Nonlinear Aeroelastic Coupled Trim and Stability Analysis of Rotor-Fuselage

HU Xin-yu; HAN Jing-long; YU Mei

doi:10.3879/j.issn.1000-0887.2010.02.011

Volume 31 Issue 2

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HU Xin-yu, HAN Jing-long, YU Mei. Nonlinear Aeroelastic Coupled Trim and Stability Analysis of Rotor-Fuselage[J]. Applied Mathematics and Mechanics, 2010, 31(2): 218-226. doi: 10.3879/j.issn.1000-0887.2010.02.011

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Nonlinear Aeroelastic Coupled Trim and Stability Analysis of Rotor-Fuselage

doi: 10.3879/j.issn.1000-0887.2010.02.011

Department of Engineering Mechanics, College of Sciences, China University of Mining and Technology, Xuzhou, Jiangsu 221008, P. R. China;
Institute of Vibration Engineering Research, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P. R. China

Received Date: 1900-01-01
Rev Recd Date: 2010-01-03
Publish Date: 2010-02-15

Abstract

Abstract

Based on the principle of Hamilton and the moderate deflection beam theory,discretizing the blade into a number of beame lements which had 15 degrees of freedom,using quasi-steady aero model,the nonlinear coupledrotor/fuselage equation was founded.The periodic solution of blades and fuselage were obtained through aeroe lastic coupledtrim using temporal finite element method.Peters.dynamic inflow modelwas adopted for vehicle stability.A calculation program was builtup,which offered the blade responses,hubloads and the rotor pitch controls.The correlation between analytical results and related literatures is good.The converged solution simultaneously satisfies the blade and the vehicle equilibrium equations.
- nonlinear,
- aeroelas ticity,
- rotor/fuselage coupling,
- temporal finite element method,
- stability

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References(14)

References

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