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E-Thesis 449 views 182 downloads

Aeroelastic methodology for flight vehicles. / Can T Bach

Swansea University Author: Can T Bach

Abstract

This thesis is set out as follows: In Chapter 1, the definition of flutter is given, together with a brief history and a short summary of some of the well know methods used in modeling and formulating the components of the equations of motion that have been employed previously. Chapter 2 includes th...

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Published: 2004
Institution: Swansea University
Degree level: Doctoral
Degree name: Ph.D
URI: https://cronfa.swan.ac.uk/Record/cronfa42259
first_indexed 2018-08-02T18:54:16Z
last_indexed 2018-08-03T10:09:40Z
id cronfa42259
recordtype RisThesis
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spelling 2018-08-02T16:24:28.6045852 v2 42259 2018-08-02 Aeroelastic methodology for flight vehicles. 6e93f3f4fd7c3c1eeee482cf62f3e84b NULL Can T Bach Can T Bach true true 2018-08-02 This thesis is set out as follows: In Chapter 1, the definition of flutter is given, together with a brief history and a short summary of some of the well know methods used in modeling and formulating the components of the equations of motion that have been employed previously. Chapter 2 includes the formulation of the numerical equations of motion for different types of structure and the numerical techniques used to solve these system of equations to obtain the structural characteristic eigensolution. Chapter 3 demonstrates the linear methods used in the panel method to compute the components of aerodynamic forces in the equations of motion, and their application in the solution of aeroelastic and aeroservoelastic problems. Chapter 4 shows the formulation of the nonlinear aerodynamic force component and its integration with the aeroelastic and aeroservoelastic multidiscipline. The formulation of the sensor and control systems and their integration are also detailed in this chapter. Chapter 5 gives the example test cases used for the aeroelastic and aeroservoelastic analysis. Chapter 6 is a short conclusion and is a summary of the study presented herein. A Matlab independent modeling of the aeroservoelastic integration is included in Appendix A. Appendix B and C give the example problem modeling data and formats. E-Thesis Civil engineering.;Aerospace engineering. 31 12 2004 2004-12-31 COLLEGE NANME Engineering COLLEGE CODE Swansea University Doctoral Ph.D 2018-08-02T16:24:28.6045852 2018-08-02T16:24:28.6045852 Faculty of Science and Engineering School of Engineering and Applied Sciences - Uncategorised Can T Bach NULL 1 0042259-02082018162440.pdf 10797967.pdf 2018-08-02T16:24:40.4600000 Output 7230672 application/pdf E-Thesis true 2018-08-02T16:24:40.4600000 false
title Aeroelastic methodology for flight vehicles.
spellingShingle Aeroelastic methodology for flight vehicles.
Can T Bach
title_short Aeroelastic methodology for flight vehicles.
title_full Aeroelastic methodology for flight vehicles.
title_fullStr Aeroelastic methodology for flight vehicles.
title_full_unstemmed Aeroelastic methodology for flight vehicles.
title_sort Aeroelastic methodology for flight vehicles.
author_id_str_mv 6e93f3f4fd7c3c1eeee482cf62f3e84b
author_id_fullname_str_mv 6e93f3f4fd7c3c1eeee482cf62f3e84b_***_Can T Bach
author Can T Bach
author2 Can T Bach
format E-Thesis
publishDate 2004
institution Swansea University
college_str Faculty of Science and Engineering
hierarchytype
hierarchy_top_id facultyofscienceandengineering
hierarchy_top_title Faculty of Science and Engineering
hierarchy_parent_id facultyofscienceandengineering
hierarchy_parent_title Faculty of Science and Engineering
department_str School of Engineering and Applied Sciences - Uncategorised{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Engineering and Applied Sciences - Uncategorised
document_store_str 1
active_str 0
description This thesis is set out as follows: In Chapter 1, the definition of flutter is given, together with a brief history and a short summary of some of the well know methods used in modeling and formulating the components of the equations of motion that have been employed previously. Chapter 2 includes the formulation of the numerical equations of motion for different types of structure and the numerical techniques used to solve these system of equations to obtain the structural characteristic eigensolution. Chapter 3 demonstrates the linear methods used in the panel method to compute the components of aerodynamic forces in the equations of motion, and their application in the solution of aeroelastic and aeroservoelastic problems. Chapter 4 shows the formulation of the nonlinear aerodynamic force component and its integration with the aeroelastic and aeroservoelastic multidiscipline. The formulation of the sensor and control systems and their integration are also detailed in this chapter. Chapter 5 gives the example test cases used for the aeroelastic and aeroservoelastic analysis. Chapter 6 is a short conclusion and is a summary of the study presented herein. A Matlab independent modeling of the aeroservoelastic integration is included in Appendix A. Appendix B and C give the example problem modeling data and formats.
published_date 2004-12-31T04:23:49Z
_version_ 1856982618511245312
score 11.096068

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