D. Bonetti , I. Pontijas Fuentes , G. Blanco Arnao , G. De Zaiacomo , L. Lorenzoni

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_1280821

This paper focuses on the Entry, Descent and Landing (EDL) Mission Analysis verification activities of the ESA/Roscosmos ExoMars 2020 mission, presenting the activities performed by DEIMOS Space in the programme Phase C to support the EDL Critical Design Review (CDR) in strict collaboration with Thales Alenia Space. The ExoMars 2020 mission consists of a Carrier Module (CM), provided by ESA, and a Descent Module, provided by Roscosmos with contributions by ESA and the European industry, which will be in charge of delivering the surface platform and the rover to the surface of Mars. The Descent Module (DM) will separate from the carrier shortly before reaching the Martian atmosphere. During the descent phase, a heat shield will protect the payload from the severe heat flux. Parachutes, thrusters, and landing systems will reduce the speed, allowing a controlled landing on the surface of Mars. After the separation, the carrier module will breakup into Martian atmosphere. The Mission Analysis activities presented in this paper focus on the DM flying qualities analysis, the EDL trajectory analysis and performance (including the CM-DM separation analysis) and at inspecting the applicable Martian atmospheric models. Flight verified design and analysis tools for Mission Engineering and the related design methodology for Atmospheric Flight have been used for this independent verification.

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In Categories: High-Speed Missions and Vehicles, HiSST 2018, Mission Design & Optimization, Operations and Environment, Space Mission Analysis
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