Aircraft flutter prediction using experimental modal parameters-Reference-Cited by-同舟云学术

Aircraft flutter prediction using experimental modal parameters

Published:2013-03-15 Issue:2 Volume:85 Page:87-96
ISSN:0002-2667
Container-title:Aircraft Engineering and Aerospace Technology
language:en
Short-container-title:

Author:

Pankaj Achuthan C.,Shanthini G.,Shivaprasad M.V.,Manjuprasad M.

Abstract

PurposeTraditional dynamic and flutter analysis demands a detailed finite element model of the aircraft in terms of its mass and stiffness distribution. However, in absence of these details, modal parameters obtained from experimental tests can be used to predict the flutter characteristics of an aircraft. The purpose of this paper is to develop an improved and reliable method to predict the flutter characteristics of an aircraft structure of unknown configuration under an anticipated aerodynamic loading using software such as MSC Nastran and experimental modal parameters (such as mode shapes, natural frequencies and damping) from ground vibration tests.Design/methodology/approachA finite element model with nodes representing the test points on the aircraft is created with appropriate boundary constraints. A direct matrix abstraction program has been written for NASTRAN software that carries out a normal modes analysis and replaces the mass normalized eigenvalues and vectors with the experimentally obtained modal parameters. The flutter analysis proceeds with the solution of the flutter equation in the flutter module of NASTRAN.FindingsThe method has been evaluated for a light composite aircraft and its results have been compared with flight flutter tests and the flutter speeds obtained from the finite element model with actual stiffness and mass distributions of the aircraft.Research limitations/implicationsThe methodology developed helps in the realistic prediction of flutter characteristics of a structure with known geometric configuration and does not need material properties, mass or stiffness distributions. However, experimental modal parameters of each configuration of the aircraft are required for flutter speed estimation.Practical implicationsThe proposed methodology requires experimental modal parameters of each configuration of the aircraft for flutter speed estimation.Originality/valueThe paper shows that an effective method to predict flutter characteristics using modal parameters from ground vibration tests has been developed.

Publisher

Emerald

Reference13 articles.

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2. Chan‐gi, P. and Shun‐fat, L. (2011), Reduced Uncertainties in the Flutter Analysis of the Aerostructures Test Wing, NASA/TM – 2011 – 216421, Dryden Flight Research Center, Edwards, CA, January.

3. Freudinger, L.C. (1989), Flutter Clearance of the F‐18 High‐Angle‐of‐Attack Research Vehicle with Experimental Wingtip Instrumentation Pods, NASA‐TM‐4148, NASA, Washington, DC, October.

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