Verification and Application of the Sam Re-Entry Model

Beck, James C.; Merrifield, J. A.; Markelov, G. N.; Holbrough, Ian; Molina, Rafael Cuevas

doi:10.1007/978-3-319-15982-9_50

Cited by 2 publications

(3 citation statements)

References 6 publications

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“…In this paragraph a comparison is presented between the presented model and the results obtained by the re-entry code Spacecraft Aerothermal Model (SAM) [28] from Belstead Research [34] for a variety of standard test cases presented during the First Demise Workshop [35]. All the simulation have been performed with the initial conditions summarised in Table 3, for four different geometrical shapes (sphere, cylinder, box and flat plate) and for two materials (aluminium 7075-T6 and titanium 6Al-4V).…”

Section: Model Validationmentioning

confidence: 99%

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Demisability and survivability sensitivity to design-for-demise techniques

2018

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The paper is concerned with examining the effects that design-for-demise solutions can have not only on the demisability of components, but also on their survivability that is their capability to withstand impacts from space debris. First two models are introduced. A demisability model to predict the behaviour of spacecraft components during the atmospheric re-entry and a survivability model to assess the vulnerability of spacecraft structures against space debris impacts. Two indices that evaluate the level of demisability and survivability are also proposed. The two models are then used to study the sensitivity of the demisability and of the survivability indices as a function of typical design-for-demise options. The demisability and the survivability can in fact be influenced by the same design parameters in a competing fashion that is while the demisability is improved, the survivability is worsened and vice versa. The analysis shows how the design-for-demise solutions influence the demisability and the survivability independently. In addition, the effect that a solution has simultaneously on the two criteria is assessed. Results shows which, among the design-for-demise parameters mostly influence the demisability and the survivability. For such design parameters maps are presented, describing their influence on the demisability and survivability indices. These maps represent a useful tool to quickly assess the level of demisability and survivability that can be expected from a component, when specific design parameters are changed.  Abbreviations DRAMA: Debris Risk Assessment and Mitigation Analysis MASTER: Meteoroid and Space Debris Terrestrial Environment Reference MIDAS: MASTER-based Impact Flux and Damage Assessment Software LMF: Liquid Mass Fraction PNP: Probability of no-penetrationamong these mitigation measures is the limitation of the long-term presence of spacecraft and upper stages in the Low Earth Orbit (LEO) and Geostationary Orbit (GEO) protected regions [5]. This in turn means that a spacecraft has to be removed from its operational orbit after its decommissioning, either by placing it in a graveyard orbit or by allowing it to re-enter into the Earth's atmosphere. For LEO spacecraft, the preferred scenario is to design a disposal by re-entry within 25 years from its decommissioning in order for the mission to comply with the 25-year rule [6]. However, when a spacecraft is to be disposed through re-entry it has also to satisfy the requirement for the limitation of the risk of human casualty on the ground associated to the debris surviving the re-entry. This can be either achieved performing a controlled re-entry, where the spacecraft is guided to impact in the ocean or not populated areas, or through an uncontrolled re-entry, where the vehicle is left to re-enter without any guidance. In the latter case, the surviving mass of the spacecraft has to be low enough to comply with the regulation on the casualty risk expectation that has to be below the threshold of 10 -4 . Controlled re-entries ha...

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Section: Model Validationmentioning

confidence: 99%

“…In fact, the differences between the stagnation point correlations are of the order of 8% [36] and the variability among the shape factor can be up to 20% [27]. The data used for the comparison are publicly available from the Belstead Research website [34].…”

Section: Model Validationmentioning

confidence: 99%

Demisability and survivability sensitivity to design-for-demise techniques

2018

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“…Several experiments have been carried out to analyse and create new fragmentation criteria for re-entry tools [21,22,23]. However, these criteria are usually very specific to particular types of connections between different modules of re-entry objects as described in Ref.…”

Section: Introductionmentioning

confidence: 99%

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

Peddakotla

Yuan²,

Minisci³

et al. 2022

Aeronaut. j.

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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.

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Verification and Application of the Sam Re-Entry Model

Cited by 2 publications

References 6 publications

Demisability and survivability sensitivity to design-for-demise techniques

Demisability and survivability sensitivity to design-for-demise techniques

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

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