Simulation of flows within an electrostatic ion thruster for space missions

2001 ◽  
Vol 105 (1053) ◽  
pp. 613-618 ◽  
Author(s):  
M. Jugroot ◽  
J. K. Harvey
Keyword(s):  
Specific Impulse ◽  
Evaluation Research ◽  
Charged Particles ◽  
Space Missions ◽  
Solar Panels ◽  
Ion Thruster ◽  
Ion Thrusters ◽  
Particle Simulations ◽  
Complex Phenomena ◽  
Physical Phenomena

Abstract Ion thrusters are well suited for near-Earth and deep space missions because of their exceptionally high specific impulse. Those already flying are also proving to be very reliable. The flow of neutral and charged particles within the different components of these devices is very complex and although they have been studied for several years, little of the detail of their internal operation is properly understood. Numerical simulations of these flows can potentially yield an improved understanding of the physical phenomena involved and in turn this should assist in the optimising of new designs and in achieving higher specific impulses. The external plume, which can potentially cause damage to other spacecraft components such as solar panels, has been the object of some studies but the flow within the internal chambers where many complex phenomena are suspected to occur has been seriously neglected. For this reason the present fully kinetic neutral and charged particle simulations, which take account of the ionisation processes and the applied magnetic field, have been conducted. The studies have been made on one specific electrostatic ion thruster - the T5 model produced by the Space Department at the Defence and Evaluation Research Agency (DERA, Farnborough, UK). Two regions within the thruster have been concentrated on, namely the exit area of the hollow cathode and the main chamber.

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.

A Microscopic Study of Before-Arc Process in Metal Vapor Plasmas Proximal Cathode Region. Part I Formation of the Proximal Cathode Region

2013 ◽  
Vol 325-326 ◽  
pp. 1339-1342
Author(s):  
Jing Li ◽  
Qiu Ting Yu ◽  
Yun Dong Cao ◽  
Xiao Ming Liu ◽  
Chong Xu
Keyword(s):  
Theoretical Study ◽  
Charged Particles ◽  
Metal Vapor ◽  
Particle Energy ◽  
Cathode Region ◽  
Plasma Sheath ◽  
Vacuum Arc ◽  
Anode Surface ◽  
Necessary Condition ◽  
Complex Phenomena

Metal vapor arc in vacuum breaker is a very complex phenomena and the researches on the process of arc creating are the effective method to improve breaking ability. By the theoretical study and numerical simulation, exploring the formation of plasma sheath near the cathode, charged particles energy distribution and influence elements in before-arc process are the fundamentals of this paper. Before-arc process is the fundermental of arc energy and the proximal cathode region is the important area for vacuum arc forming, so before-arc process of metal vapor arc was simulated here. The modification to electron motion produced by the interaction between charged particles and plane electrodes and both elastic and charge exchange collisions between electrons and neutral gases were considered here. The copper cross section adopted here was related to the particle energy. The tracks of electrons were traced until they reached to the anode surface. Based on this method, the formation of proximal cathode region and some microscopic parameters were simulated here. The results show that the collision between charged particles with the electrodes is the necessary condition in proximal cathode regions formation.

scholarly journals Particle Simulations of the Effects of Atomic Oxygen on Ion Thruster Plumes

2018 ◽  
Vol 55 (5) ◽  
pp. 1154-1165 ◽  
Author(s):  
Ozgur Tumuklu ◽  
Deborah A. Levin
Keyword(s):  
Atomic Oxygen ◽  
Ion Thruster ◽  
Particle Simulations

Vortex Effect, Vortex Power

2018 ◽  
pp. 500-533
Author(s):  
Serebryakov Rudolf ◽  
Vladimir Vasilyevich Biryuk ◽  
Vyacheslav Volov
Keyword(s):  
Renewable Energy ◽  
Pressure Gradient ◽  
Thermal Energy ◽  
Nonlinear Effects ◽  
Continuous Media ◽  
Swirling Flows ◽  
Secondary Flows ◽  
Vortex Effect ◽  
Complex Phenomena ◽  
Physical Phenomena

One of the non-traditional types of renewable energy is vortex energy, which arises when swirling flows of continuous media (e.g., liquid and gas) are formed and which can be converted into thermal energy, work, and also used to raise the temperature in some systems or to create a pressure gradient. Vortex structures are systematically found in many physical processes. In recent years, new aspects of studying the vortex have been considered. These aspects are associated with physical phenomena, which indicate the occurrence of nonlinear effects in liquid media. Vortex flows of continuous media are one of the most important and complex phenomena in the mechanics of liquids and gases. They are characterized by specific manifestations that are fundamentally different from the axial properties of the motion of the medium, such as the appearance of secondary flows.

scholarly journals Hollow Cathode and Low-Thrust Extraction Grid Analysis for a Miniature Ion Thruster

2008 ◽  
Vol 2008 ◽  
pp. 1-11 ◽  
Author(s):  
Richard Wirz ◽  
Regina Sullivan ◽  
JoHanna Przybylowski ◽  
Mike Silva
Keyword(s):  
Hollow Cathode ◽  
High Efficiency ◽  
Low Thrust ◽  
Discharge Performance ◽  
Ion Thruster ◽  
Ion Extraction ◽  
Ion Thrusters ◽  
Future Space ◽  
Thrust Characteristics ◽  
Computational Analyses

Miniature ion thrusters are well suited for future space missions that require high efficiency, precision thrust, and low contamination in the mN to sub-mN range. JPL's miniature xenon Ion (MiXI) thruster has demonstrated an efficient discharge and ion extraction grid assembly using filament cathodes and the internal conduction (IC) cathode. JPL is currently preparing to incorporate a miniature hollow cathode for the MiXI discharge. Computational analyses anticipate that an axially upstream hollow cathode location provides the most favorable performance and beam profile; however, the hot surfaces of the hollow cathode must be sufficiently downstream to avoid demagnetization of the cathode magnet at the back of the chamber, which can significantly reduce discharge performance. MiXI's ion extraction grids are designed to provide >3 mN of thrust; however, previous to this effort, the low-thrust characteristics had not been investigated. Experimental results obtained with the MiXI-II thruster (a near replica or the original MiXI thruster) show that sparse average discharge plasma densities of ∼5×1015–5×1016 m-3 allow the use of very low beamlet focusing extraction voltages of only ∼250–500 V, thus providing thrust levels as low as 0.03 mN for focused beamlet conditions. Consequently, the thrust range thus far demonstrated by MiXI in this and other tests is 0.03–1.54 mN.

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