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Nonlinear Aeroelastic Simulation of a Full-Span Aircraft with Oscillating Control Surfaces  

Yoo, Jae-Han (한국과학기술원 기계공학과 항공우주전공 대학원)
Kim, Dong-Hyun (경상대학교 기계항공공학부)
Kwon, Hyuk-Jun (한국과학기술원 기계공학과 항공우주전공 대학원)
Lee, In (한국과학기술원 기계공학과 항공우주전공)
Paek, Seung-Kil (한국항공우주산업(KAL))
Kim, Young-Ik (한국항공우주산업(KAL))
Publication Information
Journal of the Korea Institute of Military Science and Technology / v.5, no.4, 2002 , pp. 81-87 More about this Journal
Abstract
In this paper, the transonic aeroelastic behavior of the generic fighter model is investigated in the time domain. The simulation of flutter flight test using forced harmonic motion of control surfaces including inertial coupling effects is conducted at the various conditions. The nonlinear aerodynamic effects are considered using a transonic small disturbance equation. A modal model obtained by a free vibration analysis is used for the structural model. The relations between the computed flutter boundary and the simulation results of the responses using the harmonic motions of control surfaces at various conditions are investigated.
Keywords
Flutter; Transonic; Control Surface; CFD; Aeroelasticity;
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