Magnetic Enhanced Plasma Propulsion System for small-satellites IOD development

Paper number

IAC-18,C4,8-B4.5A,2,x45774

Author

Dr. Marco Manente, Italy

Coauthor

Dr. Fabio Trezzolani, Italy

Coauthor

Dr. Nicolas Bellomo, Italy, T4i

Coauthor

Dr. Mirko Magarotto, Italy, University of Padova - DII/CISAS

Coauthor

Dr. Elena Toson, Italy, T4i

Coauthor

Mr. Riccardo Mantellato, Italy, CISAS – “G. Colombo” Center of Studies and Activities for Space, University of Padova

Coauthor

Dr. Francesco Barato, Italy, University of Padova - DII/CISAS

Coauthor

Prof. Daniele Pavarin, Italy, CISAS – “G. Colombo” Center of Studies and Activities for Space, University of Padova

Year

2018

Abstract

Miniaturized satellites have become increasingly common in recent years. In order to enable different mission scenarios, satellite platforms as small as CubeSats (U-class spacecraft) require versatile, low-cost, compact and reliable propulsion systems.

The Magnetic Enhanced Plasma (MEP) technology is a good candidate as propulsion system for small satellites. In fact, its main features are: (i) a simple architecture consisting in a discharge chamber, an antenna and a magnetic field generator, (ii) no need for neutralizer and grids, (iii) no need for the PPU to provide high voltage DC output. Thanks to these peculiarities the MEP propulsion system is characterized by a long lifetime and a low cost. In particular, it can work with different propellants (such as Ar, Kr, Xe, Air, CO$_2$) without significant modifications to the system geometry. Because of this last feature it seems extremely promising to investigate the employment of Iodine as propellant, which is particularly appealing for space applications thanks to its capability of being stored in the solid state, thus resulting in a huge reduction of the storage volume. Vice-versa, for a fixed amount of storage volume the employment of Iodine, rather than Xenon, can lead to an increase of the stored propellant mass of 4-5 times. Therefore the Iodine propellant could enable new concepts of space missions in particular in the small-satellites and CubeSat segment.

T4i, the Spin-Off of the University of Padova founded by its Space Propulsion group, is currently developing REGULUS, a compact propulsion system based on a MEP technology, satisfying CubeSat standard requirements; the REGULUS system has been successfully operated with Xe propellant. REGULUS will be fully operational at the beginning of 2019 when an In Orbit Demonstration (IOD) has been planned. In this work we will describe: (i) the design of REGULUS operated with Iodine, (ii) the fluidic line, sensors, and security procedures employed in the ground test, (iii) the design of a Iodine fluidic line for CubeSat space applications, (iv) new mission scenarios which the use of Iodine propellant will enable.

Abstract document

IAC-18,C4,8-B4.5A,2,x45774.brief.pdf

Manuscript document

IAC-18,C4,8-B4.5A,2,x45774.pdf (🔒 authorized access only).

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