Effects of multiple structural nonlinearities on limit cycle oscillation of missile control fin

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Aeroelastic analyses are performed for a 2-D typical section model with multiple nonlinearities. The differences between a system with multiple nonlinearities in its pitch and plunge spring and a system with a single nonlinearity in its pitch are thoroughly investigated. The unsteady supersonic aerodynamic forces are calculated by the doublet point method (DPM). The iterative V-g method is used for a multiple-nonlinear aeroelastic analysis in the frequency domain and the freeplay nonlinearity is linearized using a describing function method. In the time domain, the DPM unsteady aerodynamic forces, which are based on a function of the reduced frequency, are approximated by the minimum state approximation method. Consequently, multiple structural nonlinearities in the 2-D typical wing section model are influenced by the pitch to plunge frequency ratio. This result is important in that it demonstrates that the flutter speed is closely connected with the frequency ratio, considering that both pitch and plunge nonlinearities result in a higher flutter speed boundary than a conventional aeroelastic system with only one pitch nonlinearity. Furthermore, the gap size of the freeplay affects the amplitude of the limit cycle oscillation (LCO) to gap size ratio. (C) 2011 Elsevier Ltd. All rights reserved.
Publisher
ACADEMIC PRESS LTD- ELSEVIER SCIENCE LTD
Issue Date
2011-05
Language
English
Article Type
Article
Keywords

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

Citation

JOURNAL OF FLUIDS AND STRUCTURES, v.27, no.4, pp.623 - 635

ISSN
0889-9746
URI
http://hdl.handle.net/10203/99529
Appears in Collection
AE-Journal Papers(저널논문)
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