Influence of Rarefied Gas Flow on Re-entry Survivability of Space Debris

Koppenwallner, G.; Lips, T.

doi:10.1063/1.3076574

Cited by 5 publications

(8 citation statements)

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“…It is important to note that the actual flight data to mimic a natural re-entry of ATV-1 is unavailable for usage. However, detailed simulations of the ATV-1 re-entry analysis were performed using SCARAB [49] code, a spacecraft-oriented tool, due to a contract for ESA/ESTEC [33, 50]. A high granularity model was used for SCARAB simulations is as seen in Ref.…”

Section: Resultsmentioning

confidence: 99%

“…Hence, low-fidelity tools have been introduced to mitigate the cost by using analytical approximations of aerodynamic and aerothermodynamic parameters but these tools come at the cost of increased uncertainty. In-general, re-entry analysis codes can be classified into two categories [4], (a) object-oriented [5, 6, 7, 8, 9, 10] and (b) spacecraft-oriented [11, 12]. The object-oriented approach is characterised by approximating the spacecraft model and its components into a set of primitive elements like spheres, cylinders and flat plates, essentially reducing the modelling complexity.…”

Section: Introductionmentioning

confidence: 99%

“…The Jules Verne Automated Transfer Vehicle (ATV-1) [33] was chosen as a reference test case scenario to test the current methodology and the usability of PD in predicting re-entry fragmentation. The structural fragmentation of the solar panels is thought to have occurred before the melt-based fragmentation [12, 33] during ATV-1’s actual re-entry, which is an intriguing aspect of this test case. For a more general use, the solar panel fragmentation is always assumed to occur at 95km altitude for object-oriented simulation purposes.…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

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 simulation and experimental investigation of this complex process was out of the scope of our present work. Such computations have been performed in the prediction of break‐up and survival of spacecrafts and satellites (e.g., Allen & Eggers, ; Bouslog et al ; Fritsche et al , ; Klinkrad ; Klinkrad et al ; Koppenwallner et al ; Rochelle et al ).…”

Section: Discussionmentioning

confidence: 99%

“…We assumed that the size (radius) of a given orbiting and falling particle is constant. The burning is a very complex thermo‐ and aerodynamical chemical process depending on the shape and composition of the particle as well as on the local composition and density of the atmosphere (Allen & Eggers ; Bouslog et al ; Fritsche et al ; Fritsche et al ; Klinkrad ; Klinkrad et al ; Koppenwallner et al ; Rochelle et al ). Involving the particle burning into our model could be an important task of a separate paper.…”

Section: Model and Methodsmentioning

confidence: 99%

Dynamics of spherical space debris of different sizes falling to Earth

et al. 2020

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Space debris larger than 1 cm can damage space instruments and impact Earth. The low-Earth orbits (at heights smaller than 2,000 km) and orbits near the geostationary-Earth orbit (at 35,786 km height) are especially endangered because most satellites orbit at these latitudes. With current technology, space debris smaller than 10 cm cannot be tracked. Smaller space debris fragments burn up and evaporate in the atmosphere, but larger ones fall to Earth's surface.For practical reasons, it would be important to know the mass, composition, shape, velocity, direction of motion, and impact time of space debris re-entering the atmosphere and falling to Earth. Since it is very difficult to measure these physical parameters, almost nothing is known about them. To partly fill this gap, we performed computer modeling with which we studied the dynamics of spherical re-entry particles falling to Earth due to air drag. We determined the time, velocity, and angle of impact as functions of the launch height, direction, speed, and size of spherical re-entry particles. Our results can also be used for semispherical meteoroid particles of the interplanetary dust entering the Earth's atmosphere.

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