Panel Flutter Design of Symmetrically Laminated Plates Using Lamination Parameters

Masaki Sato; Hisao Fukunaga; Hideki Sekine

doi:10.1299/kikaic.64.1013

Panel Flutter Design of Symmetrically Laminated Plates Using Lamination Parameters

Masaki Sato, Hisao Fukunaga, Hideki Sekine

ENG - Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

3 Citations (Scopus)

Abstract

The present paper examines the optimal laminate configuration to maximize the flutter boundary for simply-supported symmetrically laminated plates with bending-twisting coupling. The Rayleigh -Ritz method is used to solve the natural vibration, and modal analysis using several lowest natural modes is applied to obtain the supersonic panel flutter boundary. First, the flutter characteristics are clarified with use of lamination parameters. Next, the optimal laminate configuration to maximize the flutter boundary is obtained using mathematical programming method where the lamination parameters are adopted as intermediate design variables.

Original language	English
Pages (from-to)	1013-1020
Number of pages	8
Journal	Nihon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C
Volume	64
Issue number	619
DOIs	https://doi.org/10.1299/kikaic.64.1013
Publication status	Published - 1998

Keywords

Bending-Twisting Coupling
Composite Material
Eigenvalue Analysis
Flutter
Lamination Parameter
Optimum Design
Self-Excited Vibration
Symmetric Laminates

ASJC Scopus subject areas

Mechanics of Materials
Mechanical Engineering
Industrial and Manufacturing Engineering

Access to Document

10.1299/kikaic.64.1013

Cite this

@article{46cb9f304fb44eaf925765e84f9f4771,

title = "Panel Flutter Design of Symmetrically Laminated Plates Using Lamination Parameters",

abstract = "The present paper examines the optimal laminate configuration to maximize the flutter boundary for simply-supported symmetrically laminated plates with bending-twisting coupling. The Rayleigh -Ritz method is used to solve the natural vibration, and modal analysis using several lowest natural modes is applied to obtain the supersonic panel flutter boundary. First, the flutter characteristics are clarified with use of lamination parameters. Next, the optimal laminate configuration to maximize the flutter boundary is obtained using mathematical programming method where the lamination parameters are adopted as intermediate design variables.",

keywords = "Bending-Twisting Coupling, Composite Material, Eigenvalue Analysis, Flutter, Lamination Parameter, Optimum Design, Self-Excited Vibration, Symmetric Laminates",

author = "Masaki Sato and Hisao Fukunaga and Hideki Sekine",

year = "1998",

doi = "10.1299/kikaic.64.1013",

language = "English",

volume = "64",

pages = "1013--1020",

journal = "Nihon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C",

issn = "0387-5024",

publisher = "Japan Society of Mechanical Engineers",

number = "619",

}

TY - JOUR

T1 - Panel Flutter Design of Symmetrically Laminated Plates Using Lamination Parameters

AU - Sato, Masaki

AU - Fukunaga, Hisao

AU - Sekine, Hideki

PY - 1998

Y1 - 1998

N2 - The present paper examines the optimal laminate configuration to maximize the flutter boundary for simply-supported symmetrically laminated plates with bending-twisting coupling. The Rayleigh -Ritz method is used to solve the natural vibration, and modal analysis using several lowest natural modes is applied to obtain the supersonic panel flutter boundary. First, the flutter characteristics are clarified with use of lamination parameters. Next, the optimal laminate configuration to maximize the flutter boundary is obtained using mathematical programming method where the lamination parameters are adopted as intermediate design variables.

AB - The present paper examines the optimal laminate configuration to maximize the flutter boundary for simply-supported symmetrically laminated plates with bending-twisting coupling. The Rayleigh -Ritz method is used to solve the natural vibration, and modal analysis using several lowest natural modes is applied to obtain the supersonic panel flutter boundary. First, the flutter characteristics are clarified with use of lamination parameters. Next, the optimal laminate configuration to maximize the flutter boundary is obtained using mathematical programming method where the lamination parameters are adopted as intermediate design variables.

KW - Bending-Twisting Coupling

KW - Composite Material

KW - Eigenvalue Analysis

KW - Flutter

KW - Lamination Parameter

KW - Optimum Design

KW - Self-Excited Vibration

KW - Symmetric Laminates

UR - http://www.scopus.com/inward/record.url?scp=4444369241&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=4444369241&partnerID=8YFLogxK

U2 - 10.1299/kikaic.64.1013

DO - 10.1299/kikaic.64.1013

M3 - Article

AN - SCOPUS:4444369241

SN - 0387-5024

VL - 64

SP - 1013

EP - 1020

JO - Nihon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C

JF - Nihon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C

IS - 619

ER -

Panel Flutter Design of Symmetrically Laminated Plates Using Lamination Parameters

Abstract

Keywords

ASJC Scopus subject areas

Access to Document

Other files and links

Fingerprint

Cite this