ExoMars 2016: Schiaparelli coasting, entry and descent post flight mission analysis

Bonetti, Davide; Zaiacomo, Gabriele De; Blanco, Gonzalo; Fuentes, Irene Pontijas; Portigliotti, S.; Bayle, Olivier; Lorenzoni, L.

doi:10.1016/j.actaastro.2018.05.029

Cited by 16 publications

(3 citation statements)

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“…From these results, and in coordination with system design activities, specifications for the design of key subsystems have been derived, in particular the F-TPS (section VI) and the inflatable structure (section VII), and for the identification of testing conditions for plasma wind tunnel (section VIII) and IS ground tests (section IX). The design methodology relies on the company's experience and flight qualified tools successfully applied to missions like ESA's IXV 23 or ESA/ Roscosmos' ExoMars16 Schiaparelli. 24 A synthesis of the results of the first steps of the design methodology are presented (reference mission and expected worst case performance) while the verification of the design (through Monte Carlo simulation and detailed assessment of margins to design constraints) is ongoing at the time of writing this paper and will be presented in a future paper.…”

Section: Mission Engineering and Gncmentioning

confidence: 99%

“…The design methodology relies on the company's experience and flight qualified tools successfully applied to missions like ESA's IXV 23 or ESA/ Roscosmos' ExoMars16 Schiaparelli. 24 A synthesis of the results of the first steps of the design methodology are presented (reference mission and expected worst case performance) while the verification of the design (through Monte Carlo simulation and detailed assessment of margins to design constraints) is ongoing at the time of writing this paper and will be presented in a future paper. At GNC subsystem level, the concept design of the overall hardware elements and of the onboard software logics is ongoing to guarantee the proper execution of the sequence of flight mission phases, in particular for the controlled ones.…”

Section: Mission Engineering and Gncmentioning

confidence: 99%

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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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Section: Mission Engineering and Gncmentioning

confidence: 99%

Section: Mission Engineering and Gncmentioning

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

View full text Add to dashboard Cite

show abstract

“…Then at a later time, the outcome of the Schiaparelli flight anomaly investigation was officially presented (T. Tolker-Nielsen, 2017) and the results of the analysis published (e.g. Portigliotti et al 2017, Bonetti et al 2018 as were the results of the AMELIA reconstructions (Aboudan et al 2018).…”

Section: Surface Sciencementioning

confidence: 99%

ExoMars Atmospheric Mars Entry and Landing Investigations and Analysis (AMELIA)

et al. 2019

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The entry, descent and landing of Schiaparelli, the ExoMars Entry, descent and landing Demonstrator Module (EDM), offered a rare (once-per-mission) opportunity for in situ investigations of the martian environment over a wide altitude range. The aim of the ExoMars AMELIA experiment was to exploit the Entry, Descent and Landing System (EDLS) engineering measurements for scientific investigations of Mars' atmosphere and surface. Here we present the simulations, modelling and the planned investigations prior to the Entry, Descent and Landing (EDL) event that took place on 19 th October 2016. Despite the unfortunate conclusion of the Schiaparelli mission, flight data recorded during the entry and the descent until the loss of signal, have been recovered. These flight data, although limited and affected by transmission interruptions and malfunctions, are essential for investigating the anomaly and validating the EDL operation, but can also contribute towards the partial achievement of AMELIA science objectives.

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The ExoMars Schiaparelli Entry, Descent and Landing Demonstrator Module (EDM) System Design

Ball

Blancquaert²,

Bayle³

et al. 2022

Space Sci Rev

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The Entry, Descent and Landing Demonstrator Module (EDM) named Schiaparelli, was the ESA-led Mars lander element of the ESA-Roscosmos ExoMars 2016 mission. Following launch on 14 March 2016 with the ExoMars Trace Gas Orbiter (TGO) and cruise to Mars, Schiaparelli separated for encounter with Mars to demonstrate entry, descent and landing technologies. Although on 19 October 2016 the final touchdown and surface operation were not achieved, other aspects were demonstrated and reported via real-time telemetry transmitted at 8 kbps in UHF during entry and descent.This paper presents a technical description of the elements of the Schiaparelli EDM system and its operation, plus reference to published post-flight analyses of the data obtained.

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ExoMars 2016: Schiaparelli coasting, entry and descent post flight mission analysis

Cited by 16 publications

References 1 publication

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

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

ExoMars Atmospheric Mars Entry and Landing Investigations and Analysis (AMELIA)

The ExoMars Schiaparelli Entry, Descent and Landing Demonstrator Module (EDM) System Design

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