Hypervelocity Impact Simulation using Smoothed-Particle Hydrodynamics

Master thesis (2023)

Authors

M.M. Harazim Aerospace Engineering

Contributors

C. Bisagni Aerospace Structures & Computational Mechanics - Aerospace Engineering (supervisor 1)
T. Cardone Aerospace Structures & Computational Mechanics - Aerospace Engineering (supervisor 2)
Faculty
Aerospace Engineering
Copyright: © 2023 Mateusz Harazim
Simulation Aluminium ESA SPH Space Debris LS-DYNA Smoothed-Particle Hydrodynamics Hypervelocity impact High-speed Impact Whipple Shield
More Info
expand_more

Published Date

22-02-2023

Language

English

Reuse Rights

Other than for strictly personal use, it is not permitted to download, forward or distribute the text or part of it, without the consent of the author(s) and/or copyright holder(s), unless the work is under an open content license such as Creative Commons.

Faculty

Aerospace Engineering

Abstract

The issue of space debris in Low Earth Orbit is a growing concern that requires comprehensive solutions. This includes preventing further pollution, removing existing debris, and designing resilient spacecraft that can withstand impacts. This thesis focuses on the improvement of spacecraft shielding structures to provide effective protection against hypervelocity impacts. The Smoothed-Particle Hydrodynamics method was used for the simulation of hypervelocity impacts using LS-DYNA. The method is preferred for the simulation of impacts at high velocity and was used to reproduce two studies from the past. The simulation was then performed on a double plate system, with results compared to data from experiments provided by Airbus Defence and Space GmbH, under co-supervison from ESA. The simulation accurately predicted the hole diameter in the 1st plate with less than 2% error, while the damage zone in the second plate showed considerable variance. The simulations consistently overpredict the damage zone, leading to conservative results.