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Initial study on non-catastrophic damage risk for all-electric satellite transferring to GEO

: Higashide, M.; Schimmerohn, M.; Schäfer, F.

International Astronautical Federation:
Unlocking imagination, fostering innovation and strengthening security. Vol.1 : 68th International Astronautical Congress (IAC 2017); Adelaide, Australia 25-29 September 2017
Red Hook/NY: Curran Associates, 2018
ISBN: 978-1-5108-5537-3
International Astronautical Congress (IAC) <68, 2017, Adelaide>
Fraunhofer EMI ()

To increase the dry weight of a geostationary earth orbit (GEO) satellite, electric propulsion technique is focused on. Since thrust force of an electric propulsion thruster is smaller than a chemical propulsion, orbit transfer duration becomes several months when electric propulsion is used for a transfer to GEO. The purpose of this study is to assess non-catastrophic damage risk of satellite transferred from geostationary transfer orbit to GEO with only electronic propulsion thrusters. The risk analysis was performed with the particle impact risk and vulnerability assessment tool. The satellite 3D model was developed based on the Boeing 702SP bus which used as the Eutelsat 115 West B and ABS-3A. As a result, particle perforation frequency of the internal components was lower than 0.001 during orbit transfer.