004-01
Language
ENG
Keywords

CONTROL SURFACE FREEPLAY; AEROELASTIC ANALYSIS; FLUTTER ANALYSIS; AIRFOIL SECTION; BEHAVIOR

Citation

JOURNAL OF SOUND AND VIBRATION, v.269, no.3-5, pp.669 - 687

ISSN
0022-460X
URI
http://hdl.handle.net/10203/5583
Appears in Collection
AE-Journal Papers(저널논문)
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