{"id":500,"date":"2016-07-04T16:19:18","date_gmt":"2016-07-04T14:19:18","guid":{"rendered":"https:\/\/people.unipi.it\/vittorio_cipolla\/?p=500"},"modified":"2021-11-25T16:25:02","modified_gmt":"2021-11-25T15:25:02","slug":"a-new-paper-published-in-aircraft-engineering-and-aerospace-technology-emerald-mission-architecture-for-mars-exploration-based-on-small-satellites-and-planetary-drones","status":"publish","type":"post","link":"https:\/\/people.unipi.it\/vittorio_cipolla\/a-new-paper-published-in-aircraft-engineering-and-aerospace-technology-emerald-mission-architecture-for-mars-exploration-based-on-small-satellites-and-planetary-drones\/","title":{"rendered":"A new paper published in Aircraft Engineering and Aerospace Technology (Emerald): “Mission architecture for Mars exploration based on small satellites and planetary drones”"},"content":{"rendered":"\r\n\r\n\r\n
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The purpose of this paper is to deal with the study of an innovative unmanned mission to Mars, which is aimed at acquiring a great amount of detailed data related to both Mars\u2019 atmosphere and surface. The Mars surface exploration is conceived by means of a fleet of drones flying among a set of reference points (acting also as entry capsules and charging stations) on the surface. The three key enabling technologies of the proposed mission are the use of small satellites (used in constellation with a minimum of three), the use of electric propulsion systems for the interplanetary transfer (to reduce the propellant mass fraction) and lightweight, efficient, drones designed to operate in the harsh Mars environment and with its tiny atmosphere. The low-thrust Earth-Mars transfer is designed by means of an optimization approach resulting in a duration of slightly more than 27 months with a propellant amount of about 125\u2009kg, which is compatible with the choice of considering a 500\u2009kg-class spacecraft. Four candidate drone configurations have been selected as the result of a sensitivity analysis. Flight endurance, weight and drone size have been considered as the driving design parameters for the selection of the final configuration, which is characterized by six rotors, a total mass of about 6.5\u2009kg and a flight endurance of 28 minutes. In the mission scenario proposed, the drone is assumed to be delivered on the Mars surface by means of a passive entry capsule, which acts also as a docking station and charging base. Such a capsule has been sized both in terms of mass (68\u2009kg) and power (80\u2009W), showing to be compatible with 500\u2009kg-class spacecraft. The concept would return incomparable scientific data and can be also be potentially implemented with a relatively low budget exploiting of the shelf components to the larger extent, small identical spacecraft buses and modular low-cost drones. The innovative mission architecture proposed in this study aims at providing a complete coverage of the surface and lowest atmospheric layers. The main innovation factor of the proposed mission consists in the adoption of small multi-copter UAVs, also called \u201cdrones,\u201d as remote-sensing platforms.<\/p>\r\n<\/section>\r\n<\/div>\r\n<\/section>\r\n<\/div>\r\n\r\n\r\n\r\n

Share and Cite<\/h4>\r\n\r\n\r\n\r\n\r\n\r\n

Pergola, P.<\/a> and Cipolla, V.<\/a> (2016), “Mission architecture for Mars exploration based on small satellites and planetary drones”, International Journal of Intelligent Unmanned Systems<\/a><\/i>, Vol. 4 No. 3, pp. 142-162<\/p>\r\n\r\n\r\n\r\n

Full-text here: https:\/\/doi.org\/10.1108\/IJIUS-12-2015-0014<\/a><\/p>\r\n","protected":false},"excerpt":{"rendered":"

The purpose of this paper is to deal with the study of an innovative unmanned mission to Mars, which is aimed at acquiring a great amount of detailed data related to both Mars\u2019 atmosphere and surface. 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