Exomars Mission Design And Analysis From Launch To Landing

Paper number

IAC-07-A5.I.-A3.I.B.11

Author

Mr. Rodrigo Haya Ramos, DEIMOS Space S.L., Spain

Coauthor

Francesco Cacciatore, DEIMOS Space S.L., Spain

Coauthor

David Gittins, United Kingdom

Coauthor

David Riley, United Kingdom

Coauthor

Mr. Juan L. Cano, DEIMOS Space S.L., Spain

Coauthor

Mr. David Northey, United Kingdom

Coauthor

Mr. Davide Bonetti, DEIMOS Space S.L., Spain

Year

2007

Abstract

ExoMars is ESA’s current mission to planet Mars. The probe is aimed for launch between 2013 and 2015. The project is currently undergoing Phase B studies under ESA management and Alcatel Alenia Space project leadership. In that context, DEIMOS Space is responsible for the Mission Analysis and Design for the interplanetary and the Entry, Descent and Landing (EDL) phases.
The current mission baseline is based on a Soyuz-Fregat launch from Kourou in 2013 (2015 as backup) of a spacecraft Composite bearing a Carrier and a Descent Module (DM). 
The trajectory profile is characterized by the need to send the highest possible mass to Mars, fact that conditions the design in two main ways: a) the need to launch into a highly elliptic orbit (HEO) and escape in a sequence of apogee raising maneuvers and b) perform a delayed transfer to Mars. 
In addition, a number of options are also analyzed in terms of a possible Mars Orbiter, either launched alone by a Soyuz launcher or by an Ariane 5 carrying the spacecraft composite. 
The paper will expose in detail the proposed escape strategy from Earth and the required operations to escape from it, which have 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 envisaged EDL concept will be based on the following sequence: after separation, the DM enters the atmosphere and deploys a two-stage parachute system. Vertical solid or liquid retrorockets are ignited to perform the final breaking. The landing is based on airbags (vented or non-vented).
The design of the EDL phases is driven by the flexibility in terms of landing site, arrival dates and a landing accuracy. Innovative approaches in terms of worst-case philosophy have been designed in order to cope with that variability and to provide a global picture of the mission capabilities in terms of landing site reachability. The concept of the entry corridors has been extended to a planetary level (Global Entry Corridor) for identification of realistic worst cases with direct mapping of landing site location with mission performance. 
The design of the D\&L phases is driven by the mass of the Lander, the limited overall mass budget, the safe separation of the frontshield and the mass margins philosophy. Parametric sizing of the DLS components has been applied to support system activities.

Abstract document

IAC-07-A5.I.-A3.I.B.11.pdf

Manuscript document

IAC-07-A5.I.-A3.I.B.11.pdf (🔒 authorized access only).

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