Activities in Electric Propulsion Development at IRS

Herdrich, Georg; Bauder, Uwe; Bock, Dagmar; Eichhorn, Christoph; Haag, Daniel; Lau, Matthias; Schönherr, Tony; Stindl, T.; Fertig, Markus; Löhle, Stefan; Auweter‐Kurtz, Monika; Röser, Hans‐Peter

doi:10.2322/tstj.7.tb_5

Cited by 4 publications

(2 citation statements)

References 26 publications

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“…248 Other PIC based packages such as oIOM are developed to investigate HEMP based ion thrusters. [249][250][251] Furthermore, a multiscale modeling of thruster-plumes using a 3D PIC method was developed [252][253][254] and the plume simulation using modern graphics processing unit (GPU) computing has been discussed. 255 More recently, additional extensive tools such as Smilei and PICLas have been introduced to simulate the plasma with multiple ion species along with neutral gas distribution.…”

Section: Modelingmentioning

confidence: 99%

Ion thrusters for electric propulsion: Scientific issues developing a niche technology into a game changer

Holste

Dietz

Scharmann

et al. 2020

Review of Scientific Instruments

138

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The transition from OLD SPACE to NEW SPACE along with increasing commercialization has a major impact on space flight, in general, and on electric propulsion (EP) by ion thrusters, in particular. Ion thrusters are nowadays used as primary propulsion systems in space. This article describes how these changes related to NEW SPACE affect various aspects that are important for the development of EP systems. Starting with a historical overview of the development of space flight and of the technology of EP systems, a number of important missions with EP and the underlying technologies are presented. The focus of our discussion is the technology of the radio frequency ion thruster as a prominent member of the gridded ion engine family. Based on this discussion, we give an overview of important research topics such as the search for alternative propellants, the development of reliable neutralizer concepts based on novel insert materials, as well as promising neutralizer-free propulsion concepts. In addition, aspects of thruster modeling and requirements for test facilities are discussed. Furthermore, we address aspects of space electronics with regard to the development of highly efficient electronic components as well as aspects of electromagnetic compatibility and radiation hardness. This article concludes with a presentation of the interaction of EP systems with the spacecraft.

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Section: Modelingmentioning

confidence: 99%

Ion thrusters for electric propulsion: Scientific issues developing a niche technology into a game changer

Holste

Dietz

Scharmann

et al. 2020

Review of Scientific Instruments

138

View full text Add to dashboard Cite

show abstract

“…Among them are steady state self-field and applied field magnetoplasmadynamic (MPD) sources, thermal arcjet devices, IPG and hybrid plasma systems [3], [4], [5]. These plasma systems are in application for aerothermodynamic testing, heat shield material characterization [6], [7], [8], [9], [10], [11], electric space propulsion [12], [13], [14], [15], [16], [17], [18] and terrestrial plasma technology (i.e. technology transfer) [19], [20], [21].…”

Section: Introductionmentioning

confidence: 99%

System analysis and test-bed for an atmosphere-breathing electric propulsion system using an inductive plasma thruster

et al. 2018

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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 systems are needed, requiring propellant to be carried on-board. An atmosphere-breathing electric propulsion system (ABEP) ingests the residual atmosphere 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 lifetime. In this paper an inductive plasma thruster (IPT) is considered for the ABEP system. The starting point is a small scale inductively heated plasma generator IPG6-S. These devices are electrodeless and have already shown high electric-to-thermal coupling efficiencies using O 2 and CO 2 . The system analysis is integrated with IPG6-S tests to assess mean mass-specific energies of the plasma plume and estimate exhaust velocities.

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Advanced scaling model for simplified thrust and power scaling of an applied-field magnetoplasmadynamic thruster

Herdrich¹,

Boxberger²,

Petkow³

et al. 2010

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Activities in Electric Propulsion Development at IRS

Cited by 4 publications

References 26 publications

Ion thrusters for electric propulsion: Scientific issues developing a niche technology into a game changer

Ion thrusters for electric propulsion: Scientific issues developing a niche technology into a game changer

System analysis and test-bed for an atmosphere-breathing electric propulsion system using an inductive plasma thruster

Advanced scaling model for simplified thrust and power scaling of an applied-field magnetoplasmadynamic thruster

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