ELV: Pressure Fed LOX/LH2 Upper Stage
- Paper number
IAC-05-C4.1.05
- Author
Mr. Max Calabro, The Inner Arch, France
- Coauthor
Mr. Christophe Bonnal, Centre National d'Etudes Spatiales (CNES), France
- Year
2005
- Abstract
ExoMars is ESA’s next mission to planet Mars. The project is currently undergoing Phase B2 studies under ESA management. In that context, DEIMOS is responsible for the Mission Analysis support to Thales Alenia Space Italy as ExoMars Prime Contractor, covering all mission phases, including launch, interplanetary, Mars orbit injection and orbiting, down to entry, descent and landing (EDL).
The current baseline is based on an Ariane 5 launch in 2013 of a spacecraft Composite made up of a Carrier Module (CM) and a Descent Module (DM). A back-up option in 2016 is studied in parallel. The trajectory profile is characterised by: a) direct transfer to Mars with an intermediate deep space manoeuvre (DSM), b) insertion into a 4-sol Mars waiting orbit (WO) and c) Composite descent from orbit, initiated by the Carrier, which then separates and burns up in the Martian atmosphere, while the DM goes on to complete the descent and landing.
The objective of this paper is to present the current mission analysis and design of ExoMars from Launch to touchdown.
The proposed escape strategy from Earth and the required operations to escape from it has been the subject of a dedicated optimization process. The paper will also present the results of the interplanetary mission design and optimization in the different possible transfer cases to Mars.
The tight link between the arrival and the EDL phase via the WO has required an extension of the EDL phase up to the Mars Orbit Insertion (MOI) in such a way that an end-to-end, i.e. continuous, mission profile from MOI to touchdown is obtained. The orbit strategy prior to arrival to the Entry Interface Point is based on the reduction of the trajectory dispersions at EIP. The result is that the landing accuracy is below 25 km.
The Global Entry Corridor (GEC) method has been extensively applied to identify the sizing trajectories and to evaluate the feasibility of selected sites. Combined with Engineering Constraints and Scientific Requirements, It allows the identification of feasible landing sites.
Detailed end-to-end Monte Carlo analyses from de-orbit to touchdown have been run to evaluate the mission performances. Multibody simulations for the descent phase have been also run to verify the stability of the system and the sensitivity to perturbations (gust). These results serve not only as a verification of the mission design but also as a validation of the design methods and tools.
- Abstract document
- Manuscript document
IAC-05-C4.1.05.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.