Design and Testing of a Double-Sided Ion Thruster for Ion-Beam Shepherd

2020 ◽  
Vol 36 (2) ◽  
pp. 202-210 ◽  
Author(s):  
M. Dobkevicius ◽  
D. Feili ◽  
M. Smirnova ◽  
A. M. Perez
Keyword(s):  
Ion Beam ◽  
Ion Thruster ◽  
Design And Testing

A 3D particle model for the plume CEX simulation

2018 ◽  
Vol 122 (1255) ◽  
pp. 1425-1441 ◽  
Author(s):  
C. Lu ◽  
P. Qiu ◽  
Y. Cao ◽  
T.P. Zhang ◽  
J.J. Chen
Keyword(s):  
Monte Carlo ◽  
Analytical Model ◽  
Ion Beam ◽  
Direct Simulation Monte Carlo ◽  
Particle Model ◽  
Neutral Atoms ◽  
Ion Thruster ◽  
Technology Application ◽  
Particle In Cell ◽  
Ion Thrusters

ABSTRACTCharge Exchange (CEX) ion is the main factor causing the plume pollution. The distribution of CEX ions is determined by the distribution of beam ions and neutral atoms. Hence, the primary problem in the study of the plume is how to accurately simulate the distribution of beam ions and neutral atoms. At present, the most commonly used model utilised for the plume simulation is the analytical model proposed by Roy for the plume simulation of the NASA Solar Technology Application Readiness (NSTAR) ion thruster. However, this analytical model can only be applied to the ion beam with small divergence angles. In addition, the analytical model is no longer applicable to the simulation for the plume of a new type of ion thruster that appeared recently, which is called the annular ion thruster. In this paper, a 3D particle model is proposed for the plume simulation of ion thrusters consisting of the particle model for beam ions, the Direct Simulation Monte Carlo (DSMC) model for neutral atoms and the Immersed Finite Element-Particle In Cell-Monte Carlo Collision (IFE-PIC-MCC) model for CEX ions. Then, the plume of the NSTAR ion thruster is simulated by both Roy's model and the 3D particle model. The simulation results of both models are then compared with the experimental results. It is shown that the numerical results of the 3D particle model agree well with those of the analytical model and the experimental data. And this 3D particle model can also be used for other electric thrusters.

Design and testing of low-cost miniature ion thruster for nanosatellites

2015 ◽  
Vol 61 (1) ◽  
pp. 1-8
Author(s):  
C. A. Barry Stoute ◽  
Brendan M. Quine
Keyword(s):  
Low Cost ◽  
Ion Thruster ◽  
Design And Testing

Ion Beam Characterisation of the RIT 10 Ion Thruster

2003 ◽  
Author(s):  
Michael Zeuner ◽  
Frank Scholze ◽  
Michael Tartz ◽  
Horst Neumann ◽  
Hans Leiter ◽  
...  
Keyword(s):  
Ion Beam ◽  
Ion Thruster

Ion beam characteristics of a 14 cm xenon ion thruster

1994 ◽  
Author(s):  
Y. Hayakawa ◽  
K. Miyazaki ◽  
S. Kitamura
Keyword(s):  
Ion Beam ◽  
Ion Thruster ◽  
Beam Characteristics

Performance of a rf neutralizer operating with noble gases and iodine

2020 ◽  
Vol 91 (1) ◽  
pp. 10901 ◽  
Author(s):  
Patrick Dietz ◽  
Felix Becker ◽  
Konstantin Keil ◽  
Kristof Holste ◽  
Peter J. Klar
Keyword(s):  
Ion Beam ◽  
Experimental Studies ◽  
Space Mission ◽  
Inert Gases ◽  
Rf Discharge ◽  
Global Modeling ◽  
Ion Thruster ◽  
Hollow Cathodes ◽  
Inductively Coupled ◽  
Ion Thrusters

Neutralization of the extracted ion beam is a mandatory task for any ion thruster based space mission. The required lifetimes are in the order of ten thousand hours. This requirement is fulfilled by hollow cathodes operating with xenon, but has not been demonstrated for operation with iodine yet. Furthermore, the power consumption as well as the demand on mass flow should be kept as low as possible. Since the halogen iodine seems to be a viable alternative to xenon for operating ion thrusters, a suitable neutralizer concept that can operate with the corrosive gas for the time periods stated above is required. We propose to use a neutralizer based on an inductively coupled rf discharge as alternative to hollow cathodes. We studied the performance of a prototypical neutralizer operating with iodine as well as the inert gases xenon and krypton and compared the experimental studies with the results of global modeling.

Ion beam plume and efflux measurements of an 8-cm mercury ion thruster

1978 ◽  
Author(s):  
G. KOMATSU ◽  
J. SELLEN, JR. ◽  
S. ZAFRAN
Keyword(s):  
Ion Beam ◽  
Mercury Ion ◽  
Ion Thruster
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