Abstract
Background: Structural response measurements are challenging in aerodynamic testing environments due to high-speed requirements, facility vibrations, and the desire for non-intrusive measurements. Objective: This study uses stereo digital image correlation (DIC) to investigate the response of a jointed beam under aerodynamic loading in a shock tube. Methods: The incident shock subjects the beam to an impulsive frontal load followed by periodic transverse loading from vortex shedding. Several considerations necessary to realize high-precision are addressed: first, a hybrid stereo camera calibration accounted for tangential distortions when imaging through thick windows. Second, a measurement bias from Xenon flash-lamp light sources was identified and removed using laser illumination. Third, facility motion was mitigated by vibration isolation and appropriate signal filtering. Finally, aero-optical distortions from turbulence were removed using a low-order reconstruction. Results: The resulting displacement data has a noise floor of approximately ± 1 μm at 20 kHz sampling rate. The reduction of primary noise sources allows a transient structural response on the order of 10–40 μm to be quantified. The highest vibrations occurred when the vortex shedding frequency matched the beam’s natural frequency. Conclusion: the noise reduction techniques described allow for structural measurements requiring high-precision, non-intrusive displacement data to be performed in aerodynamic environments.
Similar content being viewed by others
References
Sarpkaya T (2004) A critical review of the intrinsic nature of vortex-induced vibrations. J. Fluids Struct. 19(4):389–447
Wagner JL, Casper KM, Beresh SJ, Hunter PS, Spillers RW, Henfling JF (2016) Response of a store with tunable natural frequencies in compressible cavity flow. AIAA J 54(8):2351–2360
DR. Blackman, DM. Clark, GJ. McNulty and JF. Wilby 1966, "a review of flight and wind tunnel measurements of boundary layer pressure fluctuations and induced structural response," NASA-CR-626
Casper KM, Beresh SJ, Henfling JF, Spillers RW, Hunter PS, Spitzer SM (2018) "hypersonic fluid-structure interactions on a slender cone," AIAA, pp 2018–1825
Currao G, Neely AJ, Buttsworth DR, Choudhury R (2016) Measurement and simulation of hypersonic-fluid-structural interaction on a cantilevered plate in a Mach 6 flow. AIAA, pp 2016–1088
Maestrello L, Linden TLJ (1971) Measurements of the response of a panel excited by shock boundary-layer interaction. J Sound Vib 16(3):385–391
Willems S, Gulhan A, Esser B (2013) Shock induced fluid-structure interaction on a flexible wall in supersonic turbulent flow. In: Progress in Flight Physics, vol 5, pp 285–308
Perez R, Bartram G, Beberniss T, Wiebe R, Spottswood SM (2017) Calibration of aero-structural reduced order models using full-field experimental measurements. Mech Syst Signal Process 86:49–65
Maestrello L (2000) Control of shock loading from a jet in a flexible structure's presence. AIAA J 38(6):972–977
Hortensius R, Dutton JC, Elliott GS (2017) Simultaneous Flowfield and Surface-Deflection Measurements of an axisymmetric jet and adjacent surface. AIAA Journal 56(3)
Dowell EH (1970) Panel flutter - a review of the aeroelastic stability of plates and shells. AIAA J 8(3):385–399
Segalman DJ (2005) A four-parameter Iwan model for lap-type joints. J. Appl. Mech. 72:752–760
Iwan WD (1966) A distributed-element model for hysteresis and its steady-state dynamic response. J Appl Mech 33:893–900
De Wit CC, Olsson H, Astrom KJ, Lischinsky P (1995) A new model for control of systems with friction. IEEE Trans Autom Control 40:419–425
JL. Wagner, SJ. Beresh, EP. DeMauro, KM. Casper, DR. Guildenbecher, BO. Pruett and P. Farias 2018, “Pulse-burst PIV measurements of transient phenomena in a shock tube,” Exp Fluids
Lynch KP, Wagner JL (2018) time-resolved pulse-burst tomographic PIV of impulsively-started cylinder wakes in a shock tube. AIAA, pp 2018–2038
Spottswood SM, Beberniss TJ, Eason TG, Perez RA, Donbar JM, Ehrhardt DA, Riley ZB (2019) Exploring the response of a thin, flexible panel to shock-turbulent boundary-layer interactions. J Sound Vib 443:74–89
Riley ZB, Perez RA, Bartram GW, Spottswood SM, Smarslok BP, Beberniss TJ (2019) Aeothermoelastic experimental design for the AEDC/VKF tunnel C: challenges associated with measuring the response of flexible panels in high-temperature, high-speed wind tunnels. J Sound Vib 441:96–105
Ogg DR, Rice BE, Peltier SJ, Staines JT, Claucherty SL, Combs CS (2018) Simultaneous stereo digital image correlation and pressure-sensitive paint measurements of a compliant panel in a Mach 2 wind tunnel. AIAA Paper:2018–3869
Wagner JL, Beresh SJ, Kearney SP, Trott WM, Casteaneda JN, Pruett BO, Baer MR (2012) A multiphase shock tube for shock wave interaction with dense particle fields. Exp Fluids 52(6):1507–1517
H. Mirels and W. Braun 1957, “Nonuniformities in shock-tube flow due to unsteady-boundary-layer action,”
JL. Wagner, EP. DeMauro, KM. Casper, SJ. Beresh, BO. Pruett and KP. Lynch 2018, “Pulse-burst PIV of an impulsively started cylinder in a shock tube for Re > 10^5," Experiments in Fluids, vol. 59, no. 106
Merzkirch W (2012) Flow visualization. Academic Press
KP. Lynch, EM. Jones, AR. Brink, DP. Rohe, RJ. Kuether, JL. Wagner, A. Mathis and D. Quinn 2019 2019, “Response of jointed-structures in a shock tube: simultaneous PSP and DIC with comparison to modeling,” AIAA Paper 2019-3654
EM. C. Jones and MA. Iadicola 2018, "A good practice guide for digital image correlation," International Digital Image Correlation Society
Taira K, Brunton S, Dawson S, Rowley C, Colonius T, McKeon B, Schmidt O, Gordeyev S, Theofilis V, Ukeiley L (2017) Modal analysis of fluid flows: an overview. AIAA J 55(12):4013–4041
Acknowledgements
Caroline Winters, Michael Clemenson, and Patrick Barnett are kindly acknowledged for their help with the spectroscopy of the flashlamp sources. For machining of the beam and setup of the test section, the support of Tom Grasser, Paul Farias, and Seth Spitzer is greatly appreciated. The help of Phillip Reu for reviewing the manuscript is also appreciated.
Sandia National Laboratories is a multimission laboratory managed and operated by National Technology & Engineering Solutions of Sandia, LLC, a wholly owned subsidiary of Honeywell International Inc., for the U.S. Department of Energy’s National Nuclear Security Administration under contract DE-NA0003525. This paper describes objective technical results and analysis. Any subjective views or opinions that might be expressed in the paper do not necessarily represent the views of the U.S. Department of Energy or the United States Government.
Funding
This study was funded by the Sandia Laboratory Directed Research and Development (LDRD) program.
Author information
Authors and Affiliations
Corresponding author
Ethics declarations
Conflict of Interest
The authors declare that they have no conflicts of interest.
Additional information
Publisher’s Note
Springer Nature remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.
Rights and permissions
About this article
Cite this article
Lynch, K.P., Jones, E.M.C. & Wagner, J.L. High-Precision Digital Image Correlation for Investigation of Fluid-Structure Interactions in a Shock Tube. Exp Mech 60, 1119–1133 (2020). https://doi.org/10.1007/s11340-020-00610-8
Received:
Accepted:
Published:
Issue Date:
DOI: https://doi.org/10.1007/s11340-020-00610-8