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Flutter Analysis of 2-D Aircraft Wings in Supersonic Flow

Author: YeXin
Tutor: ChenYuShu
School: Harbin Institute of Technology
Course: General and Fundamental Mechanics
Keywords: nonlinear vibration supersonic 2-d aircraft wings Hopf bifurcation LCOs
CLC: O322
Type: Master's thesis
Year: 2009
Downloads: 57
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Abstract


In the design of aircraft structures, non-linear factors cannot be avoided. In this paper, a two-degree-of-freedom airfoil and cubic stiffness nonlinearities in pitching degree-of-freedom operating in supersonic flight speed regimes has been analyzed. The twice-order piston theory aerodynamice is used to evaluate the unsteady non-linear aerodynamic force and moment, Then the averaging method and the theory of flutter are used to analyze the nonlinear dynamic system of the dualistic airfoil in the supersonic flow, and the Hopf bifurcation point is determined by using the Hurwitz determinant. The last section presents a study on the aerolelastic flutter of the dualistic airfoil, and analysis of the influence of the dynamic system by the physical parameters. The main contributions of this paper are listed in the following:1. The piston theory is introduced, then evaluate the aerodynamic force and moment by using it, considering the cubic stiffness nonlinearities in pitching degree-of-freedom, the dymanic model of the two-degree-of-freedom is found, furthermore, the V-g method and numerical simulation are used to receive the flutter speed of the model, and analysis the reliability by the consequence of the different methods.2. Considering the flutte of system as a condition of internal resonance, the first order approximate solution is obtained by using averaging method, then the relation between the response of the system and the velocity can be received. Considering the result calculated by using the Runge-Kutta method, the correctness of result calculated by the averaging method is verified;3. The bifurcation point of system is determined by using the theory of bifurcation, considering the result received by numerical simulation, the result show that, they are correspondence mostly;4. The aerolelastic flutter of the system is studied, the LCOs are exhibited, then analysis the influence of the dynamic system by the physical parameters, the result show how to improve the flutter speed.These results will be used to provide theoretical guidance for studying the dynamic behavies of the two-degree-of-freedom airfoil in the supersonic flow, and as a reference for engineering.

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CLC: > Mathematical sciences and chemical > Mechanics > Vibration theory > Nonlinear vibration
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