Inductive Plasma Thruster: design, set-up, and first ignition.
- Paper number
IAC-20,C4,5,11,x58032
- Author
Mr. Francesco Romano, Germany, Institute of Space Systems, University of Stuttgart
- Coauthor
Dr. Georg H. Herdrich, Germany, University of Stuttgart
- Coauthor
Mr. Yung-An Chan, Germany, Institute of Space Systems, Universität Stuttgart
- Coauthor
Dr. Peter C.E. Roberts, United Kingdom, The University of Manchester
- Coauthor
Mr. Constantin Traub, Germany, Institute of Space Systems, University of Stuttgart
- Coauthor
Prof. Stefanos Fasoulas, Germany, University of Stuttgart
- Coauthor
Dr. Nicholas H. Crisp, United Kingdom, The University of Manchester
- Coauthor
Dr. Steve Edmondson, United Kingdom, The University of Manchester
- Coauthor
Dr. Sarah Haigh, United Kingdom, The University of Manchester
- Coauthor
Mr. Brandon A. Holmes, United Kingdom, The University of Manchester
- Coauthor
Ms. Sabrina Livadiotti, United Kingdom, The University of Manchester
- Coauthor
Mr. Alejandro Macario Rojas, United Kingdom, The University of Manchester
- Coauthor
Dr. Vitor Toshiyuki Abrao Oiko, United Kingdom, The University of Manchester
- Coauthor
Dr. Katharine Smith, United Kingdom, University of Manchester
- Coauthor
Ms. Luciana Sinpetru, United Kingdom, The University of Manchester
- Coauthor
Dr. Jonathan Becedas Rodríguez, Spain, Elecnor Deimos
- Coauthor
Ms. Rosa María Domínguez, Spain, Elecnor Deimos Satellite Systems
- Coauthor
Ms. Valeria Sulliotti-Linner, Spain, Elecnor Deimos Satellite Systems
- Coauthor
Mr. Simon Christensen, Denmark, GomSpace Aps
- Coauthor
Mr. Thomas Kauffman Jensen, Denmark, GomSpace Aps
- Coauthor
Mr. Jens Nielsen, Denmark, GomSpace Aps
- Coauthor
Dr. Morten Bisgaard, Denmark, GomSpace ApS
- Coauthor
Dr. Daniel Garcia-Almiñana, Spain, UPC-BarcelonaTECH
- Coauthor
Dr. Silvia Rodriguez-Donaire, Spain, UPC-BarcelonaTECH
- Coauthor
Dr. Miquel Sureda, Spain, Universitat Politecnica de Catalunya (UPC BarcelonaTech)
- Coauthor
Ms. Marina García-Berenguer, Spain, UPC-BarcelonaTECH
- Coauthor
Dr. Dhiren Kataria, United Kingdom, University College London (UCL)
- Coauthor
Mrs. Rachel Villain, France, Euroconsult
- Coauthor
Mr. Simon Seminari, France, Euroconsult
- Coauthor
Mr. Alexis Conte, France, Euroconsult
- Coauthor
Ms. Badia Belkouchi, France, Euroconsult
- Year
2020
- Abstract
The IRS inductive plasma thruster (IRS IPT) is designed within the framework of the H2020 EU-funded DISCOVERER project. The IPT is an RF, contact-less thruster based on helicon-wave plasma discharge using a birdcage antenna. The contact-less characteristic of the thruster removes any issues regarding potential electrode erosion due to aggressive gases (see RIT, HET), such as atomic oxygen highly present in Earth orbit, extends propellant flexibility and can easily cope with variations of propellant flow and composition. This paper deals with the design, set-up, and first ignition of the inductive plasma thruster (IPT). Such thruster makes use of a birdcage antenna tuned at resonance to the frequency of the RF generator of f=40.68 MHz. Birdcage antennas are commonly used in magnetic resonance imaging (MRI) machines in the medical sector and only recently applied for plasma purposes. The birdcage antenna at resonance is a partially matched load for the RF circuit and, at the chosen resonance mode, provides linearly polarized electromagnetic fields that lead to an exhaust velocity for both ions and electrons along the same axial direction, enabling an efficient use of the power combined with a neutral plasma exhaust that removes the need of a neutralizer. The IPT is a laboratory model with an external electromagnet for variable static magnetic field application. The IPT design procedure supported by software simulations, its implementation and the first ignition tests will be presented with an early evaluation of the plasma discharge based on power, mass flow, and propellant.
- Abstract document
- Manuscript document
IAC-20,C4,5,11,x58032.pdf (🔒 authorized access only).
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