Abstract
Piccolo tubes are parts of aircraft wings anti-icing system and consist of titanium pipes inserted into the internal structure of the slat. Due to differential thermal expansion, clearances between the tube and its support are unavoidable and cause the overall system to exhibit highly nonlinear behavior, resulting from impacts and friction. This paper addresses the identification and modeling of the nonlinearities present in the slat-Piccolo tube connection. The complete identification procedure, from nonlinearity detection and characterization to parameter estimation, is carried out based upon sine-sweep measurements. The use of several techniques, such as the acceleration surface method, enables to understand the complex dynamics of the Piccolo tube and build a reliable model of its nonlinearities. In particular, the parameters of nonsmooth nonlinear stiffness and damping mechanisms are estimated. The nonlinear model is finally validated on standard qualification tests for airborne equipments.
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References
Van Der Vorst, R., Magerman, J., Bernay, B., Vandenberk, S., et al.: Vibration qualification test of an aircraft piccolo tube using multiple-input-multiple-output control technology. SAE technical paper, 2013-01-2315 (2013)
Masri, S.F., Caughey, T.K.: A nonparametric identification technique for nonlinear dynamic problems. J. Appl. Mech. 46, 433–447 (1979)
Dossogne, T., et al.: Nonlinear ground vibration identification of an F-16 aircraft – part II understanding nonlinear behaviour in aerospace structures using sine-sweep testing. In: Proceedings of the International Forum on Aeroelasticity and Structural Dynamics, St-Petersburg (2015)
Pintelon, R., Schoukens, J.: System Identification: A Frequency Domain Approach. IEEE Press, Piscataway (2001)
Noël, J.-P., Renson, L., Kerschen, G.: Complex dynamics of a nonlinear aerospace structure: experimental identification and modal interactions. J. Sound Vib. 33, 2588–2607 (2014)
Lankarani, H.M., Nikravesh, P.E.: A contact force model with hysteresis damping for impact analysis of multibody systems. J. Mech. Des. 112, 369–376 (1990)
RTCA SC-135: Environmental conditions and test procedures for airborn equipment. RTCA, Washington, DC (2010)
Acknowledgements
The authors T. Dossogne and J.P. Noël are Research Fellow (FRIA fellowship) and Postdoctoral Researcher, respectively, of the Fonds de la Recherche Scientifique – FNRS which is gratefully acknowledged.
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© 2019 The Society for Experimental Mechanics, Inc.
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Dossogne, T., Trillet, P., Schoukens, M., Bernay, B., Noël, J.P., Kerschen, G. (2019). Nonlinearities of an Aircraft Piccolo Tube: Identification and Modeling. In: Barthorpe, R. (eds) Model Validation and Uncertainty Quantification, Volume 3. Conference Proceedings of the Society for Experimental Mechanics Series. Springer, Cham. https://doi.org/10.1007/978-3-319-74793-4_8
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DOI: https://doi.org/10.1007/978-3-319-74793-4_8
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