Comparison between two spacecraft-oriented tools: PAMPERO &amp; SCARAB

Annaloro, Julien; Galera, Stéphane; Kärräng, P.; Prigent, G.; Lips, T.; Omaly, Pierre

doi:10.1016/j.jsse.2017.02.004

Cited by 10 publications

(8 citation statements)

References 2 publications

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“…The critical stretch damage model is used to allow for the propagation of cracks in the DLSP specimen and using the Equation (11) gives a value of s c = 4.82 × 10 −3 . The loading rate of 1mm/min used in Ref.…”

Section: Diagonally Loaded Square Plate (Dlsp)mentioning

confidence: 99%

“…On the other hand, spacecraft-oriented tools model the spacecraft to a high granularity level consistent with the real design. The aerodynamic and aerothermodynamic coefficients are calculated for realistic and complex geometries [11] as opposed to the primitive shapes of object-oriented codes. Breakup events are then computed by analysing mechanical loads at pre-defined sections/cuts using simplified breaking stress criteria [13] and accurate thermal load modelling for material ablation.…”

Section: Introductionmentioning

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%

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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: Diagonally Loaded Square Plate (Dlsp)mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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 ONERA engineering code ARES (Atmospheric Re-Entry Software) couples 4 independent codes: MUSIC (flight mechanics solver), FAST, 8,9 (aerodynamics and aerothermodynamics solver), AtMoS (atmospheric conditions solver) and MoDeTheC (heat and mass transfers as well as thermal degradation within the material). In the first part of this project, only FAST is considered to quickly calculate aerodynamic force and moment coefficients as well as wall heat flux at specific flight points or along complete Earth and Mars atmospheric entry trajectories.…”

Section: Computational Strategymentioning

confidence: 99%

EFESTO - advancing European hypersonic inflatable heatshield technology for Earth recovery and Mars high-mass delivery missions

Guidotti¹,

Fuentes²,

Trovarelli³

et al. 2022

AAOAJ

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The European Union H2020 EFESTO project is coordinated by DEIMOS Space with the end goals of improving the European TRL of Inflatable Heat Shields for re-entry vehicles (from 3 to 4/5) and paving the way towards further improvements (TRL 6 with a future In-Orbit Demonstrator). This paper presents the project objectives and provides with a general overview of the activities ongoing and planned for the next two years, promoting its position in the frame of a European re-entry technology roadmap. EFESTO aims at (1) the definition of critical space mission scenarios (Earth and Mars applications) enabled by the use of advanced inflatable Thermal Protection Systems (TPS), (2) characterization of the operative environment and (3) validation by tests of both the flexible materials needed for the thermal protection (flexible thermal blanket will be tested in arcjet facility in both Earth and Martian environments) and the inflatable structure at 1:2 scale (exploring the morphing dynamics and materials response from packed to fully inflated configuration). These results will be injected into the consolidated design of a future In-Orbit Demonstrator (IOD) mission.

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“…Currently, re-entry simulation of such space debris components relies on correlation-based codes which include many assumptions regarding the thermal degradation of COPVs [9,10]. This results in large uncertainties regarding the risk assessment of impact to ground.…”

Section: Introductionmentioning

confidence: 99%

Study of the degradation of epoxy resins used in spacecraft components by thermogravimetry and fast pyrolysis

Torres-Herrador

Eschenbacher

Blondeau

et al. 2022

Journal of Analytical and Applied Pyrolysis

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Comparison between two spacecraft-oriented tools: PAMPERO & SCARAB

Cited by 10 publications

References 2 publications

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

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

EFESTO - advancing European hypersonic inflatable heatshield technology for Earth recovery and Mars high-mass delivery missions

Study of the degradation of epoxy resins used in spacecraft components by thermogravimetry and fast pyrolysis

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