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A Novel Method to Correlate a Rocket Launcher Finite Element Model Using Experimental Modal Test Measurements and Identification Algorithms

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Shock & Vibration, Aircraft/Aerospace, Energy Harvesting, Acoustics & Optics, Volume 9

Abstract

The structural dynamics of a launcher system used to guide the initial trajectory of target test missiles is considered. Launcher induced body rates alter the trajectories of target vehicles at egress which can detrimentally affect the successful execution of flight test missions. As a result, flight mission analysts must have the capability to accurately reproduce the dynamic response of the launcher system to evaluate its effect on launch vehicle egress. Accurately reproducing this response requires a high fidelity finite element model that is correlated to modal survey test data. An experimental modal survey of a modified Nike-Hercules launch system is conducted and modal parameters are determined using conventional and output-only methodologies. A model correlation procedure is proposed and utilized that incorporates these experimentally determined modal parameters in conjunction with a set of correlation criteria to improve the accuracy of a high-fidelity launcher finite element model. After several iterations of the model correlation procedure, the model is able to accurately reproduce the dominant dynamic behaviors observed in the modal survey tests, especially at the key location of the launcher tip. This approach provides a basis for future launcher simulation and modeling efforts.

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Abbreviations

DFT:

Discrete Fourier transform

ERA:

Eigensystem realization algorithm

FE:

Finite element

FRF:

Frequency response function

FRM:

Frequency response matrix

IRF:

Impulse response function

IRM:

Impulse response matrix

MAC:

Modal assurance criterion

POD:

Proper orthogonal decomposition

POM:

Proper orthogonal modes

POV:

Proper orthogonal values

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Acknowledgments

The authors would like to thank Dr. Brian Feeny for his guidance on Output Only modal identification methodologies and Mrs. Heather Borowski for her work on the launcher finite element model.

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Authors and Affiliations

  1. The Johns Hopkins University Applied Physics Laboratory, 11100 Johns Hopkins Road, Laurel, MD, 20723, USA

    Ronald N. Couch, Eliott J. Radcliffe & Rickey A. Caldwell

Authors
  1. Ronald N. Couch
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  2. Eliott J. Radcliffe
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  3. Rickey A. Caldwell
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Corresponding author

Correspondence to Ronald N. Couch .

Editor information

Editors and Affiliations

  1. Department of Technology and Innovation, University of Southern Denmark, Copenhagen, Denmark

    Anders Brandt

  2. Canadian Space Agency, Montreal, Canada

    Raj Singhal

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© 2016 The Society for Experimental Mechanics, Inc.

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Couch, R.N., Radcliffe, E.J., Caldwell, R.A. (2016). A Novel Method to Correlate a Rocket Launcher Finite Element Model Using Experimental Modal Test Measurements and Identification Algorithms. In: Brandt, A., Singhal, R. (eds) Shock & Vibration, Aircraft/Aerospace, Energy Harvesting, Acoustics & Optics, Volume 9. Conference Proceedings of the Society for Experimental Mechanics Series. Springer, Cham. https://doi.org/10.1007/978-3-319-30087-0_14

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  • DOI: https://doi.org/10.1007/978-3-319-30087-0_14

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  • Publisher Name: Springer, Cham

  • Print ISBN: 978-3-319-30086-3

  • Online ISBN: 978-3-319-30087-0

  • eBook Packages: EngineeringEngineering (R0)

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