Aeroelastic Analysis of Rotor Blades Using Three Dimensional Flexible Multibody Dynamic Analysis

Persistent Link:
http://hdl.handle.net/10150/195601
Title:
Aeroelastic Analysis of Rotor Blades Using Three Dimensional Flexible Multibody Dynamic Analysis
Author:
Das, Manabendra
Issue Date:
2008
Publisher:
The University of Arizona.
Rights:
Copyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.
Abstract:
This study presents an approach based on the floating frame of reference method to model complex three-dimensional bodies in a multibody system. Unlike most of the formulations based on the floating frame of reference method, which assume small or moderate deformations, the present formulation allows large elastic deformations within each frame by using the co-rotational form of the updated Lagrangian description of motion. The implicit integration scheme is based on the Generalized-alpha method, and kinematic joints are invoked in the formulation through the coordinate partitioning method. The resulting numerical scheme permits the usage of relatively large time steps even though the flexible bodies may experience large elastic deformations. A triangular element, based on the first order shear deformable theory, has been developed specifically for folded plate and shell structures. The plate element does not suffer from either shear or aspect-ratio locking under transverse and membrane bending, respectively. A stiffened plate element has been developed that combines a shear deformable plate with a Timoshenko beam. A solid element, that utilized the isoparametric formulation along with incompatible modes, and one-dimensional elements are also included in the element library. The tools developed in the present work are then utilized for detailed rotorcraft applications. As opposed to the conventional approach of using beam elements to represent the rotor blade, the current approach focuses on detailed modeling of the blade using plate and solid elements. A quasi-steady model based on lifting line theory is utilized to compute the aerodynamic loads on the rotor blade in order to demonstrate the capabilities of the proposed tool to model rotorcraft aeroelasticity.
Type:
text; Electronic Dissertation
Keywords:
Flexible Mutibody Dynamics; Large Deformations; Nonlinear Finite Element Analysis; Plate Elements; Rotorcraft Aeroelasticity
Degree Name:
Ph.D.
Degree Level:
doctoral
Degree Program:
Mechanical Engineering; Graduate College
Degree Grantor:
University of Arizona
Advisor:
Madenci, Erdogan
Committee Chair:
Madenci, Erdogan

Full metadata record

DC FieldValue Language
dc.language.isoENen_US
dc.titleAeroelastic Analysis of Rotor Blades Using Three Dimensional Flexible Multibody Dynamic Analysisen_US
dc.creatorDas, Manabendraen_US
dc.contributor.authorDas, Manabendraen_US
dc.date.issued2008en_US
dc.publisherThe University of Arizona.en_US
dc.rightsCopyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.en_US
dc.description.abstractThis study presents an approach based on the floating frame of reference method to model complex three-dimensional bodies in a multibody system. Unlike most of the formulations based on the floating frame of reference method, which assume small or moderate deformations, the present formulation allows large elastic deformations within each frame by using the co-rotational form of the updated Lagrangian description of motion. The implicit integration scheme is based on the Generalized-alpha method, and kinematic joints are invoked in the formulation through the coordinate partitioning method. The resulting numerical scheme permits the usage of relatively large time steps even though the flexible bodies may experience large elastic deformations. A triangular element, based on the first order shear deformable theory, has been developed specifically for folded plate and shell structures. The plate element does not suffer from either shear or aspect-ratio locking under transverse and membrane bending, respectively. A stiffened plate element has been developed that combines a shear deformable plate with a Timoshenko beam. A solid element, that utilized the isoparametric formulation along with incompatible modes, and one-dimensional elements are also included in the element library. The tools developed in the present work are then utilized for detailed rotorcraft applications. As opposed to the conventional approach of using beam elements to represent the rotor blade, the current approach focuses on detailed modeling of the blade using plate and solid elements. A quasi-steady model based on lifting line theory is utilized to compute the aerodynamic loads on the rotor blade in order to demonstrate the capabilities of the proposed tool to model rotorcraft aeroelasticity.en_US
dc.typetexten_US
dc.typeElectronic Dissertationen_US
dc.subjectFlexible Mutibody Dynamicsen_US
dc.subjectLarge Deformationsen_US
dc.subjectNonlinear Finite Element Analysisen_US
dc.subjectPlate Elementsen_US
dc.subjectRotorcraft Aeroelasticityen_US
thesis.degree.namePh.D.en_US
thesis.degree.leveldoctoralen_US
thesis.degree.disciplineMechanical Engineeringen_US
thesis.degree.disciplineGraduate Collegeen_US
thesis.degree.grantorUniversity of Arizonaen_US
dc.contributor.advisorMadenci, Erdoganen_US
dc.contributor.chairMadenci, Erdoganen_US
dc.contributor.committeememberMadenci, Erdoganen_US
dc.contributor.committeememberNikravesh, Parviz E.en_US
dc.contributor.committeememberHaldar, Achintyaen_US
dc.contributor.committeememberKundu, Tribikramen_US
dc.contributor.committeememberStraub, Friedrich K.en_US
dc.identifier.proquest10102en_US
dc.identifier.oclc659750633en_US
All Items in UA Campus Repository are protected by copyright, with all rights reserved, unless otherwise indicated.