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Aeroelastic analysis of rotor blades...

The University of Arizona., Mechanical Engineering.

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Aeroelastic analysis of rotor blades using three dimensional multibody dynamic analysis.

Record Type:	Language materials, printed : Monograph/item
Title/Author:	Aeroelastic analysis of rotor blades using three dimensional multibody dynamic analysis./
Author:	Das, Manabendra.
Description:	219 p.
Notes:	Adviser: Erdogan Madenci.
Contained By:	Dissertation Abstracts International69-11B.
Subject:	Applied Mechanics. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3336579
ISBN:	9780549901259

Aeroelastic analysis of rotor blades using three dimensional multibody dynamic analysis.
Das, Manabendra.

Aeroelastic analysis of rotor blades using three dimensional multibody dynamic analysis. - 219 p.

Adviser: Erdogan Madenci.

Thesis (Ph.D.)--The University of Arizona, 2008.

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.

ISBN: 9780549901259Subjects--Topical Terms:

1018410
Applied Mechanics.

Aeroelastic analysis of rotor blades using three dimensional multibody dynamic analysis.
LDR:02919nam 2200337 a 45 001 855616
005 20100708
008 100708s2008 ||||||||||||||||| ||eng d
020 $a 9780549901259
035 $a (UMI)AAI3336579
035 $a AAI3336579
040 $a UMI $c UMI
100 1 $a Das, Manabendra. $3 1022256
245 1 0 $a Aeroelastic analysis of rotor blades using three dimensional multibody dynamic analysis.
300 $a 219 p.
500 $a Adviser: Erdogan Madenci.
500 $a Source: Dissertation Abstracts International, Volume: 69-11, Section: B, page: 7092.
502 $a Thesis (Ph.D.)--The University of Arizona, 2008.
520 $a 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.
590 $a School code: 0009.
650 4 $a Applied Mechanics. $3 1018410
650 4 $a Engineering, Aerospace. $3 1018395
650 4 $a Engineering, Mechanical. $3 783786
690 $a 0346
690 $a 0538
690 $a 0548
710 2 $a The University of Arizona. $b Mechanical Engineering. $3 1022255
773 0 $t Dissertation Abstracts International $g 69-11B.
790 $a 0009
790 1 0 $a Haldar, Achintya $e committee member
790 1 0 $a Kundu, Tribikram $e committee member
790 1 0 $a Madenci, Erdogan, $e advisor
790 1 0 $a Nikravesh, Parviz E. $e committee member
790 1 0 $a Straub, Friedrich K. $e committee member
791 $a Ph.D.
792 $a 2008
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3336579