Limit cycle oscillation of missile control fin with structural non-linearity |
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| Institution: | 1. Electrical Engineering, Khalifa University of Science and Technology, Sas Al Nakhl, Abu Dhabi, United Arab Emirates;2. Saint-Petersburg State University, Saint-Petersburg, Russia;3. Institute for Problems in Mechanical Engineering of the Russian Academy of Sciences (IPME RAS), St.Petersburg, Russia;4. University of Jyväskylä, Jyväskylä, Finland;1. School of Mathematics and Statistics, Shandong Normal University, Ji’nan, Shandong 250014, PR China;2. School of Science, Shandong Jiaotong University, Ji’nan, Shandong 250357, PR China;1. Department of Mathematics, Huzhou University, Huzhou, Zhejiang 313000, PR China;2. Department of Mechanical and Industrial Engineering, Southern Illinois University, Edwardsville,IL 62026-1805, USA |
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| Abstract: | 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. |
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