Single launch, direct Earth return MSR mission
- Paper number
IAC-07-D2.7.06
- Author
Dr. Dominique Valentian, Snecma, France
- Coauthor
Michel Muszynski, Snecma, France
- Year
2007
- Abstract
The standard Mars Sample Return mission profile implies two launches (one orbiter and one lander) and a rendezvous in Mars orbit before returning the sample to Earth. This paper explores the possibility to combine an improved cryogenic upper stage of ARIANE 5 using VINCI engine, an orbital propulsion module using cryogenic propellants, associated with active refrigeration for interplanetary cruise or a combination of electric propulsion provided by Hall effect Thrusters (PPS 5000) with chemical propulsion, either cryogenic or earth storable bipropellant. The mass provided by these combinations is sufficient to land several tons on Mars surface. This enables a large increase of the lander mass. It is therefore possible to return the samples directly to Earth without Mars orbit rendezvous (required Delta V ~ 6 km/s) The Mars ascent vehicle may use a semi cryogenic combination with simplified active refrigeration requirements and high density.. This option may offer additional freedom in the landing site selection. The payload gain comes from three factors: Ø The direct payload gain from VINCI engine and its re-starting capability for interplanetary missions. Ø The use of electric propulsion where it is the most efficient: for orbit transfer around a celestial body (e.g. from “GTO like” to highly elliptical orbit) instead of being used during interplanetary flight. Ø The use of chemical propulsion where it is the most effective: for impulsive injection into interplanetary orbit by firing at perigee (conversely by firing the chemical engine on an hyperbolic trajectory to insure planetary capture). A typical mission profile would imply an injection on a GTO like orbit (payload 12 tons or more). An electric propulsion transfer to an highly elliptical orbit, a chemical firing to insure the injection into interplanetary trajectory, a chemical propulsion firing to insure Mars capture on a highly elliptical trajectory and last a circularisation around Mars using electric propulsion, enabling the select any landing site. The mission is also possible with a cryogenic propulsion module from Earth orbit to Mars orbit.
- Abstract document
- Manuscript document
IAC-07-D2.7.06.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.