Orpheus Project: a study proposal for a Mars ISRU plant.
- Paper number
IAC-05-E2.3.04
- Author
Mr. Gabriele Bellei, Politecnico di Milano, Italy
- Coauthor
Dr. Andrea Davighi, Politecnico di Milano, Italy
- Coauthor
Dr. Elvina Finzi, Politecnico di Milano, Italy
- Coauthor
Mr. Massimiliano Vasile, Politecnico di Milano, Italy
- Coauthor
Mr. Stefano Cattaneo, Politecnico di Milano, Italy
- Coauthor
Mr. Massimiliano Politi, Politecnico di Milano, Italy
- Coauthor
Ms. Luisa Vizzi, Politecnico di Milano, Italy
- Year
2005
- Abstract
Space exploration has always been drastically constrained by the masses that can be launched into orbit: in particular whenever it is required to return a sample from another planet or in case of human missions, extra propellant has to be provided in order to perform the return itself: the larger the mass which is expected to come back, the bigger the amount of propellant. The growing interest for Mars exploration and its eventual manned colonization impose to test new technologies and try different approaches to the problem. A possible solution is to install an "In Situ Resource Utilization" platform on the surface of Mars, which is able to produce the propellant needed to carry the payload back to Earth using the resources available in the Martian environment. A Mars ISRU mission is also planned in the Aurora Programme, the European program for the exploration of the solar system. Orpheus Project is a technological demonstrator whose purpose is to show the advantages of an In Situ Propellant Production (ISPP) instead of carrying all the extra propellant from Earth. The main requirement of the mission is that the mass of the propellant produced "In Situ" must be higher than the one of the ISPP plant. Two different scenarios have been investigated considering different masses of the payload to be carried back: 1- A Small Size Mission (SSM), more feasible and with more conservative solutions, with a contained launch mass. 2- A Large size Mission (LSM), that features more advanced solutions, has been sized to show that is possible to produce enough propellant to launch an eventual manned module from a future Martian base. Once that the propellant production is completed, both scenarios require that the payload will be sent to the Earth-return trajectory with a Mars Ascent Vehicle (MAV). Here are briefly reported the results of the design process: the SSM is a technological demonstrator able to bring back to Earth 3 kg of mass with the propellant (ethylene/oxigen) produced "in situ". The total ISPP plant mass is about 300 kg, while the total amount of propellant produced is 850 kg: therefore the main constraint to the mission design is satisfied. A single module (about 1950 kg) is put directly into the desired escape hyperbola by the Ariane 5 cryogenic upper-stage ECB. After a 214 days of interplanetary transfer, the module directly enters the Martian atmosphere, where combined systems of inflatable aero shell, parachutes and retro-rockets will perform a soft-landing, necessary because of the fragility of the payload. The LSM is a more futuristic mission that can provide propellant to return about 2250 kg of payload. Due to the higher masses and dimensions involved, two launches are necessary: a first module brings the ISPP power plant, a nuclear reactor, to Mars. The second one has to carry the actual ISPP plant, for a total payload mass of 6600 kg. Both modules are put into the escape orbit with the cryogenic upper-stage of the launcher and the cruising phase should take about 200 days for each module. Small DV propelled manoeuvres permit the insertion into a Martian eccentric orbit, then an aero-braking phase permits to lower the energy level for the subsequent entry phase. A soft landing is required, therefore both modules are equipped with parachutes and retro-rockets and an additional radio-guidance system that is necessary to obtain a precise landing. Once on the Martian surface, a rover connects the ISPP to the power source. During its operational life the LSM produces 35000 kg of propellant satisfying the requirements of the mission.
- Abstract document
- Manuscript document
IAC-05-E2.3.04.pdf (🔒 authorized access only).
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