Design optimisation and mass saving of the structure of the ORION-MPCV European Service Module
- Paper number
IAC-18,C2,1,11,x48504
- Author
Mr. Gandolfo Di Vita, The Netherlands, European Space Agency (ESA)
- Coauthor
Mr. Goncalo Rodrigues, The Netherlands, European Space Agency (ESA)
- Coauthor
Mr. Guillaume Dussardier, France, ArianeGroup SAS
- Coauthor
Mr. Antoine Alouani, Germany, ArianeGroup
- Coauthor
Mr. Stefano Scalisi, Italy, Thales Alenia Space Italia (TAS-I)
- Coauthor
Mr. Moreno Faraud, Italy, Thales Alenia Space Italia (TAS-I)
- Coauthor
Mr. Ghosn Louis J., United States, NASA Glenn Research Center
- Coauthor
Ms. Sofia Caeiro, The Netherlands, ESA - European Space Agency
- Coauthor
Mrs. Tiziana Cardone, The Netherlands, ESA - European Space Agency
- Coauthor
Mr. Andrea Amaldi, The Netherlands, ESA - European Space Agency
- Coauthor
Mr. Ryan Proud, United States, NASA
- Coauthor
Mr. Paolo Palmieri, Italy, Thales Alenia Space Italia (TAS-I)
- Coauthor
Mr. Gerben Sinnema, The Netherlands, European Space Agency (ESA-ESTEC)
- Year
2018
- Abstract
This paper presents an overview of all the design optimisation measures that have been proposed, analysed and implemented in order to reduce the mass of the structure, including the MMOD (Micro-Meteoroid and Orbital Debris) protection system, of the ESM (European Service Module) for the “Orion” MPCV (Multi-Purpose Crew Vehicle). Under an agreement between NASA and ESA, the new NASA Multi-Purpose Crew Vehicle (MPCV) for human space exploration missions will be powered by an European Service Module (ESM), based on the design and experience of the ATV (Automated Transfer Vehicle). The development and qualification of the European Service Module (ESM) is managed and implemented by ESA. The ESM prime contractor and system design responsible is Airbus Defence and Space, while Thales Alenia Space Italia is responsible for the design and integration of the ESM Structure and Micro-Meteoroids and Orbital Debris (MMOD) protection system, in addition to the Thermal Control System and the Consumable Storage System. The Orion Multi-Purpose Crew Vehicle (MPCV) is a pressurized, crewed capsule that transports up to four crew members from the Earth’s surface to a nearby destination or staging point, and brings the crew members safely back to the Earth’s surface at the end of the mission. The MPCV provides all services necessary to support the crew members while on-board for short duration missions (up to 21 days) or until they are transferred to another element. The European Service Module supports the crew module from launch through separation prior to re-entry. It provides in-space propulsion capability for orbital transfer, attitude control, and high altitude ascent aborts. It provides the water and oxygen needed for a habitable environment, generates and stores electrical power, and maintains the temperature of the vehicle's systems and components. The ESM has been designed and qualified for the first 2 Orion MPCV missions to the Moon orbit, EM-1 (Exploration mission 1), unmanned flight planned at the end of 2019 and EM-2 (Exploration Mission 2), manned flight planned in 2022 or 2023. The mass saving of the Service Module, object of this paper, has been considered necessary, together with other improvements like the introduction of the parallel tanks propellant depletion, to consolidate the ESM design and make possible future different missions beyond EM-1 and EM-2. The mass saving study has introduced new optimized structural concepts, optimization of the MMOD protection shields, optimized redesign of parts for manufacturing through 3D printing technologies. Keywords: Orion-MPCV, Structure, Mass-saving
- Abstract document
- Manuscript document
IAC-18,C2,1,11,x48504.pdf (🔒 authorized access only).
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