The effect of exit velocity and material on the sabot separation launched by ground-based railgun

Hirotaka Kasahara, Akiko Matsuo

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

In this paper, the sabot separation process in super/hypersonic flight from 600 to 2501 m/s is numerically investigated by using CFD and RBD (Rigid Body Dynamics). Firstly, the motion of sabot separation is calculated for validating our in-house code. CFD-RBD code shows good agreements with Mehmet’s experiment. Secondary, the effects of exit velocity from muzzle are examined. While all sabot velocities differ, sabot separations indicate the same trajectory. The variation of sabot velocity can be eliminated by non-dimensionalization considering exit velocity. Finally, the effects of sabot material, which means mass density, are investigated with railgun acceleration condition. Sabot separation shows different motion completely depending on sabot material. However, non-dimensionalization eliminates the effect of sabot material on separation. Proposed non-dimensionalization method can represent the various sabot separation motions in unique one trajectory, considering exit velocity and sabot density in time term.

Original languageEnglish
Title of host publication2018 Applied Aerodynamics Conference
Publisher[publishername] American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105593
DOIs
Publication statusPublished - 2018 Jan 1
Event36th AIAA Applied Aerodynamics Conference, 2018 - [state] GA, United States
Duration: 2018 Jun 252018 Jun 29

Other

Other36th AIAA Applied Aerodynamics Conference, 2018
CountryUnited States
City[state] GA
Period18/6/2518/6/29

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering

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  • Cite this

    Kasahara, H., & Matsuo, A. (2018). The effect of exit velocity and material on the sabot separation launched by ground-based railgun. In 2018 Applied Aerodynamics Conference [AIAA 2018-3819] [publishername] American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-3819