Experimental and FEM Modal Analysis of a Deployable-Retractable Wing

The aim of this paper is to conduct experimental modal analysis and numerical simulation to verify the structural characteristics of a deployable-retractable wing for aircraft and spacecraft. A modal impact test was conducted in order to determine the free vibration characteristics. Natural frequencies and vibration mode shapes were obtained via measurement in LMS Test. Lab. The frequency response functions were identified and computed by force and acceleration signals, and then mode shapes of this morphing wing structure were subsequently identified by PolyMAX modal parameter estimation method. FEM modal analysis was also implemented and its numerical results convincingly presented the mode shape and natural frequency characteristics were in good agreement with those obtained from experimental modal analysis. Experimental study in this paper focuses on the transverse response of morphing wing as its moveable part is deploying or retreating. Vibration response to different rotation speeds have been collected, managed and analyzed through the use of comparison methodology with each other. Evident phenomena have been discovered including the resonance on which most analysis is focused because of its potential use to generate large amplitude vibration of specific frequency or to avoid such resonant frequencies from a wide spectrum of response. Manufactured deployable-retractable wings are studied in stage of experimental modal analysis, in which some nonlinear vibration resulted should be particularly noted because such wing structure displays a low resonant frequency which is always optimal to be avoided for structural safety and stability.

[1]  P. Guillaume,et al.  Application of a Fast-Stabilizing Frequency Domain Parameter Estimation Method , 2001 .

[2]  Elena Pierro,et al.  On the vibro-acoustical operational modal analysis of a helicopter cabin , 2009 .

[3]  Matthew P. Cartmell,et al.  Vibration-based damage detection in an aircraft wing scaled model using principal component analysis and pattern recognition , 2008 .

[4]  Keith Worden,et al.  Damage assessment of structures V: DAMAS 2003 , 2001 .

[5]  Haiyan Hu,et al.  Prediction of transient responses of a folding wing during the morphing process , 2013 .

[6]  N. Ameri,et al.  Ground vibration tests of a helicopter structure using OMA techniques , 2013 .

[7]  Herman Van der Auweraer,et al.  Ground Vibration Testing in the Aeroelastic Design and Certification of a Small Composite Aircraft , 2005 .

[8]  W. Zhang,et al.  Nonlinear dynamic behaviors of a deploying-and-retreating wing with varying velocity , 2013 .

[9]  Ning Hu,et al.  Damage assessment of structures using modal test data , 2001 .

[10]  Paul Sas,et al.  Modal Analysis Theory and Testing , 2005 .

[11]  Gregory W. Reich,et al.  Introduction to Morphing Aircraft Research , 2007 .

[12]  Gaëtan Kerschen,et al.  Modal testing of nonlinear vibrating structures based on nonlinear normal modes: Experimental demonstration , 2011 .

[13]  Yves Govers,et al.  AIRBUS A350 XWB GVT: State-of-the-Art Techniques to Perform a Faster and Better GVT Campaign , 2014 .

[14]  William H. Semke,et al.  Application of Modal Testing and Analysis Techniques on a sUAV , 2013 .

[15]  Andres F. Arrieta,et al.  Variable stiffness material and structural concepts for morphing applications , 2013 .

[16]  Jonathan E. Cooper,et al.  Experimental Identification of a System Containing Geometric Nonlinearities , 2014 .

[17]  Charles R. Farrar,et al.  A summary review of vibration-based damage identification methods , 1998 .

[18]  Giuliano Coppotelli,et al.  Advanced shaker excitation signals for aerospace testing , 2011 .

[19]  Bart Peeters,et al.  Ground Vibration Testing Master Class: modern testing and analysis concepts applied to an F-16 aircraft , 2011 .

[20]  Shaker A. Meguid,et al.  Shape morphing of aircraft wing: Status and challenges , 2010 .

[21]  Vladimir Brailovski,et al.  Optimized design of an active extrados structure for an experimental morphing laminar wing , 2010 .

[22]  Anders Brandt,et al.  Modal Analysis Theory , 2011 .

[23]  Nuno M. M. Maia,et al.  Theoretical and Experimental Modal Analysis , 1997 .

[24]  P. Guillaume,et al.  Modal parameter estimation by combining stochastic and deterministic frequency-domain approaches , 2013 .