Thesis

Multi-disciplinary modelling of the aerothermodynamically-induced fragmentation of re-entering bodies

Downloadable Content

Download PDF
Creator
Rights statement
Awarding institution
  • University of Strathclyde
Date of award
  • 2025
Thesis identifier
  • T17356
Person Identifier (Local)
  • 202066155
Qualification Level
Qualification Name
Department, School or Faculty
Abstract
  • A globally proposed solution to remove objects from space is to make them undergo destructive atmospheric re-entry, through which they break into several fragments, eventually demising due to the high aerothermal loads experienced during the re-entry process. Therefore, accurate prediction of the destructive process and trajectory dynamics is of utmost importance to determine the re-entry safety. However, most state-of-the-art prediction tools use engineering and surrogate models that cannot capture the collision dynamics and occurring flow interactions formed by the proximity of multiple fragments in high-enthalpy regimes. To overcome this issue, this work presents the development of a multi-fidelity based tool TITAN (TransatmospherIc flighT simulAtioN). The tool handles the fragments using a common spatial domain to account for the interactions due to proximity. It also employs an automated criterion to identify the level of fidelity required at each time step, enabling switching between low-fidelity and high-fidelity models to compute the aerodynamic and aerothermodynamic quantities during the re-entry process. A detailed description of the framework is introduced in this work, along with various experimental and numerical test cases to verify and validate the implemented submodules, aimed to deliver the capability to perform a complete simulation from the re-entry interface until the ground collision. The dynamic motion of the objects is computed using the integrated 6 Degrees of Freedom (DoF) trajectory propagator under a quasi-steady assumption, enabling the analysis of the individual fragment trajectory. The framework is finally tested against two conceptual re-entry spacecraft, and an analysis of debris dispersion due to proximity interaction is conducted.
Advisor / supervisor
  • Fossati, Marco
Resource Type
DOI
Funder

Relations

Items

Thumbnail Title Date Uploaded Visibility Actions
file details PDF of thesis T17356 2025-06-03 Public Download