MME  Vol.4 No.4 , November 2014
Experimental and FEM Modal Analysis of a Deployable-Retractable Wing
Author(s) P. Jia1,2,3*, S. K. Lai4, W. Zhang3, C. W. Lim1,2
ABSTRACT
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.

Cite this paper
Jia, P. , Lai, S. , Zhang, W. and Lim, C. (2014) Experimental and FEM Modal Analysis of a Deployable-Retractable Wing. Modern Mechanical Engineering, 4, 183-197. doi: 10.4236/mme.2014.44018.
References
[1]   Zhang, W., Sun, L., Yang, X.D. and Jia, P. (2013) Nonlinear Dynamic Behaviors of a Deploying-and-Retreating Wing with Varying Velocity. Journal of Sound and Vibration, 332, 6785-6797.
http://dx.doi.org/10.1016/j.jsv.2013.08.006

[2]   Zhao, Y.H. and Hu, H.Y. (2013) Prediction of Transient Responses of a Folding Wing during the Morphing Process. Aerospace Science and Technology, 24, 89-94.
http://dx.doi.org/10.1016/j.ast.2011.09.001

[3]   Kuder, I.K., Arrieta, A.F., Raither, W.E. and Ermanni, P. (2013) Variable Stiffness Material and Structural Concepts for Morphing Applications. Progress in Aerospace Sciences, 63, 33-55.
http://dx.doi.org/10.1016/j.paerosci.2013.07.001

[4]   Coutu, D., Brailovski, V. and Terriault, P. (2010) Optimized Design of an Active Extrados Structure for an Experimental Morphing Laminar Wing. Aerospace Science and Technology, 14, 451-458.
http://dx.doi.org/10.1016/j.ast.2010.01.009

[5]   Reich, G. and Sanders, B. (2007) Introduction to Morphing Aircraft Research. Journal of Aircraft, 44, 1059.
http://dx.doi.org/10.2514/1.28287

[6]   Sofla, A.Y.N., Meguid, S.A., Tan, K.T. and Yeo, W.K. (2010) Shape Morphing of Aircraft Wing: Status and Challenges. Material and Design, 31, 1284-1292.
http://dx.doi.org/10.1016/j.matdes.2009.09.011

[7]   Peeters, M., Kerschen, G. and Golinval, J.C. (2011) Modal Testing of Nonlinear Vibrating Structures Based on Nonlinear Normal Modes: Experimental Demonstration. Mechanical System and Signal Processing, 25, 1227-1247.
http://dx.doi.org/10.1016/j.ymssp.2010.11.006

[8]   Peeters, B., Carrella, A., Lau, J., Gattp, M. and Coppotelli, G. (2011) Advanced Shaker Excitation Signals for Aerospace Testing. Advanced Aerospace Applications, 1, 229-241.

[9]   Lubrina, P., Giclais, S., Stephan, C., Boeswald, M., Govers, Y. and Botargues, N. (2014) AIRBUS A350 XWB GVT: State-of-the-Art Techniques to Perform a Faster and Better GVT Campaign. Conference Proceedings of the Society for Experimental Mechanics Series, Topics in Modal Analysis II, Vol. 8, 243-256.

[10]   Lemler, K.J. and Semke, W.H. (2013) Application of Modal Testing and Analysis Techniques on a sUAV. Conference Proceedings of the Society for Experimental Mechanics Series, Special Topics in Structural Dynamics, Vol. 6, 47-57.

[11]   Londono, J.M. and Cooper, J.E. (2014) Experimental Identification of a System Containing Geometric Nonlinearities. Proceedings of the 32nd IMAC, A Conference and Exposition on Structural Dynamics, Conference Proceedings of the Society or Experimental Mechanics Series, 7, 253-260.

[12]   Ameri, N., Grappasonni, C., Coppotelli, G. and Ewins, D.J. (2013) Ground Vibration Tests of a Helicopter Structure Using OMA Techniques. Mechanical Systems and Signal Processing, 35, 35-51.
http://dx.doi.org/10.1016/j.ymssp.2012.09.013

[13]   Lau, J., Peeters, B., Debille, J., Guzek, Q., Flynn, W., Lange, D.S. and Kahlmann, T. (2011) Ground Vibration Testing Master Class: Modern Testing and Analysis Concepts Applied to an F-16 Aircraft. Advanced Aerospace Applications, Conference Proceedings of the Society for Experimental Mechanics Series, 1, 221-228.

[14]   Trendafilova, I., Cartmell, M.P. and Ostachowicz, W. (2008) Vibration-Based Damage Detection in an Aircraft Wing Scaled Model Using Principal Component Analysis and Pattern Recognition. Journal of Sound and Vibration, 313, 560-566.
http://dx.doi.org/10.1016/j.jsv.2007.12.008

[15]   Doebling, S.W., Farrar, C.R. and Prime, M.B. (1998) A Summary Review of Vibration-Based Damage Identification Methods. The Shock and Vibration Digest, 30, 91-105.

[16]   Hu, N., Wang, X., Fukunaga, H., Yao, Z.H., Zhang, H.X. and Wu, Z.S. (2001) Damage Assessment of Structures Using Modal Test Data. International Journal of Solids and Structures, 38, 3111-3126.
http://dx.doi.org/10.1016/S0020-7683(00)00292-4

[17]   Peeters, B., Baets, P.D., Mosenich, L., Vecchio, A., Auweraer, H.V. and Lambert, F. (2005) Ground Vibration Testing in the Aeroelastic Design and Certification of a Small Composite Aircraft. 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Austin, 18-21 April 2005, 5370-5383.

[18]   EI-Kafafy, M., Guillaume, P. and Peeters, B. (2013) Modal Parameter Estimation by Combining Stochastic and Deterministic Frequency-Domain Approaches. Mechanical Systems and Signal Processing, 35, 52-68.
http://dx.doi.org/10.1016/j.ymssp.2012.08.025

[19]   Van Der Auweraer, H., Guillaume, P., Verboven, P. and Vanlandutt, S. (2001) Application of a Fast-Stabilization Frequency Domain Parameter Estimation Method. ASME Journal of Dynamic Systems, Measurement, and Control, 123, 651-658.

[20]   Heylen, W., Lammens, S. and Sas, P. (1997) Modal Analysis Theory and Testing. K. U. Leuven, Belgium.

[21]   Mala, N.M.M. and Silva, J.M.M. (1997) Theoretical and Experimental Modal Analysis. Research Studies Press, Taunton.

[22]   Pierro, E., Muchi, E., Soria, L. and Vecchio, A. (2009) On the Vibro-Acoustical Operational Modal Analysis of a Helicopter Cabin. Mechanical Systems and Signal Processing, 23, 1205-1217.
http://dx.doi.org/10.1016/j.ymssp.2008.10.009

 
 
Top