Supersonic flutter prediction of functionally graded panel

Merve Melek; Metin O. Kaya

doi:10.1109/RAST.2009.5158184

Supersonic flutter prediction of functionally graded panel

Merve Melek^*
, Metin O. Kaya

^*Corresponding author for this work

Department of Aeronautical Engineering

Istanbul Technical University

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

3 Citations (Scopus)

Abstract

In this paper, the supersonic flutter behaviors of functionally graded panels are analyzed by using the Differential Transformation Method (DTM). The material properties are assumed to be graded in the thickness direction and the Mori-Tanaka scheme and a simple power-law are used to estimate the effective material properties. The structural formulation is based on Classical Plate Theory (CPT) and the aerodynamic loading is formulated using quasi-steady supersonic piston theory. The governing equations are derived using the Hamilton's principle.

Original language	English
Title of host publication	RAST 2009 - Proceedings of 4th International Conference on Recent Advances Space Technologies
Pages	139-144
Number of pages	6
DOIs	https://doi.org/10.1109/RAST.2009.5158184
Publication status	Published - 2009
Event	4th International Conference on Recent Advances in Space Technologies 2009, RAST '09 - Istanbul, Turkey Duration: 11 Jun 2009 → 13 Jun 2009

Publication series

Name	RAST 2009 - Proceedings of 4th International Conference on Recent Advances Space Technologies

Conference

Conference	4th International Conference on Recent Advances in Space Technologies 2009, RAST '09
Country/Territory	Turkey
City	Istanbul
Period	11/06/09 → 13/06/09

Keywords

Component
Functional grade (FG)
Supersonic panel flutter

Access to Document

10.1109/RAST.2009.5158184

Cite this

@inproceedings{2053fdb6c06f457a8d00e4343d3c7528,

title = "Supersonic flutter prediction of functionally graded panel",

abstract = "In this paper, the supersonic flutter behaviors of functionally graded panels are analyzed by using the Differential Transformation Method (DTM). The material properties are assumed to be graded in the thickness direction and the Mori-Tanaka scheme and a simple power-law are used to estimate the effective material properties. The structural formulation is based on Classical Plate Theory (CPT) and the aerodynamic loading is formulated using quasi-steady supersonic piston theory. The governing equations are derived using the Hamilton's principle.",

keywords = "Component, Functional grade (FG), Supersonic panel flutter",

author = "Merve Melek and Kaya, \{Metin O.\}",

year = "2009",

doi = "10.1109/RAST.2009.5158184",

language = "English",

isbn = "9781424436286",

series = "RAST 2009 - Proceedings of 4th International Conference on Recent Advances Space Technologies",

pages = "139--144",

booktitle = "RAST 2009 - Proceedings of 4th International Conference on Recent Advances Space Technologies",

note = "4th International Conference on Recent Advances in Space Technologies 2009, RAST '09 ; Conference date: 11-06-2009 Through 13-06-2009",

}

Melek, M & Kaya, MO 2009, Supersonic flutter prediction of functionally graded panel. in RAST 2009 - Proceedings of 4th International Conference on Recent Advances Space Technologies., 5158184, RAST 2009 - Proceedings of 4th International Conference on Recent Advances Space Technologies, pp. 139-144, 4th International Conference on Recent Advances in Space Technologies 2009, RAST '09, Istanbul, Turkey, 11/06/09. https://doi.org/10.1109/RAST.2009.5158184

Supersonic flutter prediction of functionally graded panel. / Melek, Merve; Kaya, Metin O.
RAST 2009 - Proceedings of 4th International Conference on Recent Advances Space Technologies. 2009. p. 139-144 5158184 (RAST 2009 - Proceedings of 4th International Conference on Recent Advances Space Technologies).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

TY - GEN

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AU - Melek, Merve

AU - Kaya, Metin O.

PY - 2009

Y1 - 2009

N2 - In this paper, the supersonic flutter behaviors of functionally graded panels are analyzed by using the Differential Transformation Method (DTM). The material properties are assumed to be graded in the thickness direction and the Mori-Tanaka scheme and a simple power-law are used to estimate the effective material properties. The structural formulation is based on Classical Plate Theory (CPT) and the aerodynamic loading is formulated using quasi-steady supersonic piston theory. The governing equations are derived using the Hamilton's principle.

AB - In this paper, the supersonic flutter behaviors of functionally graded panels are analyzed by using the Differential Transformation Method (DTM). The material properties are assumed to be graded in the thickness direction and the Mori-Tanaka scheme and a simple power-law are used to estimate the effective material properties. The structural formulation is based on Classical Plate Theory (CPT) and the aerodynamic loading is formulated using quasi-steady supersonic piston theory. The governing equations are derived using the Hamilton's principle.

KW - Component

KW - Functional grade (FG)

KW - Supersonic panel flutter

UR - https://www.scopus.com/pages/publications/70350356253

U2 - 10.1109/RAST.2009.5158184

DO - 10.1109/RAST.2009.5158184

M3 - Conference contribution

AN - SCOPUS:70350356253

SN - 9781424436286

T3 - RAST 2009 - Proceedings of 4th International Conference on Recent Advances Space Technologies

SP - 139

EP - 144

BT - RAST 2009 - Proceedings of 4th International Conference on Recent Advances Space Technologies

T2 - 4th International Conference on Recent Advances in Space Technologies 2009, RAST '09

Y2 - 11 June 2009 through 13 June 2009

ER -

Supersonic flutter prediction of functionally graded panel

Abstract

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Keywords

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