SYSTEM ANALYSIS AND TEST-BED FOR AN ATMOSPHERE-BREATHING ELECTRIC PROPULSION SYSTEM USING AN INDUCTIVE PLASMA THRUSTER
- Paper number
IAC-17,C4,6,5,x41810
- Author
Mr. Francesco Romano, Institute of Space Systems, Universität Stuttgart, Germany
- Coauthor
Mr. Tilman Binder, University of Stuttgart, Germany
- Coauthor
Dr. Georg H. Herdrich, University of Stuttgart, Germany
- Coauthor
Dr. Peter C.E Roberts, The University of Manchester, United Kingdom
- Coauthor
Dr. Silvia Rodriguez-Donaire, UPC-BarcelonaTECH, Spain
- Coauthor
Dr. Daniel Garcia-Almiñana, UPC-BarcelonaTECH, Spain
- Coauthor
Dr. Nicholas H. Crisp, The University of Manchester, United Kingdom
- Coauthor
Dr. Steve Edmondson, The University of Manchester, United Kingdom
- Coauthor
Dr. Sarah Haigh, The University of Manchester, United Kingdom
- Coauthor
Mrs. Rachel Lyons, United Kingdom
- Coauthor
Dr. Vitor Oiko, The University of Manchester, United Kingdom
- Coauthor
Dr. Katharine Smith, University of Manchester, United Kingdom
- Coauthor
Dr. Jonathan Becedas, Elecnor Deimos Satellite Systems, Spain
- Coauthor
Mr. Gerardo González, Elecnor Deimos Satellite Systems, Spain
- Coauthor
Ms. Irene Vázquez, Elecnor Deimos Satellite Systems, Spain
- Coauthor
Mr. Álvaro Braña, Elecnor Deimos Satellite Systems, Spain
- Coauthor
Ms. Kelly Antonini, GomSpace ApS, Denmark
- Coauthor
Mr. Kristian Bay, GomSpace ApS, Denmark
- Coauthor
Mr. Leonardo Ghizoni, GomSpace ApS, Denmark
- Coauthor
Mr. Victor Jungnell, GomSpace ApS, Denmark
- Coauthor
Dr. Jonas Morsbøl, GomSpace ApS, Denmark
- Coauthor
Mr. Adam Boxberger, IRS, University of Stuttgart, Germany
- Coauthor
Prof. Stefanos Fasoulas, University of Stuttgart, Germany
- Coauthor
Mrs. Dhiren Kataria, Mullard Space Science Laboratory, United Kingdom
- Coauthor
Dr. Mark Davidson, The Tech Toybox, United States
- Coauthor
Prof. Ron Outlaw, United States
- Coauthor
Ms. Badia Belkouchi, Euroconsult, France
- Coauthor
Mr. Alexis Conte, Euroconsult, France
- Coauthor
Mr. Perez Jose Santiago, France
- Coauthor
Mrs. Rachel Villain, Euroconsult, France
- Coauthor
Ms. Barbara Heißerer, concentris research management gmbh, Germany
- Coauthor
Ms. Ameli Schwalber, concentris research management gmbh, Germany
- Year
2017
- Abstract
Challenging space mission scenarios include those in low altitude orbits, where the atmosphere creates significant drag to the S/C and forces their orbit to an early decay. For drag compensation, propulsion sys- tems are needed, requiring propellant to be carried on-board. An atmosphere-breathing electric propulsion system (ABEP) ingests the residual atmosphere’s particles through an intake and uses them as propellant for an electric thruster. Theoretically applicable to any planet with atmosphere, the system might allow to orbit for unlimited time without carrying propellant. A new range of altitudes for continuous operation would become accessible, enabling new scientific missions while reducing costs. Preliminary studies have shown that the collectible propellant flow for an ion thruster (in LEO) might not be enough, and that electrode erosion due to aggressive gases, such as atomic oxygen, will limit the thruster’s lifetime. In this paper we introduce the use of an inductive plasma thruster (IPT) as thruster for the ABEP system. IPT is based on a small scale inductively heated plasma generator IPG6-S. These devices have the advantage of being electrodeless, and have already shown high electric-to-thermal coupling efficiencies using O2 and CO2 as propellant. A water cooled nozzle has been developed and applied to IPG6-S. The system analysis is integrated with IPG6-S equipped with the nozzle for testing to assess mean mass-specific energies of the plasma plume and estimate exhaust velocities.
- Abstract document
- Manuscript document
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