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Derivations of Knockdown Factors for Cylindrical Structures Considering Different Initial Imperfection Models and Thickness Ratios

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Abstract

This work conducts postbuckling analyses of axial-loaded cylinders and derives shell knockdown factors for the buckling design of space launch vehicle structures. Simple isotropic cylinders without stiffeners are considered as analysis models, and a commercial nonlinear finite element analysis code, ABAQUS, is used for the present postbuckling analyses. Two different methods, single perturbation load approach (SPLA) and multiple perturbation load approach (MPLA), are used for modeling the geometrically initial imperfection of a cylinder. In addition, various shell-thickness ratios (ratio of radius to thickness) are considered to derive knockdown factors using SPLA. In the postbuckling analyses, local and global bucklings are investigated and, using the obtained analysis results, the shell knockdown factors are derived for the buckling design of launch vehicle structures. The MPLA, with more perturbation loads, provides lower knockdown factors. Furthermore, for the three different thickness ratios, the knockdown factors derived using the SPLA all are higher than the values using NASA’s buckling design criteria, and they are nearly constant with respect to shell-thickness ratios.

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Acknowledgements

This work was supported by research on the preceding technologies for geostationary satellite launch vehicle of the Korea Aerospace Research Institute (KARI).

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Authors and Affiliations

  1. Department of Aerospace Engineering, Chungnam National University, Daejeon, 34134, Korea

    Chang-Hoon Sim, Han-Il Kim, Ye-Lin Lee & Jae-Sang Park

  2. Launcher Performance Team, Korea Aerospace Research Institute, Daejeon, 34133, Korea

    Keejoo Lee

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  1. Chang-Hoon Sim
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  2. Han-Il Kim
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  3. Ye-Lin Lee
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  4. Jae-Sang Park
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Correspondence to Jae-Sang Park.

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Sim, CH., Kim, HI., Lee, YL. et al. Derivations of Knockdown Factors for Cylindrical Structures Considering Different Initial Imperfection Models and Thickness Ratios. Int. J. Aeronaut. Space Sci. 19, 626–635 (2018). https://doi.org/10.1007/s42405-018-0069-4

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  • DOI: https://doi.org/10.1007/s42405-018-0069-4

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