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Localized Lagrange multipliers in Flexible multibody dynamics

Localized Lagrange multipliers in Flexible multibody dynamic...

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The sixth Asian Conference on Multibody Dynamics(ACMD 2012)

作者： olivier A.bauchau University of Michigan-Shanghai Jiao Tong University Joint Institute

＜正＞A distinguishing feature of multibody systems is the presence of joints that impose constraints on the relative motion of the various bodies of the system[1].A basic tool used for handling constraints in dynamical systems is the Lagrange multiplier method,which has found extensive use in multibody *** resulting differential-algebraic equations have been the focus of intense scrutiny and many approaches have been developed for their solution[2,3].The augmented Lagragian formulation proposed by Bayo et al.[4,5] is now a well established solution procedure that improves the conditioning of the equations and transforms

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An Efficient Tightly Coupled Fluid-Solid Interaction Approach For Modeling Rotors in Forward Flight

An Efficient Tightly Coupled Fluid-Solid Interaction Approac...

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第二届旋翼飞行器技术基础研究国际学术会议

作者： Sujeet Phanse Lakshmi N.Sankar olivier bauchau School of Aerospace Engineering Georgia Institute of Technology Atlanta GA 30332-0150 Doctoral Candidate School of Aerospace Engineering Georgia Institute of Technology Atlanta GA 30332-0150 Professor School of Aerospace Engineering Georgia Institute of Technology Atlanta GA 30332-0150 Professor

＜正＞A tightly coupled fluid-solid dynamics interaction approach has been developed for the efficient prediction of aerodynamic loads on rotor blades in forward flight. The aerodynamic computations are done using a 3-D Navier-Stokes solver modeling the viscous flow over the blade and the near wake. The elastic structural dynamic computations are carried out using a multi-body dynamics approach. The fluid and solid dynamics equations are simultaneously integrated in time, providing a tight coupling between the structural dynamic and fluid dynamic solvers at every time step. A generalized grid motion module has been developed to account for the effects of the blade motion and elastic deformations on the aerodynamics. A free self-induced wake model is used to model the tip vortex effects once the blade tip vortices leave the resolved CFD domain. A four-bladed UH-60A rotor at a high advance ratio has been studied, and the results compared with flight test data.

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