 Research article
 Open Access
 Published:
Global models for radiofrequency ion thrusters
EPJ Techniques and Instrumentation volume 8, Article number: 10 (2021)
Abstract
The emerging “new space” age strengthens the importance of rapid development and qualification procedures of electric engines and their peripheral devices. A key element is the reliable simulation of the thrusters and their supply units on short time scales. Global models seem to be well suited for this purpose. In this article, three variants of global models are presented and validated by comparison with experimental results. All models show excellent agreement with experiment, illustrating the strength of this modeling approach. Future developments of radiofrequency ion thrusters can be significantly accelerated with the help of these global models.
Introduction
As of 2021, electric spacecraft propulsion (EP) has become an essential part of modern spaceflight. It enables highly massefficient and, hence, economically beneficial missions with prolonged durability in contrast to conventional chemical propulsion. Two prominent applications come to mind for which EP had caused a disrupting influence: geostationary/geosynchronous station keeping (GSK) and electric orbit raising (EOR) of telecommunication satellites [1]. Typically, small chemical orbital propulsion devices such as cold gas or monopropellant thrusters had been used to compensate for ecliptic effects and solar winds during GSK missions, which led to a high wettodrymass ratio of the satellites due to low specific impulse I_{sp} of said propulsion devices. Additionally, to bring the geostationary telecommunication satellites (geosats) into their orbits of operation, the launcher would take the satellites directly to a geostationary elliptical transfer orbit (GTO). Typically, chemical mono or bipropellant thrusters had been used to initiate a kickburn at the apogee to ultimately bring the telecommunication satellites to their final orbits. Those kickburns consumed a large amount of propellant due to comparably low I_{sp} of the socalled “apogee engines”. The propellant required contributed significantly to the launch mass and volume of the satellite. However, the complete transfer only took about one week until the satellites would be fully operational in orbit.
Within the last recent years, substantial financial savings could be achieved using EP for GSK and EOR [2]. Due to the much higher I_{sp} (up to a factor of 10) in comparison to typical chemical devices, considerable economic advantages occur because the amount of propellant to be launched could significantly be reduced. Since the total cost of a mission relates strongly to the absolute mass to be launched, either considerable financial savings or a substantial increase of dry mass might be achieved. Nowadays, most geosats are brought to low earth orbit (LEO) with the launcher. With the use of continuously operating electric thrusters, a constant (electric) orbit raising (EOR) is achieved, which consumes only fractions of the propellant mass typically associated with an orbit raise. However, compared with chemical engines, EOR requires a significantly longer period of time for spiralup due to the low thrust of EP devices (up to 6 months). Given the advantages listed above (most prominently the fact that the geosats can use the same thrusters for EOR and GSK, ridding the need of different systems with different piping, valves, tanks, etc.), many satellite operators favor this option nowadays.
There are different types of EP devices available and ready for those applications [3, 4]. Hall effect thrusters (HET) have been flightproven since 1971 [5] and have, up to now, been the first choice for EP demands. However, radiofrequency (RF) ion thrusters represent a viable alternative. This is mainly due to their typically almost twice as high I_{sp}, which resides in the area 3,000−4,000s. Additionally, plasma generation and extraction can be regarded as decoupled mechanisms which facilitates scalability of RF ion thrusters. This makes them, in principle, the optimal technology for EOR and GSK. Unfortunately, RF ion thrusters often struggle with lifetime issues which result from extraction grid erosion. In contrast to HET where the plasma ions are extracted through an annular orifice (for a detailed description of HET refer to Ref. [3] and references therein), in RF ion thrusters ions are extracted from the plasma using a gridded extraction system; hence their classification as gridded ion engine (GIE). An inherent issue of GIEs is grid erosion effects caused by highenergy ions bombarding the grids directly (direct impingement) or chargeexchange collisions (CEX) between fast ions and slow neutrals which exchange momentum of those species. The latter results in fast neutrals and slow (positive) ions which are attracted by the negative potential of the accelerator grid, which in turn manifests itself in socalled “barrel erosion” of the accelerator grid [6].
To overcome those drawbacks, numerical analyses are often performed starting at a very early stage in the thruster development process. Since timescales are limited in industry and detailed knowledge of the internal microscopic processes is often not needed, global and hybrid models which are trimmed to speed are the preferred choice. Therefore, a precise knowledge of details such as the electron energy distribution function, which can be determined by PICMCC approaches [7], is not necessarily required, as long as the accuracy of the determination of quantities such as the required input power of the RFG is not diminished significantly. Furthermore, global models can be rather easily used to simulate plasmas fed by molecular propellants, such as an iodine [8] or oxygen [9]. For both iodine and oxygen, the discharge can be electronegative, which shows that global models can even be applied to such plasmas. This a remarkable advantage of modeling ion sources used for materials processing using global models, since those often use molecular gases, which exhibit a much more complicated plasma chemistry in comparison with noble gases. Electronegative gases, such as iodine or sulfur hexafluoride are also investigated as propellant for a neutralizer free electric propulsion system, where both negatively and positively charged ions are extracted in order to avoid a charging of the spacecraft. This principle has been introduced in the frame of the project PEGASES (plasma propulsion with electronegative gases) [10].
In this paper, we want to analyze different approaches of global (and hybrid) RF ion thruster models published in literature, discuss their pros and cons as engineering tools during thruster development and try to give recommendations how to integrate global and hybrid models into the development steps of a real thruster. For this purpose, we briefly introduce the most relevant physics of RF ion thrusters in “Physics of RF ion thrusters” section, then introduce three different, but nevertheless somewhat similar models in “Global RF ion thruster modeling” section: pure global (furthermore referred to as 0D model), 0D/2D (referred to as 2D model) and 0D/3D (referred to as 3D model) hybrid models. The nomenclature is due to the specialized handling of the plasma and electromagnetic phenomena, respectively. The basic plasma processes are described in a global (0D) fashion, albeit with slight modifications depending on the attached electromagnetic model (0D, 2D, or 3D). We work out the theories used for each of the models in detail in the respective sections. A benchmark thruster (RIT4), as depicted in Fig. 1, is analyzed with each model in “Comparison and discussion of the results” section and their respective outputs are compared and validated by experiments in “Experimental validation” section.
Physics of RF ion thrusters
The foundation of RF ion thrusters, which were formally invented by H. Löb in the 1960s [11], are inductivelycoupled plasma (ICP) sources which have been and still are widely used for materials processing purposes [12–14]. The advantageous characteristics of ICP sources for materials processing purposes, e.g. scaleable ion beam energy and low divergence angle, are also what makes them interesting for space propulsion. Low divergence angles are correlated with high specific impulse which relates the effective axial exhaust velocity of the thrusters c_{eff} to the gravitational acceleration on the Earth surface g_{0}:
High I_{sp} implies high mass utilization efficiency which can be deduced from the equation for thrust:
This relation is derived directly from Newton’s laws (mainly Netwon’s third law “ actio=reactio” reflecting momentum conservation) and is an essential figure of merit for space propulsion systems. Substituting Eq. (1) in Eq. (2) results in
which shows that for constant thrust F low mass consumption \(\dot {m}_{\mathrm {p}}\) corresponds to high I_{sp}.
From Eq. (1) it is evident that high I_{sp} is based on high effective axial exhaust velocity which can be obtained by adjusting the extraction grid voltages to the ICP parameters accordingly. The grid voltages V_{screen} and V_{accel} correspond to the screen grid and the acceleration grid potentials, respectively. V_{screen} determines the kinetic energy and hence the exhaust velocity of the extracted ions of chargetomass ratio q_{i}/m_{i} reads:
This is an approximate relationship due to the negligible influences of the ion flux towards the walls induced by the voltage drop V_{p}≪V_{screen} between the plasma center and the walls as well as, secondly, neutral particles escaping the thruster with only thermal velocity. Furthermore, η denotes the divergence angle due to radial velocity components which will not contribute to thrust, if a perfect axisymmetric ion beam is assumed.
The extraction of highvelocity particles will only be accomplished, if the plasma yield (energy and density of ions at the plasma sheathedge) is high enough. In other words, there has to be a sufficient amount of flux of chargecarriers (electrons and ions) towards the extraction grid to meet the amount of thrust to be generated. The thrust can also be expressed as a function of the ion beam current I_{b} and the effective exhaust velocity, as can be derived when substituting Eq. (4) in Eq. (2):
Equal amounts of flux of electrons and ions characterize bounded plasmas. Since in all plasmas quasineutrality is demanded; i.e., positive charge must equal negative charge within the bulk volume on a macroscopic scale, and since many technological plasmas, such as those used in RF ion thrusters, consist of mainly electrons and singly positively charged ions, the number density of both species is approximately equal:
This equation, however, does not hold true in the plasma sheath between the bulk of the plasma and structural walls of the discharge vessel. Due to their significantly lower mass, electrons will traverse the sheath layer much faster than ions, leading to negative charging of the walls with respect to the plasma bulk. This negative potential promotes further ion flux and prohibits further electron flux towards the walls and ultimately a steady state with equal fluxes of ions and electrons arises, resulting in stable plasma parameters with n_{+}≫n_{−} in the sheath layer [12].
The particle flux is a direct consequence of the plasma parameters and thus related to the input parameters coil current \(\underline {I}_{\text {coil}}\), radiofrequency f, and propellant mass flow \(\dot {m}_{\mathrm {p}}\). The (inter)dependence of plasma parameters, electromagnetic fields and input RF coil current can be described using a timeharmonic diffusion equation of the electrodynamic vector potential
In this equation, \(\mathbf {\underline {J}}_{\mathrm {s}}\) denotes the source current density generating a vector potential \(\mathbf {\underline {A}}\) and ω=2πf. Throughout this paper, the underline denotes a complex quantity.
In typical lowtemperature plasmas, the permeability approximates to the vacuum permeability (μ≈μ_{0}) and is thus independent of space. The interconnection of plasma and EM (electromagnetic) fields is expressed by the conductivity \(\underline {\kappa }\), which can be correlated to plasma density and electron temperature in terms of collision parameters. For this purpose, Drude models are often used for global (RF) plasma modeling [13, 15, 16]:
In this equation, ω_{pe}=(n_{e}e^{2}/(m_{e}ε_{0}))^{0.5} denotes the electron plasma frequency; i.e., the collective oscillation of the electron “cloud”, ε_{0} the vacuum permittivity and ν_{eff} the effective collision frequency of electrons. Strictly for RF plasmas, the ions are often regarded as immobile with respect to the quickly alternating EM fields due to their inertia and thus are not taken into account as primary particles in Eq. (8). They are, however, considered as background particles with whom the electrons may collide, thus they contribute to the effective collision frequency:
The first term in this equation is the elastic electronneutral collision frequency which is derived from the collision cross section and the second term describes the above mentioned Coulomb collisions between electrons and ions. Detailed information about these processes and the underlying cross sections is given elsewhere [12–14, 17–20].
Equation (8) determines the electric power needed to sustain the plasma, depending on the stationary conditions of the plasma discharge parameters, mainly electron temperature T_{e}, neutral gas density n_{0} and bulk ion density n_{+}. Equation (7) can be solved for A and related to the electric field vector by assuming no scalar potential gradient within the plasma bulk area [21], leading to
The absorbed RF power is then given by volume integration of the power density,
with \(E=\left \underline {\mathbf {E}}\right \).
To correlate the RF power to the propulsive performance of a RF ion thruster, the generated beam current I_{b} has to be further examined. The beam current is given by
with the elementary charge e, the ion density at the plasma presheath edge n_{+,s}, the Bohm velocity of ions u_{B}=(k_{B}T_{e}/m_{i})^{0.5}, the total cross section area of the extraction grid A_{g} and its ion transmission factor β_{i} [12, 22]. Only singly positively charged ions are assumed here which holds true to a certain extent for most RF ion thruster operational regimes [22, 23].
As can be deduced from Eqs. (11) and (12), the ion density as well as the electron temperature, in terms of u_{B}, relate the ion beam current to the electromagnetic field effects inside the plasma chamber and thus the necessary RF power to sustain the corresponding state of the plasma.
An important quantity is the ion transmission factor β_{i} which is selfconsistently dependent on the plasma parameters (T_{e} and n_{−}≈n_{+} as well as n_{0}). It is given by the ion beam current related to the current traversing the plasma (pre)sheath. Thus, it can be obtained by analyzing the ion trajectories through the extraction system. If a strong defocusing of ions occurs, β_{i} will be reduced, also reducing the beam current. Hence the thrust and overall propulsive performance of the thruster will suffer. Additionally, the beam divergence is affected, which is hence inherently coupled to the transmission factor. More information on ion optics in general can be found in [24–30] and in particular, in terms of transmission factor modeling, will be shown later in the paper.
To focus the ions and accelerate them to high exhaust velocities, screen voltages in the kV range are typically used. The power dissipated by the extraction grid system is given by
where V_{screen} is the screen grid voltage. The acceleration grid is negatively biased with V_{accel}. Purposes of this approach are the abovementioned focusing of ions and the repelling of electrons to avoid electron backstreaming (EBS) which changes operational conditions for the thruster and hence gives rise to adverse eroding mechanisms. However, since typically I_{accel}≪I_{b} and V_{accel}<V_{screen}, there is hardly any power deposited on the acceleration grid. The same applies for the ground grid in 3gridsystems.
Altogether, the power to sustain a given mode of operation is given by the sum of Eqs. (11) and (13). The powering electronics can be divided into RF and DC components. In the remainder of the paper, only the RF electronics will be analyzed in greater detail, since it comprises an inextricable part of the plasma generation system. The DC part can easily be decoupled as DC electronics can be considered linear under most operation conditions.
To ensure efficient energy coupling from RF generator (RFG) to the thruster plasma, its output frequency is often matched to the resonant frequency of the thruster impedance, which is determined by the ohmicinductive plasma load and a series resonant capacitor. Additionally, the influence of the feeding cable has to be accounted for as well. More information on the subject is given elsewhere [31, 32].
The thruster impedance can be correlated to its propulsive performance and hence its input terminal’s parameters (voltage, current, frequency) following Poynting’s theorem:
Radiative processes are neglected, which holds true due to comparably low frequency (i.e. large wavelengths of about 100m) and short conducting structures which do not form any kind of waveguide. The impedance \(\underline {Z}=R+\mathrm {i}\omega L\) can be derived from Eq. (14) following the procedure given in Ref. [21].
Global RF ion thruster modeling
Global plasma and ion source models have been reported on since the early days of exceedingly increasing computing capabilities. Most of them can be traced back to Ref. [33] and references therein. Inductivelycoupled plasma sources have been used most prominently for materials processing applications. Hence, a majority of existing global models focus on plasma sources of the inductive type [15, 16]. They are regarded as basis for many published global (0D) RF ion thruster models [8, 22, 34–38]. Those models have in common that they treat all of the underlying physical mechanisms as described in Eqs. (2)–(14) in a global, volumeaveraged way. This speeds up simulations and allows one to derive, even for large thrusters, results in a reasonable time frame. Thus, it provides a useful virtual prototyping tool for thruster development. There are, however, certain drawbacks and restrictions of global models. Especially, if strong geometrical features break symmetries. This is typically the case for RF ion thruster induction coils which are often electrically short. The magnetic field generated inside such coils cannot be considered purely axial; especially at the coil ends there will be a strong radial component which builds up approaching these limits. Those radial components will have a measurable effect on the coupling of RF energy into the plasma and may lead to significant errors if not properly taken care of (scaling parameters, fit functions, etc.).
Most of the problems induced by global assumptions have been solved by 2D axisymmetric approaches. In some models only the EM solver is capable to handle 2D geometries and the plasma is still regarded as homogeneous [34]. There are more consistent approaches which predefine a density distribution [39–41], either derived from empirical studies [42], fluid models [43, 44] or full particleincell/MonteCarlocollision (PIC/MCC) approaches [7, 45, 46]. It is evident that fluid and especially PIC/MCC models aim at a totally different output (deeper understanding of microscopic plasma behavior, evolution of statistical distribution functions etc.) than global models, which, due to typically long simulation duration, makes them inappropriate for virtual prototyping applications.
To enable the most realistic representation of the EM fields inside actual thruster geometries, 3D models have to be used. To keep simulation duration at a minimum, even those models are coupled to homogeneous or predefined plasma density profiles [47, 48]. This approach is considered as the most reasonable tradeoff between accuracy and simulation duration. However, as will be shown in “Comparison and discussion of the results” section, for typical cylindrical discharge vessel and coil geometries, the 2D approach should be a good enough representation of the actual physics involved–even though simplified solvers are used. The models developed at our respective institutes are shown in the following sections. Table 1 lists the main working mechanisms and differences of the proposed models.
0D model
The global model examined here is based on a publication by Chabert et al. [36]. In addition, it has been extended by linking it to the software IGUN [49] to adequately model the ion optics of the thruster’s grid system.
The global model is composed of four coupled differential equations describing the time evolution of neutral gas density n_{0}, ion or electron density n_{+}, neutral gas temperature T_{0}, and electron temperature T_{e}. All rate coefficients are calculated using the cross sections provided by the “Biagi database” [50] assuming a Maxwellian electron energy distribution function. While the 3D model uses the same cross sections, the 2D axisymmetric model uses those provided by the “Hayashi database” [51]. Assuming a Maxwellian distribution function is quite common in global modeling, due to simplicity and a lack of precise knowledge of the actual distribution function in the plasma. The actual distribution may, among other factors, even depend on the thruster’s operational point. Multiply charged ions are not considered and due to quasineutrality of the main plasma, ion and electron density are described by the same equation in the model. The ion and neutral gas temperatures are assumed to be equal. The input parameters used to represent the geometry are length l_{DC} and radius of the discharge chamber R in addition to the number of coil windings N_{Coil}. The coil windings are considered to be evenly distributed over the entire length of the cylindrical discharge chamber. The transmission properties of the gridsystem are described by two dimensionless parameters for the neutral gas β_{n} and the ions β_{i}. In a first approach, the efficient transparency for neutral gas β_{n} can be calculated as the product of the geometrical transparency of the screen grid, with respect to the cross section corresponding to the diameter of the discharge vessel, and the total transmission probability P_{Total} through one extraction channel. P_{Total} is determined as a serial connection of pipes of arbitrary length [52]:

A_{1} : Cross section of a aperture in the screen grid.

A_{i} : Cross section of element with the index i.

P_{Total}: Total transmission probability.

P_{i}: Transmission probability of element of index i.
$$ \delta_{i,i+1} = \left\{\begin{array}{l} 1 \quad A_{i+1}<A_{i} (\text{Reduction of cross section}) \\ 0 \quad A_{i+1}\geq A_{i} (\text{No reduction of cross section}). \end{array}\right. $$(16)
The transmission probability for one element of the extraction channel P_{i}, either an aperture, or a part of the inter space between the grids, is considered and calculated the with the empirical formula for cylindrical pipes of arbitrary length l and diameter d [52]:
This approach typically estimates slightly smaller values, about 5% to 10%, of β_{n} compared to the more advanced methods, such as described in “2D axisymmetric model” section. For this reason, this approach was not used for the simulations of this publication. Instead, the value obtained by the more advanced method presented in “2D axisymmetric model” section was used; yielding a better comparability of the results.
Furthermore, the frequency of the RF current in the coil, the ohmic resistance of the coil at this frequency, the propellant mass flow \(\dot {m}_{\mathrm {p}}\) injected into the discharge chamber and the RF power P_{RF} are also input parameters of the model. From the electron temperature, ion density and neutral gas density, the ion current generated by the thruster can be calculated. In contrast to the works of Chabert et al. the neutral gas temperature was kept constant in order to be able to compare this modeling approach to the other two models.
Based on the electron temperature and ion density as well as the grid geometry and applied voltages, IGUN allows the extracted ion current to be calculated [49]. The ion density is weighted by the factor h_{l}, which describes the edgetocenter plasma density ratio on the grid surface, before entered into IGUN. For calculating the factor h_{l} as well as h_{r} the solution for the intermediate pressure regime introduced by Godyak [53] is used. The ion current obtained that way serves as a comparison for the ion current obtained from the global model in order to be able to find a value for the ion optics parameter β_{i}. This must be determined iteratively by the aforementioned comparison, since the ion optics parameter both depends on and affects the particle densities and electron temperature.
To determine the plasma parameters and the necessary RF power at a given mass flow and beam current set point I_{b,set}, the procedure shown in the flow chart in Fig. 2 is applied.
With the given thruster parameters, the differential equations from Chabert et al., denoted as ODEs in Fig. 2, are solved. The values of the densities and temperatures in steady state are used to calculate the beam current I_{b}. The RF power is adjusted until the beam current matches the beam current set point. Then the output values of the differential equations are used to perform a calculation with IGUN. The beam current output from IGUN (I_{IGUN}) is compared to the beam current from the differential equations. If the currents do not match, the ion optics parameter in the global model will be adjusted accordingly. If these currents are identical, it must be verified if the beam current still matches the beam current set point. If this is not the case, the RF power will be adjusted accordingly and the process will be repeated. If the beam current of the global model and the beam current set point match, the calculation at the specific operating point will be terminated. The thrust is calculated according to Eq. (5) under the assumption of a parallel ion beam and, therefore, cosη=1.
2D axisymmetric model
A quite detailed description of the 2D model is given in Ref. [41]. Here, only the most important features should be addressed to give the reader an idea about the model’s inner mechanisms and how to work out the main differences to the other presented models. It is noteworthy that within the 2D axisymmetric simulation domain, which is described by cylindrical coordinates (r,ϕ,z), all quantities x are assumed to be constant with respect to the azimuth angle ϕ, leading to simplified equations. Hence, all quantities x that can be deduced from the vectorpotential are independent of ϕ and, therefore, ∂x/∂ϕ=0. This leads to simplified equations.
A flow chart of the 2D model is given in Fig. 3.
Here, the grid transmission coefficient for ions β_{i} is composed of several single transmission coefficients τ_{i}; one for each beamlet, depending on the plasma density adjacent to each simulated grid cell. Their values are stored as functions of T_{e} and n_{+} in a database and their values are interpolated when accessed by the global model. The ion transmissions coefficients are obtained by an inhouse 2D trajectory tracker based on the PIC method [54, 55], as discussed in “Ions” section. The transmission coefficient for neutrals β_{n} is predetermined using Sandia National Lab’s SPARTA DSMC package [56, 57]. It is an explicit function of the extraction grid geometry since no intermolecular collisions are assumed. Further information can be found further below in this section.
The set point parameters include the angular frequency ω, the beam current I_{b,set}, the extraction voltages V_{screen} and V_{accel}, the propellant mass flow \(\dot {m}_{\mathrm {p}}\) and the temperature of the propellant gas and all of the thruster components T_{0}. A full thermal equilibrium of neutrals and ions is assumed. Additionally, initially best guesses of the bulk ion/electron density n_{+}/n_{−} and the Maxwellian electron temperature T_{e} are used to start the iterative operation.
Before the iterations start, the neutral gas density, which is assumed constant throughout the volume, can be derived as a function of the set point beam current:
Here, v_{th}=(8k_{B}T_{0}/(πm))^{0.5}denotes the thermal Maxwellian velocity magnitude of the neutrals, with their mass m and A_{g} the extraction grid area.
Charge conservation
The innermost loop is a charge conservation equation which relates the volume ionization rate to the charge lost due to flux out of the plasma:
In this equation, K_{iz}=K_{iz}(n_{0},T_{e}) denotes the rate coefficient for ionization of neutrals by incident electrons and is strongly coupled to the underlying distribution function of the particles, which is here assumed to be Maxwellian (electrons, ions and neutrals are all assumed to obey a Maxwell distribution in phase space; however, since T_{e}≫T_{i}≈T_{0}, only ions (T_{i}) and neutrals (T_{0}) are assumed to be in thermal equilibrium with the structural components). R furthermore denotes the upper radial, z_{min} and z_{max} the lower and upper axial boundaries of the plasma in the simulation domain, respectively. H is a heuristic density distribution function first introduced in Ref. [39]. It is based on analytic sheathtobulk density factors [33, 42]. It follows a parabolic shape and can thus be used to examine most of the operational points of an RF ion thruster plasma [58]:
Here, h_{r} and h_{l} denote the sheathtobulk density ratios which depend strongly on n_{0} and z_{0} denotes the axial center of the plasma.
Equation (19) is solved by means of numerical integration and Newton’s method for T_{e}.
EM field solver / energy conservation
With T_{e} and n_{0}, the plasma conductivity from Eq. (8) can be formulated. The structural components of the thruster, such as gas inlet, induction coil, extraction grid and housing, are parameterized by temperature dependent conductivity models following first order approximations,
with the electrical resistivity ρ_{0} at temperature 𝜗 and an empirical fit parameter α which is provided for many metals by databases like NIST. A thorough overview is given in Ref. [59].
The inductively coupled RF power from Eq. (11) is obtained by a finitedifference representation of Eq. (7) which is numerically solved [47]. This absorbed power within the plasma region is computed against the power lost to collisions and wall flux and solved for n_{+}:
The collision and wall flux losses are given by (with the temperatures T_{e} and T_{0} given in V):
where K_{m},K_{ei},K_{iz},K_{ex},E_{iz} and E_{ex} denote the rate coefficients for momentum transfer (electronneutral), Coulomb collisions (electronion), single ionization (electronneutral), excitation (electronneutral), the first ionization energy threshold and the excitation energy threshold. For the latter, about 50 states are incorporated in case of xenon as propellant gas. The voltage drop across the plasma presheath and sheath region V_{p} is furthermore given by
with the mean Maxwellian electron velocity v_{e}=(8eT_{e}/(πm_{e}))^{0.5}. Equation (22) can finally be solved for n_{+} in an outer iterative loop.
Extraction and performance model
With T_{e} and n_{+} converged to stable values, a variation of Eq. (12) can be solved for the beam current. The corresponding ion transmission parameter β_{i}(T_{e},n_{+}) is calculated from each τ_{i} stored in a lookup table which is accessed during evaluation from several sub models. Therefore, it is advisable to obtain this table prior to the global model simulations which will be shown in the next section.
If the calculated beam current does not match the desired set point value (I_{b}≠I_{b,set}), the coil current is updated by a proportionalintegral controller. After convergence, the thruster performance (Eqs. (3) and (5)) and impedance (derived from Eq. (14)) are calculated.
Transmission factor modeling
This section gives a brief introduction of the two sub models that determine the transmission factors for neutral flux β_{n} and ion flux β_{i}. Both models need the actual extraction grid geometry as input.
Ions
The ion transmission coefficient β_{i} is determined by a trajectory tracking code loosely based on the PIC method. In this case, axisymmetry is assumed, hence only the center beamlet can be evaluated. If the distance between adjacent beamlets is large enough, the error is negligibly small as can be demonstrated by comparison to full 3D PIC solutions [60, 61].
A flow chart of the trajectory tracking code is shown in Fig. 4.
The scheme follows approaches shown in Refs. [49, 60, 62–64] with a special treatment of the differential operator for cylindrical axisymmetry. In principle, a nonlinear static electric potential equation is solved iteratively while the ions traverse the simulation domain until all trajectories have exited the modeled domain of the extraction channel. The numerical solution is rather complicated due to the nonlinear term in the Poisson equation,
which is given by the Boltzmann factor for the electron density at the sheath edge, with Φ_{0} denoting the potential of ions and electrons when entering the simulation domain at the plasma sheathedge. It arises due to the negative wall potential with respect to the Maxwellian plasma bulk and hinders electrons to traverse the sheath unless they have a sufficiently high kinetic energy. It is however crucial to incorporate this term due to otherwise nonrealistic ion trajectories, since all particles are extracted from a quasineutral plasma and the sheath is governed by spacecharge effects.
After each successive potential update, a chain of operations is performed which a) calculates the spacecharge of ions within the simulation domain (“Scatter”), b) maps the electric field vectors, which are stored on discrete grid points, onto the charges which can be located at arbitrary positions (“Gather”), c) uses those electric field values as driving forces in an equation of motion q_{p}E=m_{p}dv_{p}/dt yielding updated velocities and d) pushes the ions to new coordinates with the updated velocity values (“Push”). For the mechanisms in c) and d) commonly the Leapfrog method is used where velocity and spatial vectors are staggered by a half time step size to increase numerical stability [65].
After all ions have either collided with structural parts or have left the simulation domain, the resulting spacecharge map is checked for changes compared to its preceding iteration. If this is the case, a new ion density map is generated (as a function of said spacecharge map) and fed back to the Poisson equation. The loop is repeated until all quantities converge within a given tolerance.
The grid ion transmission factor β_{i} is then calculated from the transmission factors for each beamlet τ_{i}. Those can be broken down to functions of the current entering the simulation domain I_{in} and the beam current I_{b} leaving the domain (the sum of all beamlet currents I_{bl}):
Neutrals
The transmission coefficient for neutrals is an explicit function of the grid geometry. Here, a 2D representation induces nonnegligible errors which will ultimately lead to very wrong power balances. Hence, a 3D solution for this particular problem is chosen. The problem is solved using Sandia’s SPARTA (stochastic parallel rarefiedgas timeaccurate analyzer). The simulated section is shown in Fig. 5 and manifests as a unitcell with symmetric boundary conditions to all lateral boundaries (not in flow direction).
As can be seen, with this approach, only a small fraction of the total grid system has to be simulated. Due to the symmetry boundary conditions a hexagonal aperture pattern arises which is typical for RF ion thruster grids.
The flow of particles is considered to be freemolecular, so no particle collisions are implemented. Instead, only diffuse reflections with structural components are taken into account.
The transmission coefficient is obtained in a similar manner than the one for ions, simply by relating the flux of particles at the downstream boundary γ_{ds} to the fixed number at the inlet γ_{in} and scaling to the full grid geometry:
In this equation, N denotes the number of extraction beamlets and A_{SPARTA} the rectangular simulation domain area in SPARTA representing half an extraction beamlet, as shown in Fig. 5.
3D model
The model described in this section is an extension of our previously published model [48]. An inhouse 3D ion extraction code, published in Ref. [61], is used to simulate a unit cell of the extraction system with the geometry shown Fig. 5. The simulated region is chosen to represent one unit cell of an indefinite large array of extraction channels arranged in a hexagonal manner. This approach with an 3D implementation takes into account the effects of adjacent holes and beamlets on the ion optics behavior; in contrast to the axisymmetric treatment presented in the last section. The same 3D approach is used to simulate the neutral gas transmission coefficient by utilizing the test particle MonteCarlo (TPMC) method [66]. This method is based on simulating the trajectories of multiple test particles. The transmission coefficient is given by the amount of test particles leaving the ion thruster divided by the amount of generated test particles. The particles are generated at a boundary representing the plasma. Hereby it is important to use statistically evenly distributed positions and velocity vectors. An isotropic velocity of neutral particles inside the plasma is assumed. The trajectories are calculated by integrating the equation of motion and applying a mirror reflection at the boundaries towards neighboring simulation domains and an explicitly diffusive reflection when colliding with an extraction grid. The neutral gas density as well as the temperatures of neutrals, ions and electrons are assumed to he spatially homogeneous.
As well as in the 2D model a density profile inside the plasma for the electrons and ions is assumed, which is considered consistently in each sub model. For the calculation of this profile h parameters describing the sheathtobulk density ratios are used, as described in Ref. [48]. The h parameters are based on analytic equations valid for different density regimes. We use a fitting equation between different regimes introduced in Ref.[53]. The profile already described by Eq. (20) was separated into two parts in order to better cope with noncylindrical geometries. For this, the center of mass of the ionization chamber is calculated and assumed to be the center of the plasma. Starting from this point the distance R towards the most distant point in radial direction, the distance l_{p} towards the most distant point in positive axial direction and the distance l_{n} towards the most distant point in negative axial direction are calculated. Based on these distances the corresponding h parameters \(\phantom {\dot {i}\!}h_{\mathrm {r}}, h_{\mathrm {l}_{\mathrm {p}}}\), and \(\phantom {\dot {i}\!}h_{\mathrm {l}_{\mathrm {n}}}\) are calculated. The profile is then calculated with
where l is the coordinate in axial direction with l=0m at the position of the plasma center and r is the radial distance from the plasma center.
Furthermore, the plasma conductivity model was updated. In the model used the electromagnetic fields are solved in 3D. The calculation of losses inside the plasma is done similarly to Eqs. (23)–(27) described for the 2D model. An integration method was implemented to enable the simulation of arbitrary geometries. Therefore, the 3D model also includes the gas inlet. While P_{iz},P_{ex} and P_{w} are calculated the same way as in the 2D model, we neglect P_{ei} and use a different equation to calculate P_{m}. The latter difference is not described in detail because the term is of negligible influence. The equations used to calculate the amount of generated and lost ions are also the same.
Solving the selfconsistent set of balance equations
To reach a self consistentsolution we use the approach presented in Ref. [67] and updated it to also incorporate our new peripheral model, which is described in the following subsection. The corresponding flow chart is illustrated in Fig. 6.
By using multiple conditions, the balance equations are decoupled to be able to calculate the three unknown state quantities (neutral gas density n_{0}, electron temperature T_{e} and ion density n_{+} at the plasma center) sequentially. First, we define the set point values. In particular, we set the neutral gas temperature T_{0} and the material temperatures T_{m} to 423K. Furthermore, we set the radiofrequency f, the grid voltages V_{ext} and the geometry. The neutral gas density is then calculated in the same manner as already mentioned in “2D axisymmetric model” section. In the 3D model, we iterate n_{0} until the balance equation of neutral particles (denoted as mass conservation in Fig. 6 is satisfied.
After n_{0} has been obtained, we assume that the density profile of electrons and ions (Eq. (32)) does not depend on the value of the ion density in the plasma center n_{+}. Accordingly, the solution of the charge conservation; i.e., the balance equation of ions generated inside the plasma and ions lost at the edge of the plasma, is independent of n_{+}. Therefore, any value of n_{+} can be chosen to solve the equation for T_{e}. This is done by iterating the electron temperature T_{e} until a value is found which satisfies the balance equation (ΔI≈0A).
After n_{0} and T_{e} have been obtained, the spatial ion extraction can be calculated with a given value of n_{+}. This is done by iterating the value of n_{+} until the simulated beam current I_{b} matches the beam current set as boundary condition. After this, all state quantities (n_{0},T_{e} and n_{+}) have been obtained. With these values the plasma losses P_{n} as well as the spatial plasma conductivity \(\underline {\kappa }_{\mathrm {p}}\) are calculated. The latter is used for the electromagnetic field solver to simulate the impedance of the thruster system \(\underline {Z}_{\text {th}}\) which includes the plasma resistance R_{p}.
With R_{p} and P_{n} known, the coil current I_{coil} is calculated with I_{coil}=(P_{n}/R_{p})^{0.5}. Finally, the simulated impedances and I_{coil} are used inside the peripheral model, in which die DC input voltage V_{DC} of the RFG is iterated until the simulated coil current matches I_{coil}. Then the input power P_{DC}, the input voltage V_{DC} and the input current I_{DC} are known.
Peripheral model
The utilized radiofrequency generator (RFG) was developed at the Technische Hochschule Mittelhessen  University of Applied Sciences (THM). It is based on a field programmable gate array (FPGA) processing a digital phase and frequency control algorithm presented in [31, 68].
The algorithm is used to generate the driving signal for a halfbridge consisting of two GaN MOSFETs of type “GS66516TE02MR” from the manufacturer GaN Systems, with the hardware assembly shown in [32]. The rectangular output signal is used to excite a resonant circuit consisting of the coil inductance and a resonant capacitance with its resonant frequency. To be able to simulate the switching losses for this setup, a more sophisticated approach than the one presented in Ref. [48] was necessary. Instead of an analytic model a simulation with LTSpice is used. The standard approach would be to use a SPICE model from the manufacturer to describe the MOSFETs in LTSpice. Utilizing these models only the currents and voltages at the MOSFETs connection interfaces; i.e., drain (D), gate (G), and source (C) are visible in the simulation. Given this information, it is difficult to deduce the internal behavior and the resulting losses. For example, turning on the MOSFET while a voltage is applied between source and drain leads to the discharge of the parasitic drainsource capacitance within the MOSFET. This generates losses inside the MOSFET, but the responsible currents do not appear as external currents measurable at the terminals. In addition, the drainsource capacitance of the “GS66516TE02MR” is up to 1nF, which may lead to significant displacement currents. Depending on the topology, these are, due to the nonlinear behavior, hard to distinguish from the active current. To allow one to evaluate the switching process in detail as well as the occurring switching losses one has to simulate the internal mechanisms of the MOSFETs used. A schematic image of the MOSFET with this modeling approach is given in Fig. 7.
The values of the capacitance C_{GS} (between gate and source), C_{GD} (between gate and drain) and C_{DS} (between drain and source) are derived from data sheet values for C_{ISS} (small signal input capacitance), C_{OSS} (small signal output capacitance) and C_{RSS} (small signal reverse transfer capacitance). While C_{GS} is nearly linear (we use C_{GS}=510 pF) the values of C_{GD} and C_{DS} are set up as look up tables to describe their nonlinear behavior. The value \(R^{\prime }_{\mathrm {G}}=1.5 \Omega \) for the internal parasitic gate resistance is also given in the data sheet. All variables with a dash correspond to internal variables of the MOSFET.
The MOSFET’s conductance is modeled by a current source for \(I^{\prime }_{\text {DS}}\) based on fitting the data sheet parameters. The current \(I^{\prime }_{\text {DS}}\) is calculated by
with the threshold voltage V_{th}, the drainsource voltage V_{DS} and the internal gatesource voltage \(V^{\prime }_{\text {GS}}\).
First we define
based on the data sheet. V_{p} and I_{p} define the pinchoff point between linear and saturation region. For \(V^{\prime }_{\text {GS}} > V_{\text {th}}\) (linear region), the term \(I_{\mathrm {p}} \left [1{\left (V_{\text {DS}}V_{\mathrm {p}}\right)}^{2}/ V^{2}_{\mathrm {p}}\right ]\) is used, which describes a parabolic behavior of \(I^{\prime }_{\text {DS}}\) with respect to V_{DS}. At V_{DS}=0V we have \(I^{\prime }_{\text {DS}}=0 \mathrm {A}\) and the vertex is at \(I^{\prime }_{\text {DS}}=I_{\mathrm {p}}\) with V_{DS}=V_{p}.
For V_{DS}≥V_{p} (saturation region), the current \(I^{\prime }_{\text {DS}}\) is assumed to be constant over V_{DS}. Since \(I^{\prime }_{\text {DS}}=f(V_{\text {DS}})\) both I_{p} and V_{p} change with \(V^{\prime }_{\text {GS}}\). This is taken into account by describing I_{p} and V_{p} as functions of \(V^{\prime }_{\text {GS}}\). For I_{p}, the fit
is used to describe the vertex of the parabola (coinciding with the current at the pinchoff point). For V_{p}, the fit
is used, so that the initial slope of the chosen parabola describes the switching resistance between drain and source R_{DS(on)} which is approximately 40mΩ. The fitting is performed for an assumed junction operating temperature of 343K with the values given in the data sheet (Rev. 161007).
The reverse conductivity is modeled by a diode. The complete peripheral model is shown in Fig. 8.
The twowire cable is described by inductance L_{cab}=140nH and resistance R_{cab}=43mΩ. The 0.15m long transmission line of type “Belden 9220” is described by a Πmodel with the transmission line’s input and output capacitance C_{tl}=7.6pF, its inductance L_{tl}=38nH and its resistance R_{tl}=7mΩ. Furthermore the resonant capacitance inside the RFG C_{res}=2.725nF is set and its equivalent series resistance R_{esr} is calculated by its loss tangent tan(δ)=0.001. The voltage sources for the gates are set to the given excitation frequency with the corresponding delay times.
Experimental validation
For validating the presented global models, a comparison with experimental results is mandatory. A meaningful comparison can only be drawn if several requirements are fulfilled. Most importantly, the pressure in the vacuum tank has to be low enough to reduce backflow of neutrals into the thruster to a minimum. Otherwise this effect is a source of error when comparing the results of the simulations and the experiment.
Experimental setup
The cylindrical vacuum chamber BigMac Evo of about 3m in length and a diameter of 1.6m was used for the experiments. Operating the thruster, xenon is mainly pumped by two cryogenic pumps with a total pumping speed of 34,000ls^{−1}. Therefore, the xenon partial pressure does not exceed 10^{−4}Pa for flow rates up to 100µgs^{−1}. Assuming a homogeneous pressure distribution inside the tank and taking the conductance of the thruster’s grid of approximately 5ls^{−1} into account, the backflow of xenon into the thruster is only about 0.01µgs^{−1} and, therefore, negligible. The actual backflow might be slightly higher, since the pressure along the thruster’s beam axis can be assumed to be slightly larger than the mean value. However, even if the actual backflow would be an order of magnitude larger, it would still be very small compared to the flow injected into the discharge vessel. A turbomolecular pump of 2,350ls^{−1} nominal pumping speed for nitrogen is used for the pumpdown and later on keeps the residual pressure of nitrogen and oxygen on an acceptable level; since the cryo pumps can not continuously be kept cold enough for pumping those gases. The pressure in the vacuum facility is monitored by a Pirani/coldcathode combination gauge from by Pfeiffer Vacuum.
The thruster is mounted radially in the center of the vacuum tank and is attached to an ISOK160 flange. A test power supply (TPS) unit is used for operating the thruster. The TPS contains the power supplies for controlling the RFG, the screen and acceleration grid of the thruster. For providing power to the RFG, a “TDKLambda GENH6012.5” is used. The screen and accel grids are supplied by “FuG MCP 7002000” and “FuG MCP 352000” sources, respectively. The deceleration grid is directly connected to the facility ground. Using an ordinary computer, all power supplies as well as the mass flow controller, type Bronkhorst “ElFlow Select” with a maximum range of 140µgs^{−1} xenon, are digitally controlled by a LabViewbased control software. A beam current controller is implemented to keep the current flowing to the screen grid constant. This current is adjusted by tuning the RFG’s input voltage. As requirement of stability for each data point of the performancemapping, the largest tolerated drift of the RFG’s input power is 1% in a time interval of 30min. In order to fulfill this condition, the overall time span operating the thruster was 6h.
For further validation of the global models, the current through the coil is monitored with a Pearson probe 2878.
Measurement results
The recorded performance mapping is shown in Fig. 9 a). The input power of the RFG decreases strictly monotonously with an increase of the mass flow. The shape of the curve is typical for operating this kind of thrusters with noble gases [48, 69, 70]. The current through the coil exhibits a similar dependence on the mass flow.
Mass and electrical efficiency deduced from the experiment are plotted in Fig. 9 b) as function of the mass flow. The largest obtained mass efficiency η_{m}, which is calculated as ratio of the mass flow of ions leaving the thruster to the mass flow injected into the thruster, is 71.8%, the smallest mass efficiency is 43.4%. Another measure for the thruster’s efficiency is the electrical efficiency η_{e}. In the case of a RF ion thruster, its common definition is the ratio of the power applied to the screen grid to the total input power required for operating the thruster. The total power is mainly determined by the sum of the RFG’s input power and the power provided to the screen grid. Other contributions to the total power balance, such as the power supplying the acceleration grid (≤0.1W) are negligible. In the covered range of the performance mapping, the obtained electrical efficiency is 39.4% for the smallest and 48.2% for the largest injected mass flow.
Comparison and discussion of the results
The performance curve obtained by the experiment serves as benchmark for the three global models. Table 2 lists the properties of the RIT 4 that are necessary to reproduce the results of the 0D model.
A comparison of the results is shown in Fig. 10. The 3D model shows a very good agreement with the experimental data, as shown in Fig. 10 a). The 2D axisymmetric as well as the 0D model do not take losses in the RFG into account. Therefore deviations to the RFG’s input power are expected. Comparing the RFG’s output power values derived with the three models at the same operational points a general trend is given over the entire range of the performancemapping shown in Fig. 10 b). The 2D axisymmetric model yielded the smallest output power of the RFG, while the 0D model estimated the largest output power. The output power values determined by the 3D model are situated between the estimates of the other models. However, at low mass flows the agreement is better between the 3D and the 0D model, whereas at large flows, a better agreement of the 3D model with the 2D axisymmetric model is given.
In Fig. 10 c) the 2D model and the 3D model estimated coil currents close to the actual value, unless the mass flows were smaller than about 65µgs^{−1}. In this range of lowest flows, both models slightly overestimate this current. The 0D model generally strongly underestimates the current transmitted by the coil. A likely reason is the very simplistic description of the coil using the approximation of long coils, which is quite inaccurate, since the length of the coil is shorter than its diameter. The 2D axisymmetric model describes the coil as N_{Coil} parallel conductor loops and solves the associated EMfield. Therefore, the coil’s helical structure is not fully considered. The 3D model fully accounts for the coil’s helical shape and solves the associated EM fields. In addition, the assumption of a homogeneous electron density profile generally leads to an underestimation of the RF current transmitted by the coil in comparison to the holistic profile assumed by both the 3D model and the 2D axisymmetric model [48].
In order to understand the difference in the results of the three models, as a first step, the amount of power deposited in several loss channels is studied. At first, the losses in the discharge vessel will be split into two categories: First, the losses inside the plasma volume (mainly excitation and ionization) and, second, losses by absorption of ions and electrons on the inner walls of the discharge vessel and the screen grid. The results are shown in Fig. 11.
All three models show that the losses by impact of electrons and ions on the thruster’s walls exceed those by processes inside the plasma volume at low input mass flows. Increasing the flow, a crossing point occurs, where losses in the volume start to become dominant. However, while for both the 3D and 2D model this crossing point is observed at a mass flow of 84µgs^{−1}, in the case of the 0D model this point is already reached at a mass flow of 68µgs^{−1}. Overall, the 0D model seems to overestimate the losses in the plasma volume. The 2D model estimated the smallest losses over the entire range of the simulation, for losses in the plasma volume as well as losses on the thruster’s walls. To gain a better understanding of this behavior, one has to consider as well the plasma parameters and must look into the losses inside the plasma volume in more detail.
The calculated plasma parameters are depicted in Fig. 12. Raising the mass flow leads to an increase of both neutral and electron density and to a decrease of the electron temperature. The neutral density is in the order of a few 10^{19}m^{−3}, while the electron density is smaller by about two orders of magnitude. The electron temperature of a few electron volts is typical for inductively coupled low temperature discharges [12]. The neutral density shows a very good agreement between all models over the entire range of mass flows studied. The electron temperature estimated by the 0D model is significantly lower compared with the 2D axisymmetric and the 3D model; which are both in very good agreement. We guess that this discrepancy is caused by the difference in the assumed electron density profiles, as discussed in detail by Reeh et al. in a recent publication [48]. The electron density in the radial center of the discharge is very similar for the 3D model and the 0D model. The mean electron density estimated by the 0D model is significantly larger. For a mass flow of 75µgs^{−1}, the mean electron density determined from the electron density profile calculated by the 3D model is about 82% of the value in the center of the discharge. The reason for the slight discrepancy of the electron density between the 2D axisymmetric and the 3D model is not known, yet. A possible reason is the use of a different cross section database. The radial profile of the electron density determined by the 2D axialsymmetric and the 3D model is identical, as shown in the insert of Fig. 12 a).
If one considers the spatially averaged electron density, the 0D model estimates a larger electron density compared to both other models. This can partially explain the larger estimated losses in the plasma volume, since all losses in the discharge volume are proportional to the product of electron density and neutral density.
Figure 13 shows the power that is used for the ionization of xenon to achieve the designated screen current of 30mA and the power which is lost due to excitation of the neutral atoms. The power required for ionization is virtually independent of the used mass flow. The power invested for ionization is similar for all models, although the 0D model estimated a slightly larger power of about 1W−1.5W. As shown by all models, the power lost due to excitation rises with increasing mass flow. However, the absolute values determined by the models disagree by a significant margin.
At the largest mass flow operating the thruster, of about 94µgs^{−1}, the difference is approximately 4W between the 0D and both the 2D model and 3D model. At smaller flows, and therefore smaller neutral gas densities, the discrepancy becomes slightly less pronounced, but does not disappear. The difference can be explained by the different mean electron densities and electron temperatures. The small difference of the losses due to excitation by the 2D and 3D model can be explained solely by the difference in the estimated electron density, since the electron temperature and therefore, the rate coefficient for excitation, is identical.
As a second series of simulations, the extracted beam current was varied while keeping the neutral gas density constant. In order to keep the neutral gas density constant while increasing the beam current, the injected mass flow is increased by the same amount as the equivalent additional mass flow leaving the discharge chamber through the apertures of the screen grid. For singly charged xenon ions, a current of 1mA is equivalent to a mass flow of 1.36µgs^{−1}. For the smallest beam current of 10mA a mass flow 24.4µgs^{−1} was chosen. The advantage of keeping the neutral gas density constant is that the electron temperature is constant as well.
This yields a rather simple situation, facilitating the discussion correlation of beam current I_{b} and the ion transmission factor β_{i}. Since the electron temperature and neutral gas density are essentially fixed, the beam current is solely dependent on β_{i} and the electron density at the sheath edge. The simulations were performed for currents ranging from 10mA to 32.5mA, the results are given in Fig. 14.
For both significant larger and smaller beam currents than in the simulated range, the beam current leaving the thruster’s grid system is no longer equal to the current transmitted through the screen grid, because large grid currents occur as ions impinge on acceleration or deceleration grids due to a detuning of the ion optics. The detuning occurs because the plasma meniscus depends on the plasma parameters. Such operational points have to be avoided while operating those thrusters and are, therefore, of less interest. As depicted in Fig. 14, an increasing beam current leads to an increase of the required electron density, while the ion transmission factor decreases. The averaged transmission coefficients calculated by all global models and their respective ion optics simulation show the same trend. The ion transmission coefficient β_{i} decreases with an increasing beam current. However, especially for beam currents of 25mA and above, the values derived by the three models deviate significantly. The difference between the 0D model and the other two models can be explained by different plasma parameters arising due to the model assumptions at the same operational points, both electron temperature and the mean electron density.
The electron temperatures are virtually constant for each model. The values of 6.5eV for the 2D and 3D model are in good agreement, while the electron temperature calculated by the 0D model is considerable lower by about 0.8eV.
In contrast, the electron density calculated by the 0D model and the 3D model appear to be in very good agreement in Fig. 14 b), whilst that derived with the 2D model is somewhat lower. However, one has to keep in mind that the electron density in the radial center is plotted, and not the mean value, which is significantly smaller for the 3D model.
The reasons for the discrepancy of the ion transmission coefficients β_{i} of the 2D axisymmetric and the 3D model are not well understood yet. While the calculated ion transmission coefficient is larger for the 2D axisymmetricmodel, the electron density calculated by the 3D model is larger by essentially the same factor at each point of operation. Therefore, the product of n_{+} and β_{i} is the same for both models, yielding the same beam current, since the electron temperature is virtually identical, as previously shown in the analysis of the performance mapping.
Computational time An important feature of global models is the rather short computational time required for modeling a performance curve. Using the 0D model, the performance curve shown can be calculated in less than half an hour including the simulation of the ion optics, which requires the majority of the computational time. If one calculates the performance mapping using a constant ion transmission coefficient, the required time is just 15s. However, to obtain the required ion transmission coefficient at the desired current leaving the discharge, a simulation of a few minutes is required first. The simulation time was achieved with a office computer with 16GiB RAM and a Intel^{Ⓒ} i5 hexacore CPU of the ninth generation. Despite the use of a CPU with six cores, most calculations are done using one core only. The 2D axisymmetricmodel and the 3D model require several hours to one day to simulate the ion optics as base for the simulation of a performance mapping. An exhaustive analysis of the ion optics over a wide range of ion densities, electron temperatures and, therefore, beam currents can require simulation times from several days to a few weeks. The remaining calculating time for the performancemapping is comparably short, for the shown results about one hour. The longer simulation time compared to the 0D model is mainly caused by the required time for simulating the electromagnetic fields. The determination of the neutral gas transmission factor using SPARTA requires only few tens of minutes and must be performed only once for a given grid system. The hardware used for running the simulations of the 2D axisymmetric model contains a fairly up to date Intel^{Ⓒ} i7 quad core processor with 16GiB RAM. The four cores are not used in parallel for all sub models, partially only one core is used. The 3D model simulation was executed on a workstation with two 8 core/16 thread CPUs (Intel^{Ⓒ} Xeon E52650) with 256GiB RAM. Regarding the ions optics simulation the integration of the trajectories with the gather process as well as solving the electrical field is simulated in parallel on 32 threads while the remaining tasks, such as the scattering, are implemented on one thread. All further calculations of the remaining sub models are done using one core.
Conclusion
All global models presented provide at least a satisfactory prediction of a performance curve of the RIT4. In particular, the 3D model can predict the necessary RFG power to operate the RIT4 very accurately. However, in difference to the 2D axisymmetric model and the 3D model, the 0D model cannot predict the coils current with sufficient accuracy. We guess, that this is caused by both the assumption of a long coil and the electron density profile used. Further studies concerning this issue have to be conducted. The calculated plasma parameters and losses show the qualitatively expected trends in all models. The neutral gas density is determined in the same fashion by all models. The electron temperature shows a very good agreement between two of the three models. The deviation of the third model, the 0D model, confirms the influence of the electron density profile on the determination of the electron temperature predicted by Reeh et al. [48]. However, there are significant differences in the determined electron densities, the cause of which is only partially known. The aforementioned deviations of the plasma parameters are mirrored in the different distribution of power losses such as the absorption of ions and electrons by the discharge vessel walls or due to excitation of electronic states of the xenon atom. In a second comparison, the beam current was varied. The results confirmed the differences of the plasma parameters. It was shown, that the discrepancy of the calculated electron density between the 2D axisymmetric and the 3D model can be directly related to the different determined ion transmission coefficients. However, the reason causing the differences is not clear yet.
Future activities should, among other things, aim at a more accurate comparison between simulation and experiment. Of particular importance is a measurement of the radial electron density distribution; since in the context of this publication the influence on the different power dissipation channels in the discharge vessel was clearly shown. Furthermore, a further runtime optimization of the ionoptics simulations appears to be essential since in each of the presented models they accounted for the largest fraction of the total computational time. All models are already able to deliver useful information for future thruster development at least at a qualitative level and should be able to accelerate the development process by a very meaningful margin. While those models may lack in accuracy in describing the details of the microscopic processes in the discharge, they can accurately calculate the quantities necessary for describing the thruster’s performance. Hence, global models are an excellent compromise of a very accurate but time consuming description of the plasma by a PICMCC approach and very fast, but often also very inaccurate, analytic approximations. However, further validations are required to confirm and ensure the predictive power of such models.
Availability of data and materials
The data sets used and/or analyzed during the current study are available from the corresponding author on reasonable request.
Abbreviations
 EP:

Electric spacecraft Propulsion
 GSK:

Geostationary/Geosynchronous Station Keeping
 EOR:

Electric Orbit Raising
 GTO:

Geostationary elliptical Transfer Orbit
 LEO:

Low Earth Orbit
 HET:

Hall Effect Thruster
 GIE:

Gridded Ion Engine
 CEX:

Charge Exchange collisions
 ICP:

Inductively Coupled Plasma
 EBS:

Electron Backstreaming
 RFG:

RadioFrequency Generator
 PIC:

ParticleInCell
 MCC:

MonteCarloCollisions
 ODE:

Ordinary Differential Equation
 SPARTA:

Stochastic Parallel Rarefied gas Timeaccurate Analyzer
 DSMC:

Direct Simulation MonteCarlo
 NIST:

National Institute of Science and Technology
 TPMC:

Test Particle MonteCarlo
 THM:

Technische Hochschule Mittelhessen
 FPGA:

Field Programmable Gate Array
 MOSFET:

MetalOxideSemiconductor FieldEffect Transistor
 TPS:

Test Power Supply unit.
References
Holste K, Dietz P, Scharmann S, Keil K, Henning T, Zschätzsch D, Reitemeyer M, Nauschütt B, Kiefer F, Kunze F, Zorn J, Heiliger C, Joshi N, Probst U, Thüringer R, Volkmar C, Packan D, Peterschmitt S, Brinkmann KT, Zaunick HG, Thoma MH, Kretschmer M, Leiter HJ, Schippers S, Hannemann K, Klar PJ. Ion thrusters for electric propulsion: Scientific issues developing a niche technology into a game changer. Rev Sci Instrum. 2020; 91(6):061101. https://doi.org/10.1063/5.0010134.
Davis JP, Mayberry JP, Penn JP. Cost Reductions and Fuel Efficiency: HighPower Solar Electric Propulsion in Space. Technical report. The Aerospace Corporation. 2018. https://aerospace.org/sites/default/files/201811/DavisMayberry_HPSEP_11212018.pdf. Accessed 08 June 2021.
Mazouffre S. Electric propulsion for satellites and spacecraft: established technologies and novel approaches. Plasma Sources Sci Technol. 2016; 25(3):033002. https://doi.org/10.1088/09630252/25/3/033002.
Lev D, Myers RM, Lemmer KM, Kolbeck J, Koizumi H, Polzin K. The technological and commercial expansion of electric propulsion. Acta Astronaut. 2019; 159:213–27. https://doi.org/10.1016/j.actaastro.2019.03.058.
Zhurin V, Porotnikov A, Shadov V. Electric propulsion research and development in the USSR. In: 12th International Electric Propulsion Conference. Key Biscayne: American Institute of Aeronautics and Astronautics: 1976. https://doi.org/10.2514/6.19761073.
Brophy J, Katz I, Polk JE, Anderson JR. Numerical Simulations of Ion Thruster Accelerator Grid Erosion. In: Proceedings of the 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Indianapolis: AiAA (American Institute of Aeronautics and Astronautics): 2002.
Henrich R, Heiliger C. Three Dimensional Simulation of Micro Newton RITs. In: Proceedings of the 33rd International Electric Propulsion Conference. Washington DC: ERPS (Electric Rocket Propulsion Society): 2013.
Grondein P, Lafleur T, Chabert P, Aanesland A. Global model of an iodine gridded plasma thruster. Phys Plasma. 2016; 23(3):033514. https://doi.org/10.1063/1.4944882.
Roberson G, Roberto M, Verboncoeur J, Verdonck P. Global model simulations of lowpressure oxygen discharges. Braz J Phys. 2007; 37(2a):457–65. https://doi.org/10.1590/s010397332007000300019.
Aanesland A, Rafalskyi D, Bredin J, Grondein P, Oudini N, Chabert P, Levko D, Garrigues L, Hagelaar G. The PEGASES Gridded IonIon Thruster Performance and Predictions. IEEE Trans. Plasma Sci. 2015; 43(1):321–6. https://doi.org/10.1109/tps.2014.2369534.
Loeb H. Ein elektrostatisches Raketentriebwerk mit Hochfrequenzionenquelle. Astronautica Acta. 1961; 8:50–62.
Lieberman MA, Lichtenberg AJ. Principles of Plasma Discharges and Materials Processing, 2nd edn. Hoboken, NJ, USA: WileyInterscience; 2005.
Chabert P, Braithwaite N. Physics of RadioFrequency Plasmas. Cambridge, UK: Cambridge University Press; 2011.
Hopwood J. Review of inductively coupled plasmas for plasma processing. Plasma Sources Sci Technol. 1992; 1:109–16.
Gudmundsson JT, Lieberman MA. Magnetic induction and plasma impedance in a cylindrical inductive discharge. Plasma Sources Sci Technol. 1997; 6:540–50.
Vahedi V, Lieberman MA, DiPeso G, Rognlien TD, Hewett D. Analytic model of power deposition in inductively coupled plasma sources. J Appl Phys. 1995; 78(3):1446–58. https://doi.org/10.1063/1.360723.
Hayashi M. Determination of electronxenon total excitation crosssections, from threshold to 100 eV, from experimental values of Townsend’s α. J Phys D: Appl Phys. 1983; 16:581–9.
Godyak VA, Piejak RB, Alexandrovich BM. Electrical characteristics and electron heating mechanism of an inductively coupled argon discharge. Plasma Sources Sci Technol. 1994; 3:169–7.
Piejak RB, Godyak VA, Alexandrovich BM. A simple analysis of an inductive RF discharge. Plasma Sources Sci Technol. 1992; 1:179–86.
Chen FF. Introduction to Plasma Physics and Controlled Fusion. Switzerland: Springer; 2016. https://doi.org/10.1007/9783319223094.
Jackson JJ. Classical Electrodynamics. Hoboken, NJ, USA: Wiley; 1998.
Goebel D, Katz I. Fundamentals of Electric Propulsion: Ion and Hall Thrusters. Hoboken, NJ, USA: Wiley; 2008.
Groh KH, Loeb HW. Radiofrequency ion sources for space propulsion (invited). Rev Sci Instrum. 1992; 63(4):2513–8. https://doi.org/10.1063/1.1142875.
Aston G, Wilbur PJ. Ion extraction from a plasma. J Appl Phys. 1981; 52(4):2614–26. https://doi.org/10.1063/1.329071.
Aston G, Kaufman HR, Wilbur PJ. Ion Beam Divergence Characteristics of TwoGrid Accelerator Systems. AIAA Journal. 1978; 16(5):516–24.
Kaufman HR. AcceleratorSystem Solutions for BroadBeam Ion Sources. AIAA Journal. 1977; 15(7):1025–34.
Whealton JH. Ion extraction and optics arithmetic. Nucl Inst Methods Phys Res. 1981; 189:55–70.
Whealton JH, Whitson JC. SpaceCharge Ion Optics Including Extrasction from a Plasma. Part Accelerators. 1979; 10:235–51.
Whealton JH, Jaeger EF, Whitson JC. Optics of singlestage accelerated ion beams extracted from a plasma. Rev Sci Instrum. 1977; 48(7):829–31. https://doi.org/10.1063/1.1135165.
Whealton JH, Jaeger EF, Whitson JC. Optics of Ion Beams of Arbitrary Perveance Extracted from a Plasma. J Comput Phys. 1978; 27:32–41.
Simon J, Probst U, Klar PJ. Development of a RadioFrequency Generator for RF Ion Thrusters. Trans Jpn Soc Aeronaut Space Sci, space technol Jpn. 2016; 14(ists30):33–9.
Junker JE, Probst U, Klar PJ. Development of a full bridge series resonant radiofrequency generator for optimized RIT operation. In: Proceedings of the 36th International Electric Propulsion Conference. Vienna, Austria: ERPS (Electric Rocket Propulsion Society): 2019.
Lee C, Lieberman MA. Global model of Ar, O2, Cl2, and Ar/O2 highdensity plasma discharges. J Vac Sci Technol A: Vac Surf Films. 1995; 13(2):368–80. https://doi.org/10.1116/1.579366.
Closs MF. RF Ion Thruster Design Software Based on Numerical Modeling. In: Proceedings of the 3rd International Conference on Spacecraft Propulsion. Cannes: ESA (Eurpoean Space Agency): 2000. p. 419–22.
Tsay MM, MartinezSanchez M. Simple performance modeling of a radiofrequency ion thruster. In: Proceedings of the 30th International Electric Propulsion Conference. Florence: ERPS (Electric Rocket Propulsion Society): 2007. p. 2007–72.
Chabert P, Monreal JA, Bredin J, Popelier L, Aanesland A. Global model of a griddedion thruster powered by a radiofrequency inductive coil. Phys Plasma. 2012; 19(7):073512. https://doi.org/10.1063/1.4737114.
Kanev SV, Khartov SA, Nigmatzyanov VV. Analytical model of radiofrequency ion thruster. Procedia Eng. 2017; 185:31–8. https://doi.org/10.1016/j.proeng.2017.03.287.
Pham QTD, Shin J. Better prediction of the performance of a radiofrequency ion thruster. J Korean Phys Soc. 2020; 76(2):137–44. https://doi.org/10.3938/jkps.76.137.
Dobkevicius M, Feili D. A coupled performance and thermal model for radiofrequency gridded ion thrusters. Eur Phys J D. 2016; 70(11):227–40. https://doi.org/10.1140/epjd/e2016702737.
Dobkevicius M, Feili D. Multiphysics Model for RadioFrequency Gridded Ion Thruster Performance. J Propuls Power. 2017; 33(4):939–53. https://doi.org/10.2514/1.B36182.
Volkmar C, Geile C, Hannemann K. RadioFrequency Ion Thrusters–Power Measurement and Power Distribution Modeling. J Propuls Power. 2018; 34(4):1061–9. https://doi.org/10.2514/1.B36868.
Lucken R, Croes V, Lafleur T, Raimbault JL, Bourdon A, Chabert P. Edgetocenter plasma density ratios in twodimensional plasma discharges. Plasma Sources Sci Technol. 2018; 27(3):035004. https://doi.org/10.1088/13616595/aaaf61.
Turkoz E, Celik M. 2D Electromagnetic and Fluid Models for Inductively Coupled Plasma for RF Ion Thruster Performance Evaluation. IEEE Trans Plasma Sci. 2014; 42(1):235–40. https://doi.org/10.1109/TPS.2013.2287903.
Turkoz E, Celik M. AETHER: A simulation platform for inductively coupled plasma. J Comput Phys. 2015; 286:87–102. https://doi.org/10.1016/j.jcp.2015.01.027.
Boyd ID, Gilder DBV, Liu X. Monte Carlo Simulation of Neutral Xenon Flows in Electric Propulsion Devices. J Propuls Power. 1998; 14(6):1009–15.
Takao Y, Eriguchi K, Ono K. TwoDimensional ParticleinCell Simulation of a Micro RF Ion Thruster. In: Proceedings of the 32nd International Electric Propulsion Conference. Wiesbaden: ERPS (Electric Rocket Propulsion Society): 2011.
Volkmar C, Ricklefs U. Implementation and verification of a hybrid performance and impedance model of gridded radiofrequency ion thrusters. Eur Phys J D. 2015; 69(227):227–43. https://doi.org/10.1140/epjd/e2015603804.
Reeh A, Probst U, Klar PJ. Global model of a radiofrequency ion thruster based on a holistic treatment of electron and ion density profiles. Eur Phys J D. 2019; 73(232):232–52. https://doi.org/10.1140/epjd/e20191000023.
Becker R, Herrmannsfeldt WB. IGUNA program for the simulation of positive ion extraction including magnetic fields. Rev Sci Instrum. 1992; 63(4):2756–8. https://doi.org/10.1063/1.1142795.
program FORTRAN. MAGBOLTZ, S.F. Biagi, version 8. 97, Biagi database. 2021 https://nl.lxcat.net/contributors/#d6. Accessed 08 May 2021.
Hayashi M. Bibliography of Electron and Photon Cross Sections with Atoms and Molecules Published in the 20^{th} Century XenonNIFSDATA079. Technical report. National Institute for fusion science. 2003. https://www.nifs.ac.jp/report/nifsdata079.htm. Accessed 08 June 2021.
In: Jousten K, (ed).Wutz Handbuch Vakuumtechnik, 11edn. Wiesbaden: Vieweg+Teubner Verlag; 2012. https://doi.org/10.1007/9783834817457.
Godyak VA. Soviet Radio Frequency Discharge Research. Okaland: Delphic Associates; 1986.
Hockney RW, Eastwood JW. Computer Simulation Using Particles. Bristol, UK: A. Hilger; 1988.
Birdsall CK. ParticleinCell ChargedParticle Simulations, Plus Monte Carlo Collisions With Neutral Atoms, PICMCC. IEEE Trans Plasma Sci. 1991; 19(2):65–85.
Bird GA. Molecular Gas Dynamics and the Direct Simulation of Gas Flows. NY, USA: Oxford University Press; 1994.
Bird GA. The DSMC Method. SC, USA: CreateSpace; 2013.
Goebel DM. Analytical discharge model for RF ion thrusters. IEEE Trans Plasma Sci. 2008; 36(5):2111–21. https://doi.org/10.1109/TPS.2008.2004232.
Desai PD, Chu TK, James HM, Y. HC. Electrical Resistivity of Selected Elements. J Phys Chem Ref Data. 1984; 13(4):1069–96.
Kalvas T, Tarvainen O, Ropponen T, Steczkiewicz O, Ärje J, Clark H. IBSIMU: A threedimensional simulation software for charged particle optics. Rev Sci Instrum. 2010; 81(2):02–703. https://doi.org/10.1063/1.3258608.
Reeh A, Probst U, Klar PJ. 3D Ion Extraction Code incorporated selfconsistently into a numerical Model of a RadioFrequency Ion Thruster. In: Proceedings of the 35th International Electric Propulsion Conference. Atlanta: ERPS (Electric Rocket Propulsion Society): 2017.
Peng X, Keefer D, Ruyten WM. Plasma Particle Simulation of Electrostatic Ion Thrusters. J Propuls Power. 1992; 8(2):361–6.
Bond RA, Latham PM. Extraction System Design and Modelling Using Computer Codes. In: Proceedings of the 23rd AIAA/AIDAA/DGLR/JSASS International Electric Propulsion Conference. Seattle: ERPS (Electric Rocket Propulsion Society): 1993. p. 1644–54.
Araki SJ, Wirz RE. Cellcentered particle weighting algorithm for PIC simulations in a nonuniform 2d axisymmetric mesh. J Comput Phys. 2014; 272:218–26. https://doi.org/10.1016/j.jcp.2014.04.037.
Brieda L. Plasma Simulations by Example. Boca Raton, FL, USA: CRC Press, Taylor & Francis Group; 2019.
In: Jousten K, (ed).Wutz Handbuch Vakuumtechnik, 8edn. Wiesbaden: Vieweg+Teubner Verlag; 2004, p. 827.
Reeh A, Probst U, Klar PJ. Elegant Approach for solving the Conservation Laws in Global Modelling of RadioFrequency Ion Thrusters. In: Proceedings of the 36th International Electric Propulsion Conference. Vienna: ERPS (Electric Rocket Propulsion Society): 2019.
Simon J. Entwicklung und Aufbau eines Radiofrequenzgenerators zur Versorgung und Elektrischen Charakterisierung induktivgekoppelter Plasmen in RadiofrequenzIonentriebwerken. PhD thesis. JustusLiebigUniversity Giessen. 2016. http://geb.unigiessen.de/geb/volltexte/2017/12283/.
Holste K, Gärtner W, Zschätzsch D, Scharmann S, Köhler P, Dietz P, Klar PJ. Performance of an iodinefueled radiofrequency ionthruster. Eur Phys J D. 2018; 72(1):9. https://doi.org/10.1140/epjd/e2017804985.
Dietz P, Gärtner W, Koch Q, Köhler PE, Teng Y, Schreiner PR, Holste K, Klar PJ. Molecular propellants for ion thrusters. Plasma Sources Sci Technol. 2019; 28(8):084001. https://doi.org/10.1088/13616595/ab2c6c.
Acknowledgements
European regional funding in the frame of the EFRE scheme of the State of Hesse is gratefully acknowledged.
Funding
Open Access funding enabled and organized by Projekt DEAL.
Author information
Authors and Affiliations
Contributions
P. Dietz conducted the experiments, wrote the sections about the experiments, the results obtained by the simulations, prepared the majority of the figures and wrote the section dealing with summary and outlook. A. Reeh contributed by performing the simulations of the 3D model and wrote the section on the associated model as well as the RFG model coupled with it. K. Keil contributed by performing the simulations with the 0D model and writing the associated section. K. Holste simulated the neutral gas transparency using COMSOL, which was used to confirm the neutral transmission factor calculated with SPARTA. C. Volkmar performed the simulations with the 2D axisymmetric model and wrote the introduction of this manuscript as well as the 2D axisymmetrical model section. P. J. Klar and U. Probst supervised the activities. All authors contributed by discussing the results obtained and improving the manuscript of this article. All authors read and approved the final manuscript.
Corresponding author
Ethics declarations
Ethics approval and consent to participate
Not applicable.
Consent for publication
All authors agree to the publication of the article.
Competing interests
The authors declare that they have no competing interests.
Additional information
Publisher’s Note
Springer Nature remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.
Rights and permissions
licensee Springer on behalf of EPJ. Open Access This article is licensed under a Creative Commons Attribution 4.0 International License, which permits use, sharing, adaptation, distribution and reproduction in any medium or format, as long as you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons licence, and indicate if changes were made. The images or other third party material in this article are included in the article’s Creative Commons licence, unless indicated otherwise in a credit line to the material. If material is not included in the article’s Creative Commons licence and your intended use is not permitted by statutory regulation or exceeds the permitted use, you will need to obtain permission directly from the copyright holder. To view a copy of this licence, visit http://creativecommons.org/licenses/by/4.0/.
About this article
Cite this article
Dietz, P., Reeh, A., Keil, K. et al. Global models for radiofrequency ion thrusters. EPJ Techn Instrum 8, 10 (2021). https://doi.org/10.1140/epjti/s40485021000685
Received:
Accepted:
Published:
DOI: https://doi.org/10.1140/epjti/s40485021000685
Keywords
 Electric propulsion
 Plasma modeling
 Global model
 Ion extraction code