Content uploaded by Konstantinos Katsonis
Author content
All content in this area was uploaded by Konstantinos Katsonis on Oct 01, 2021
Content may be subject to copyright.
AEC2020_525
CO2 BASED ISRU PROPULSION FOR SATELLITES AND SPACECRAFTS IN THE
VICINITY OF MARS
Chloe Berenguer(1), Konstantinos Katsonis(1), Jose Gonzalez del Amo(2)
(1) DEDALOS Ltd., Vas. Olgas 128, 54645, Thessaloniki, Greece, Email: katsonis.dedalos@gmail.com
(2) ESTEC, European Space Agency, Noordwijk, The Netherlands, Email: jose.gonzalez.del.amo@esa.int
KEYWORDS: Mars atmosphere, Mars orbits,
Detailed Global Model, CO2 propellant, Plasma
components, Functioning Diagram, Theoretical
spectra, Optical Emission Spectroscopy
ABSTRACT:
The CO2DGM Detailed Global Model is used to
characterize electric thrusters using in situ available
CO2 as propellant. Low pressure values in the region
of 1 mTorr to 10 mTorr with a feed of 40 sccm are
addressed. Besides an improved functioning insight,
the essentials of optical emission spectroscopy
diagnostics and monitoring are provided by this
model. Collecting of the electric thruster propellant in
the region where a mission is intended is particularly
advantageous, hence this technology is meant to be
used in Solar System missions related e.g. to Mars
and Venus.
1. INTRODUCTION
CO2-fueled Electric Thrusters (ET) have been lately
considered in the context of In Situ Resource
Utilization (ISRU) for satellite and s/c propulsion in
the space region near Mars [1] with the help of
models of the Global Model (GM) type [2]. In order to
support this technology, DEDALOS Ltd has
constituted an heritage of Detailed Global Models
(DGM), supporting fueling of ETs by the most
common propellants encountered in the Solar
System (SSys), including CO2 , nitrogen, oxygen and
their mixtures. Such potential propellants appear
notably as constituents of Atmospheric Remnants
(AtRems). Description of the GM development and
its formulation in case of gaseous molecular
constituents as N2, N2O and air are contained in [2-
5], allowing to evaluate their possible use as ET
propellants. In the present contribution, modeling
and Optical Emission Spectroscopy (OES)
diagnostics supporting CO2 related ISRU technology
are sought, based on a dedicated DGM, with
“detailed” referring to inclusion in the GM of a
sufficiently high number of statistical equations in
order to obtain theoretical emission spectra
(ThSpec) of the main plasma components. This
model, CO2DGM, meant to support Mars and near
Mars missions, concerns e.g. study of the Mars
satellites and of more distant minor planets as Ceres
and Hygeia, expected to contain H2O. It is also of
interest to missions related to exploration of Venus,
of various satellites and other bodies of our Solar
System. In general, CO2DGM provides the
necessary modeling and diagnostics tools for CO2-
breathing ETs. Specifically, it evaluates the plasma
components composition and provides functioning
diagrams describing the thruster functioning
conditions. It also calculates detailed ThSpecs for
comparison with experimental spectra, thus resulting
to OES diagnostics. General considerations on the
ISRU technology support to missions concerning
Earth and Mars and their regions are addressed in a
separate contribution of this Conference [6].
Mars ATMosphere (MATM) is used here as
propellant to support satellite propulsion in Low Mars
Orbits (LMO) and Very Low Mars Orbits (VLMO) and
s/c propulsion for missions addressing notably the
Phobos and Deimos regions. CO2DGM allows for
controlling and diagnosing the ET plasma and for
optimizing the ET, resulting to handy tools for the
plasma analysis even in-flight. It is adaptable to the
ET plasma form factor and type and gives preview,
characterization, diagnostics and monitoring of CO2-
fueled ETs [1]. These tasks are obtained using the
following main CO2DGM assets, which are
addressed and discussed in details :
(i) Plasma Component Composition (PCC)
diagrams, allowing for the evaluation of the electron
density and temperature and of the densities of
various ET plasma components. For a given form
factor, these are depending mainly on the plasma
pressure, on the absorbed electric power and on the
feed of the selected CO2 propellant.
(ii) Functioning Diagrams (FD), providing the
ionization percentage of each of the plasma
components following iso-baric and iso-thermal
curves. The total ionization level depends for a given
form factor and a selected feed on the total pressure
and on the absorbed power. Thus, we can obtain a
thrust preview and optimize the ET functioning.
(iii) Calculation of ThSpecs belonging to various ET
functioning conditions. Absolute intensity values of
the spectral lines composing the ThSpec obtainable
by acquisition of the plasma emission spectra allow,
in comparison with the experimental ones, for OES
diagnostics, a powerful non perturbing method which
avoids all of the drawbacks of the commonly used
Langmuir probes. Detailed study of the ThSpecs
addressed here constitute a prerequisite of
1
AEC2020_525
satisfactory OES results, required for ET
characterization and monitoring.
CO2DGM modeling and its results in evaluating the
thruster plasma components and in previewing the
thruster functioning were described elsewhere [7-11].
CO2DGM model lead simultaneously to the
corresponding ThSpecs of O I, II and C I, II, which
constitute the basis of OES diagnostics for ETs of
low, high and very high power classes. CO2 ThSpecs
have been compared with acquired experimental
spectra belonging to a very high power class
experiment addressing entry to Mars [12]. In addition
to neutral and lowly ionized oxygen [13] species,
those of carbon [12] have been used in order to
compare results from oxygen spectra with those
obtained by carbon ones. More information on
characterization, optimization and diagnostics of ETs
pertaining to various technologies addressed by CO2
-breathing ETs is available in ResearchGate [14].
In Section 2 of this contribution, we review plasma
composition modeling results for CO2-breathing
which are obtained by CO2DGM. These are
addressing the Mars AtRems. Description of the ET
functioning is presented in Section 3. Theoretical
spectra which are simultaneously obtained by
CO2DGM are presented and discussed in Section 4.
Finally, conclusions and perspectives are presented
in Section 5.
2. PLASMA COMPOSITION OF CO2-FUELLED
ELECTRIC THRUSTERS
Preview and analysis of CO2–fueled ET plasma
composition is obtained by means of the
CO2DGM model. As reported previously, PCC
diagrams are on the basis of this task. In so doing,
electron temperature Te and percentages of the
remaining CO2 and of other neutral and ionized
species components of the thruster plasma
depending on the functioning conditions are also
calculated, together with the total ionization
percentage TOT. We present these results in
diagrams concomitant to the PCCs ones, obtaining
an overall evaluation of the plasma state.
For CO2–fueled ISRU devices which are of interest
here, comfortable fuel abundance is expected,
allowing to obtain easily quite high feed levels.
Consequently, we address here feeds of 40 sccm.
Note that higher feeds are expected to result to
higher thrusts in general, provided sufficient power
is absorbed by the propellant. Otherwise, the
available power is mostly spend to various
chemical reactions without leading to the
necessary ionization.
We address a typical ET form factor, consisting in
a radius of R = 2 cm and a length of L = 18 cm,
resulting to a rather small plasma volume of the
order of 200 cm3, pertaining e.g. to Helicon type
technology. Various form factors, of interest to
various thruster technologies and also to
atmospheric entrance have been addressed
elsewhere [15-22].
Results concerning main parameters as electron
density ne and temperature Te , total density nTOT
and the densities of the main plasma constituents
obtained by CO2DGM are shown in the provided
PCC diagrams and their concomitants, in the
rather low pressure region of 1 mTorr to 10 mTorr.
Results belonging to the same form factor and CO2
feed level but in a quite higher pressure region of
10 mTorr to 50 mTorr, are addressed in [6].
The calculated PCCs pertain to an extended
absorbed power values domain, from Pabs = 80 W
up to Pabs = 4.0 kW. However, only two typical Pabs
cases of 80 W and of 1 kW are presented in this
Section. A higher ionization level is expected when
the other functioning parameters remain the same
while the pressure diminishes.
2.1. Results for an absorbed power of 80 W
The plasma composition obtained by CO2GM in
this case is reported in Figs. 1 and 2. Main plasma
parameters are reported in these figures. In order
to avoid using too busy figures, densities of
components including carbon atoms are shown
separately in Fig. 1, while those containing only
oxygen being addressed in Fig. 2. nTOT and ne
values appear in both figures in order to ease the
comparison of results pertaining to the species
appearing in the two figures. Lines appearing in
these two figures and in subsequent ones are used
mainly to ease the eye, with diagrams using similar
symbols.
Figure 1. Pressure-dependent PCC, only C
containing components, 80 W of absorbed power
2
AEC2020_525
Figs. 1 and 2 show the two parts of a PCC diagram
providing fundamental results as total density nTOT ,
electron density ne and the densities of the main
plasma constituents for Pabs = 80 W.
It can be seen in Fig. 1 that under the chosen
conditions, ne (dot dashed red line) corresponding
to the sum of the ionic species densities is not
high, increasing roughly by one order of magnitude
when the pressure is increasing similarly. The total
CO2 density (black curve with squares ■) increases
steadily with pressure, following the total density
nTOT (dash double dotted magenta curve). It is to be
observed that the two curves differ slightly more for
low pressure values, because the lower pressures
favor both dissociation and ionization of CO2 . CO
density (blue line with full triangles ▲) is increasing
with pressure but slower than this of CO2 .The
molecular ions CO2+ (black curve with empty
triangles ∆) are the main positively charged
species, following closely the presence of ne .
Consequently, densities of CO+ (blue curve with x)
(and also these of O+, see Fig. 2) remain to low
levels of around 1011 cm-3. This indicates that the
absorbed power of 80 W is here spend prioritarily
to ionize the abundant CO2 molecule.
C density (green curve with full green diamonds ♦)
starts with low values of about 3x1010 cm-3 for
pressure of 2 mTorr and increases slowly with
pressure, reaching in about 10 mTorr values about
half lower than the ones of the molecular ion CO+.
Inversely, C+ density (green curve with empty
circles o) diminishes slowly with pressure increase.
Figure 2. Pressure-dependent PCC, only O
containing components, 80 W of absorbed power
Fig. 2 shows low values for the total molecular
oxygen presence (Tot O2 , red curve with inverted
triangles), near to those pertaining to the atomic
carbon, corresponding to a CO2 dissociation
channel. However, neutral CO and O species are
much more abundant, indicating a preferential
dissociation channel of CO2 .
Total atomic oxygen density (Tot O, red curve with
empty circles o) has much higher values than Tot
O2 for all pressures, and increases rather slowly
with pressure. Tot O2 is mainly composed by the n
= 0 vibrational level. The atomic oxygen 3s excited
state has density about 109 cm-3 in the 2 mTorr
region exhibiting a metastable character. Its
presence remains the same for all the pressure
values shown.
Presence of O+, (red line with crosses) and even
more of O2+, (red line with stars) are low and
diminish slowly with increasing pressure.
Electronegativity (O- density values, red dotted line
with empty stars) begins with very low values for 2
mTorr, but arrives to almost two orders of
magnitude higher values for an order of magnitude
higher pressure.
A diagram concomitant to the PCC given in two
parts in Figs. 1 and 2 is presented in Fig. 3. It
illustrates additional CO2GM results in a different
form, focusing to the ionization percentage of the
main species. Conditions pertaining to Fig. 3
remain the same with those of Figs. 1 and 2 and
pressure influence is illustrated.
Figure 3. Te , TOT , electron, atomic and molecule
percentage variations. 80 W of absorbed power
We observe in Fig. 3 that Te (red curve with
squares ■, values to be read at the right side of the
figure) reaches very high values for the smaller
pressure values, and that the total ionization
percentage TOT (blue curve with full circles ●,
values to be read at the left side of the figure)
diminishes from more than 20 % for 2 mTorr to
about 8 % approximately for 10 mTorr.
3
AEC2020_525
It can be seen in Fig. 3 that the remaining CO2 is
very abundant; the obtained percentage results are
divided by two in order to be contained in the
figure. They increase steadily with pressure,
exceeding 80 % for 10 mTorr pressure. Ionized
CO2+ (black curve) is the main ionized component
and, as the small difference from the TOT values
appearing around 1 mTorr implies, other ionized
species are scarce, especially with increasing
pressure. Presences of oxygen and CO species
are comparable, with increasing pressure favoring
the latter. All other species are very scarce.
2.2. Results for an absorbed power of 1 kW
We address now the case of a higher absorbed
power of form factor, with Pabs = 1 kW, the other
conditions remaining the same. As was the case in
Section 2.1. we present the corresponding PCC in
two separate figures, pertaining to carbon and to
oxygen results, with symbols similar to those used
in the previous figures.
By increasing the absorbed power while the
plasma volume and the propellant feed remain the
same we obtain a higher ionization, as illustrated
by the two parts of the PCC shown in Figs. 4 and
5, where it can be seen that ne and then the ionic
species densities are more abundant, especially
for low pressure values.
Figure 4. Pressure-dependent PCC, only C
containing components, 1 kW of absorbed power
It can be seen in Fig. 4 that ne increases steadily
with increasing pressure. The presence of CO2
molecule, noted by TotCO2, increases of more than
an order of magnitude when the pressure
increases from 2 mTorr to 10 mTorr. CO2+ density is
higher than this of CO2 both increasing similarly for
increasing pressure values. Densities of CO and of
C increase less fast with the pressure. Increase of
the corresponding ions CO+ and C+ densities is less
pronounced; a tendency to reach a plateau when
pressure increases appears especially for the first
of them.
Density variations for the oxygen components is
illustrated in Fig. 5. The total oxygen atom
presence (Tot O) increases of more than an order
of magnitude when the pressure increases from 2
mTorr to 10 mTorr and remains by far the more
present neutral species, with comparable C density
values increasing similarly to those of the neutral
oxygen. O+ becomes the most present ion for
higher pressures. Unlike atomic oxygen species,
Tot O2 and O2+ have low densities which become
comparable when pressure increases, with the
density of the former remaining about stable and
the density of the latter reaching a plateau at about
2 mTorr. The O metastable level 5S2 3s bearing n°
6 in the Grotrian diagram of O I, has low density,
while the O- density begins with even lower values
for low pressure values but increases fast with
increasing pressure.
Figure 5. Pressure-dependent PCC, only O
containing components, 1 kW of absorbed power
In Fig. 6 a diagram concomitant to the PCC
diagram given in Figs. 4, 5 is shown. In this figure,
total ionization percentage xTOT = nIONS / nTOT shown
is quite different from ne percentage for low
pressure values. This indicates that doubly ionized
4
40
40
AEC2020_525
species exist, although the latter have not been
reported at the bottom of the figure. When p is
diminishing, the total ionization percentage TOT
reaches a plateau at about 4 mTorr.
It can be also seen in Fig. 6 that with diminishing
pressure, Te becomes considerably high, exceeding
8 eV for pressure values lower than 3 mTorr.
Percentages of remaining CO2 , CO and O2
molecules and of atomic carbon are also low, not
exceeding 10 %. The most abundant carbon
containing species is CO2+. Its percentage increase
fast with the pressure. This tendency is also
observed for the corresponding neutral species
CO2 .
Figure 6. Te , TOT , electron, atomic and molecule
percentage variations. 1 kW of absorbed power
3. DESCRIPTION OF THE ET FUNCTIONING
Seeking a better insight of the thruster functioning,
the ionization percentages of the plasma
components following iso-baric and iso-thermal
curves has been evaluated on the basis of FDs
obtained by CO2DGM. In fact, further to PCC
diagrams as the ones presented in Sections 2.1
and 2.2, which provide snapshots of the plasma
composition under various conditions in case of a
CO2-fueled thruster, CO2DGM can lead to a
condensed description of the ET functioning
conditions. Such FD based descriptions for Earth
atmospheric remnants and CO2 addressing also
their comparison have been done previously
elsewhere [23-25].
We address here a typical pressure depending FD,
describing the functioning of a small volume ET
case. Results of absorbed powers from 80 W to
3.0 kW in case of 40 sccm CO2 feed are illustrated
in the FD shown in Fig. 7. In this figure, besides
the feed amount, the form factor and pressure
values spanning the region going from 2 mTorr to
10 mTorr where important variations of results are
expected remain the same.
Figure 7. Pressure-dependent FD, absorbed
power of 80 W to 3 kW
Characteristics of the PCCs addressed in Figs. 1 -
3 (for 80 W) and in Figs. 4 - 6 (for 1 kW) which are
discussed in Section 2 are somehow embedded in
this figure. The considered Pabs values allow for
pressure dependent Te values going from 3 eV up
to 10 eV. The black thick arrow corresponds to
Pabs = 3 kW when the pressure is about 3.5 mTorr.
It indicates that whenever Pabs reaches this level, a
satisfactory ionization is obtained for pressures
about 4.0 mTorr. Under the conditions which
prevail here, optimum pressure region is around 8
mTorr. In case of lower Pabs values the provided
power may mostly be spend to chemical reactions.
It can be seen in Fig. 7 that, once the propellant
feed is selected, the ionization level depends on
the total pressure and on the absorbed power. It is
to be noted that, as we address here an ISRU type
technology, the availability of the propellant
becomes an important issue only in case of
projects addressing missions aiming e.g. Near
Mars Trips (NMT) or space exploration missions
based in the vicinity of Mars or of Venus.
3. OES DIAGNOSTICS SUPPORT BY CO2DGM
Together with the previously presented results
obtained by CO2DGM, theoretical spectra have
been also obtained which constitute the basis of
OES diagnostics, based either simply on oxygen or
also on carbon atomic and ionic species. We
address here only typical cases of OES diagnostics
based solely on the oxygen species, with this choice
limited to the first and second oxygen spectra, in
order to reduce the length of the text. However, ne
and Te results obtained by OES based in oxygen
5
AEC2020_525
spectra can be further compared to those coming
from OES based on the carbon spectra obtained
simultaneously. This comparison of carbon based
OES results to the oxygen based ones may improve
the diagnostics confidence and could be considered
if detailed carbon experimental spectra are also
available.
The first and second theoretical oxygen spectra
obtained by CO2DGM pertaining to the CO2-fueled
ET plasma addressed in Section 2.1 are presented
in Figs. 8 and 9 correspondingly. Various colors are
used for the identification of the addressed multiplets
and of the corresponding evaluated intensities,
aiming a better distinction of the spectral
components. Cores to which the multiplets belong
are also given in parenthesis. Note that the obtained
theoretical VUV lines are by far the most intense in
both spectra, therefore their intensities are divided by
100 in order to fit in the figures. This illustrates a well
known universal pattern of the first, second and
following spectra of oxygen and other elements. It
was then encountered in TheoSp calculated for
carbon and nitrogen species by our DGMs [12,13].
Figure 8. O I theoretical spectrum from the VUV up
to IR regions for CO2 feed of 40 sccm. Pabs of 80 W
Figure 9. O II theoretical spectrum in the VUV, UV
and visible regions for CO2 feed. Pabs of 80 W
For the chosen typical initial conditions, which are
also noted in both Figs. 8 and 9, large spectral
regions including the VUV, UV, visible and IR regions
are addressed. Both theoretical spectra belong to a
total feed of 40 sccm CO2 , 80 W of Pabs and 2 mTorr
of pressure.
Main spectral lines of O I in the 80 nm to 1320 nm
region are shown in Fig. 8. Those of O II in the 80
nm to 700 nm region are shown in Fig. 9.
Comparison of the Figs. 8 and 9 with similar ones
given elsewhere and corresponding also to a CO2
total feed of 40 sccm, but pertaining to other
conditions, do present the same general pattern for
both cases but the intensities of the lines are quite
different. This indicates that the plasma is also not in
coronal equilibrium [26], hence OES diagnostics
becomes possible, provided the corresponding
experimental spectra are available. Consequently,
comparison of the O I and O II theoretical line
intensities shown in Figs. 8 and 9 with acquired
experimental ones results straightforwardly to
evaluation of ne, Te and of the plasma ionization level
and, indirectly, to the abundances of the O, O+ and of
the C, C+ species.
Oxygen species spectra, pertaining to 1 kW
absorbed power, are shown in Figs. 10 and 11.
Figure 10. O I theoretical spectrum from the VUV up
to IR regions for CO2 feed of 40 sccm. Pabs of 80 W.
Figure 11. O II theoretical spectrum in the VUV, UV
and visible regions for CO2 feed. Pabs of 1 kW
6
AEC2020_525
These figures are similar to Figs. 8 and 9 and follow
the same form, but correspond to the high absorbed
power of 1 kW, a case which was addressed in
Section 2.3.
Although the units used in all the theoretical spectra
shown in this Section are arbitrary, they remain the
same for all the figures. As the arbitrary units used in
Figs. 8 to 11 are common, it becomes
straightforward to verify that the shown intensities of
the two spectra corresponding to Pabs of 1 kW are
more intense than those corresponding to Pabs of 80
W. Also, relative intensities belonging to
corresponding lines are different both in the O I and
the O II spectra, as coronal equilibrium is not valid to
any plasma shown.
4. CONCLUSIONS AND PERSPECTIVES
Application of the CO2DGM model in theoretically
characterizing and diagnosing CO2-fed ETs of
interest to one of the more interesting ISRU based
cases for Solar System missions is addressed and
related results have been reviewed. A quite high feed
of 40 sccm has been considered and the main C I –
III levels data sets have been included in the model,
aiming a detailed description of the thruster plasma
and an improved calculation of theoretical spectra to
be used in OES diagnostics. Although only the first
and second oxygen spectra have been used, OES
diagnostics based on carbon species could also be
considered, allowing comparison with the described
results coming from oxygen ones. Reported results
may be used in order to prepare, optimize and
diagnose prototype ETs fed by CO2 in on ground
experiments.
Acknowledgment : Two of the authors (ChB & KK)
are supported for this work by the project AETHER,
which has received funding from the European
Union’s Horizon 2020 research and innovation
programme under grant agreement No 821953.
5. ABBREVIATIONS AND ACRONYMS
AtRems : Atmospheric Remnants
DGM : Detailed Global Model
ET : Electric Thruster
FD : Functioning Diagram
ISRU : In Situ Resources Utilization
L : Plasma length
LMO : Low Mars Orbit
ne : Electron density
nTOT : Total plasma species density
OES : Optical Emission Spectroscopy
p : Pressure
Pabs : Absorbed power
PCC : Plasma Components Composition
QTOT : Total flow rate
R : Plasma radius
Te : Electron temperature
TGAS : Gas temperature
: Total ionization percentage
ij : Wavelength
6. REFERENCES
1. Katsonis, K. & Berenguer, Ch. (2018). The
CO2DGM for CO2 – Breathing Thrusters, EPIC
2018 Workshop, London, UK
2. Katsonis K. & Berenguer, Ch. (2013). Global
Modeling of N2O, air and N2 Discharges and
Applications, Lambert Academic Publishing,
Saarbrucken, Germany
3. Katsonis, K. & Berenguer, Ch. (2013). Global
Modeling of N2O Discharges: Rate Coefficients
and Comparison with ICP and Glow Discharges
Results, International Journal of Aerospace
Engineering 2013, Article ID 737463
4. Katsonis, K. & Berenguer, Ch. (2013). Global
Modeling of N2O Discharges: Helicon Plasma
Thruster Application, International Journal of
Aerospace Engineering 2013, Article ID 467503
5. Berenguer Ch. & Katsonis, K. (2014). Detailed
Global Modeling of Low Pressure Nitrogen
Plasmas, 6th ESA Workshop on Radiation of
High Temperature Gases in Atmospheric Entry,
St. Andrews, UK
6. Katsonis, K., Berenguer, Ch. & Cesaretti, G.
(2020). ISRU Technology Propulsion for
Missions in the Solar System, this Conference
7. Berenguer, Ch. & Katsonis, K. (2014). Global
Modeling of CO2 Discharges with Aerospace
Applications, Advances in Aerospace
Engineering 2014, Article ID 847097
8. Katsonis, K., Berenguer, Ch., Gonzalez del Amo
J. & Stavrinidis, C. (2016). CO2 / N2 Breathing
Electric Thrusters for LMOs, 5th Space
Propulsion Conference, Paper ID
SP2016_3124972, Rome, Italy
9. Berenguer Ch. & Katsonis, K. (2016). A Detailed
Global Model for Characterization of CO2 Fed
Electric Thrusters, Imperial Journal of
Interdisciplinary Research 2, 1708
10. Katsonis, K. & Berenguer, Ch. (2018).
Characterization and Optical Diagnostics of
CO2 Fed Electric Thrusters by Using a Detailed
Global Model, 6th Space Propulsion
Conference, Paper ID SP2018_237, Seville,
Spain
11. Katsonis, K. & Berenguer, Ch. (2018).
Characterization and Optical Diagnostics of
CO2 Fed Electric Thrusters by Using a Detailed
Global Model, 6th Space Propulsion
Conference, Poster, Seville, Spain
12. Berenguer, Ch., Katsonis, K., Herdrich, G. &
Burghaus, H. (2019). A Detailed Global Model
7
AEC2020_525
for Modeling and Optical Diagnostics of Low
Power Propulsion Devices Fed by CO2, 36th
International Electric Propulsion Conference,
IEPC-2019-682, Vienna, Austria
13. Berenguer, Ch. & Katsonis, K. (2018).
Characterization and Optical Diagnostics of Air
– Breathing Electric Thrusters by 4CDGM,
EPIC 2018 Workshop, London, UK
14. Katsonis, K. & Berenguer, Ch. (2019). CO2
based ISRU propulsion for satellites and
spacecrafts near Mars / ISRU-MARS, update of
ResearchGate project : CO2 based ISRU
propulsion for satellites and spacecrafts near
Mars / ISRU-MARS
15. Katsonis, K., Berenguer, Ch., Kaminska, A. &
Dudeck, M. (2011). Argon 4s and 4p excited
states atomic data applied in ARCJET
modeling, International Journal of Aerospace
Engineering 2011, Article ID 896836
16. Berenguer, Ch. & Katsonis, K. (2012). Plasma
Reactors and Plasma Thrusters Modeling by Ar
Complete Global Models, International Journal
of Aerospace Engineering 2012, Article ID
740869
17. Katsonis, K., Bonnet, J., Packan, D., Berenguer,
Ch., Clark, R.E.H., Cornille, M. & Maynard, G.
(2007). A Xenon Collisional-Radiative Model for
Plasma Thruster Optical Diagnostics and
Modeling, 30th International Electric Propulsion
Conference, IEPC-2007-285, Florence, Italy
18. Katsonis, K., Berenguer, Ch., Pavarin, D.,
Trezzolani, F., Manente, M. & Gonzalez del
Amo, J. (2018). A Xenon Detailed Global Model
in Support of Electric Propulsion Technology, 6th
Space Propulsion Conference, Paper ID
SP2018_212, Seville, Spain
19. Katsonis, K., Berenguer, Ch. & Gonzalez del
Amo, J. (2018). An Indium Detailed Global
Model for FEEP Thrusters Characterization and
Optical Diagnostics, 6th Space Propulsion
Conference, Paper ID SP2018_097, Seville,
Spain
20. Katsonis, K., Berenguer, Ch., Pavarin, D. et al.
(2019). Modeling and Optical Diagnostics of
Iodine Fed Helicon Type Thrusters by a
Detailed Global Model (DGM), 36th International
Electric Propulsion Conference, IEPC-2019-
448, Vienna, Austria
21. Katsonis, K. & Berenguer, Ch. (2014).
Characterization of Low Pressure CO2
Plasmas in Space, 6th ESA Workshop on
Radiation of High Temperature Gases in
Atmospheric Entry, St. Andrews, UK
22. Katsonis, K. & Berenguer, Ch. (2016). Study of
CO2 Plasma of Interest to Space Applications
Based on a Detailed Global Model, 7th ESA
Workshop on Radiation of High Temperature
Gases in Atmospheric Entry, Stuttgart,
Germany
23. Berenguer, Ch., Katsonis, K. & Gonzalez del
Amo, J. (2018). Air Breathing Electric Thruster
Characterization and Diagnostics by a Four
Components Detailed Global Model, 6th Space
Propulsion Conference, Paper ID SP2018_345,
Seville, Spain
24. Berenguer, Ch., Katsonis, K., Gonzalez del Amo,
J. & Stavrinidis, C. (2016). Diagnostics of Air-
Breathing Electric Thrusters by Optical
Emission Spectroscopy, 5th Space Propulsion
Conference, Paper ID SP2016_3124973,
Rome, Italy
25. Berenguer, Ch., Katsonis, K. & Gonzalez del
Amo, J. (2018). Using of an Iodine Detailed
Global Model for Characterization and for
Optical Diagnostics of Helicon Thrusters, 6th
Space Propulsion Conference, Paper ID
SP2018_215, Seville, Spain
26. Katsonis, K., Siskos, A. & Touzeau, M. (2003).
Coronal Type and Collisional-Radiative
Modelling of Rare Gases Plasmas, 28th
International Electric Propulsion Conference,
IEPC-2003-285, Toulouse, France
8
