A numerical approach to evaluate temperature-dependent peridynamics damage model for destructive atmospheric entry of spacecraft

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Abstract

The evaluation of the on-ground casualty risk assessments due to a controlled or uncontrolled re-entry is highly sensitive to the accurate prediction of fragmentation events during an atmospheric re-entry. The main objective of this study is an investigation into the use of Peridynamics (PD) to improve the analysis of fragmentation during atmospheric re-entry with respect to currently adopted semi-empirical approaches. The high temperatures characterising such scenarios may substantially impact fragmentation, which requires appropriate modelling of the damage process within the PD method. The damage models in PD require experimentally determined fracture mechanical properties that are unavailable as a function of temperature. This work proposes a numerical methodology to estimate the PD damage parameters changes with temperature to enable the study of fragmentation during atmospheric re-entry. Initially, tensile-testing simulation experiments are performed in peridynamics to calibrate material parameters for steel and aluminium alloys as a function of temperature. Then, a parametric study is carried out to evaluate the temperature-dependent damage model parameters for the same materials. The applicability of the proposed methodology is showcased using a re-entry test case scenario.
Original languageEnglish
Number of pages30
JournalThe Aeronautical Journal
Early online date28 Jul 2022
DOIs
Publication statusE-pub ahead of print - 28 Jul 2022

Keywords

  • re-entry analysis
  • peridyamic simulations
  • space debris
  • damage modelling
  • design for demise

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