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Characterization and Optical Diagnostics of Air -Breathing Electric Thrusters by 4CDGM

Authors:
Chloe Berenguer at DEDALOS Ltd., Thessaloniki, Greece
Chloe Berenguer
  • DEDALOS Ltd., Thessaloniki, Greece
Konstantinos Katsonis at DEDALOS Ltd., Thessaloniki, Greece
Konstantinos Katsonis
  • DEDALOS Ltd., Thessaloniki, Greece
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Abstract and Figures

♣ 4CDGM is a volume averaged detailed global model of four initial components (O, O2 , N, N2) mixtures, meant to analyze the functioning of space propulsion by Air-Breathing Electric Thrusters (ABET) devices. ♣ 4CDGM allows to foresee the thruster plasma constitution and to diagnose it by Optical Emission Spectroscopy (OES). This model provides Plasma Component Composition (PCC) and Functioning Diagrams (FD) and, simultaneously, theoretical atomic line intensities. ♣ The latter allow for Optical Emission Spectroscopy (OES) diagnostics, with the help of atomic line intensities acquired experimentally.
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Characterization and Optical
Diagnostics of Air – Breathing
Electric Thrusters by 4CDGM
Ch. Berenguer, K. Katsonis
Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
Electric Propulsion Innovation & Competitiveness
EPIC Workshop, 15 -17 October 2018
Ch. Berenguer, Project Manager,
DEDALOS Ltd.,
Vass. Olgas 128, 54645 Thessaloniki, Greece
berenguer.dedalos@gmail.com
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
Abstract
♣ 4CDGM, a four initial components (O, O2 , N,
N2) is a volume averaged detailed global model
meant to analyze the functioning of Electric
Thrusters (ET) of Air-Breathing Electric
Thrusters (ABET) type, to foresee the plasma
constitution and to diagnose it by Optical Emission
Spectroscopy (OES)
♣ Towards this aim, 4CDGM provides Plasma
Component Composition (PCC), Functioning
Diagrams (FD) and theoretical atomic line
intensities with the adequate model allowing for
Optical Emission Spectroscopy (OES) diagnostics
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
Following 1. Introduction, results of 4CDGM are
presented consisting of :
2. Density of species, containing PCC and
concomitant diagrams
3. A pressure depending FD
4. Typical oxygen & nitrogen theoretical emission
spectra, leading to Optical Emission Spectroscopy
(OES) diagnostics
5. Conclusions
Summary of Presentation
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
1. Introduction (1/3)
♣ Disruptive ET propulsion technology based on In
Situ Resources Utilization (ISRU) for propellant to be
used by ET, developed for Low Earth Orbit (LEO)
satellites maintenance and for orbit raising is supported
by 4CDGM. It is also of interest to Very Low Earth
Orbit (VLEO) satellites and to propulsion of very low
flying s/c of various types. Whenever the breathed
propellant is conveniently stored, ABET technology
may also serve for extended space traveling.
♣ The four components addressed here are the main
atomic and molecular constituents of the Atmospheric
Remnants (AtR) in about 180 km altitude (50.1 % O /
47.5 % N2 / 2.16 % O2 / 0.28 % N).
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
REFERENCES
1. Katsonis, K. & Berenguer, Ch. (2014). Properties of the Atmospheric Mixtures
Prevailing Around 200 km Altitude in Conditions of Low Absorbed Power and
Pressure. ESA 6th RHTG Works. St. Andrews, UK
2. Katsonis, K., Berenguer, Ch., Gonzalez del Amo, J. & Stavrinidis, C. (2015).
Atmospheric Remnants in the Low Earth Orbit Region around 200 km Altitude.
World Journal of Engineering and Technology 3, 26
3. Katsonis, K., Berenguer, Ch. & Gonzalez del Amo, J. (2015). Characterization of
Air Breathing Plasma Thrusters Fueled by Atmospheric Mixtures Encountered in
Earth Atmosphere at an Altitude of About 200 km. 34th IEPC Conference. IEPC-
2015-268, Kobe, Japan
4. Stavrinidis, C., Gonzalez del Amo, J., Berenguer, Ch. & Katsonis, K. (2015).
Diagnostics of Air-Breathing Electric Thrusters. World Journal of Engineering and
Technology 3, 33
5. Berenguer, Ch., Katsonis, K., Gonzalez del Amo, J. & Stavrinidis, C. (2016).
Diagnostics of Air-Breathing Electric Thrusters by Optical Emission Spectroscopy,
Space Propulsion Conference, Paper ID SP2016_3124973, Rome, Italy, May 2016
6. Berenguer, Ch. & Katsonis, K. & Gonzalez del Amo J. (2018). Air Breathing
Electric Thrusters Characterization and Diagnostics by a Four Components Detailed
Global Model, 6th Space Propulsion Conference, Paper ID SP2018_00345, Seville,
Spain; Summary presentation in Poster.
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
1. Introduction (2/3)
♣ OES diagnostics pertains here to plasma containing
neutral / ionized species created in case of ETs fed by
AtR. In order to better tackle OES diagnostics, extended
sets of nitrogen and of oxygen data encompassing the
main N I to III, O I to III levels, had been included in
4CDGM.
♣ Electron temperature Te , pressure p and absorbed
power PABS , are the main parameters present in the PCCs
diagrams giving the plasma composition with FD giving
the plasma ionization percentage for the propellant feed
which contains iso-thermal, iso-energetic and iso-baric
curves.
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
1. Introduction (3/3)
♣ We consider typical AtR propellant constitution
encountered in about 180 km altitude. 4CDGM results
corroborate our conjecture for feeding by an adequate
O2 / N2 mixture instead of the cumbersome AtR one,
without relying on cumbersome hyperthermal atomic
oxygen O and molecular nitrogen N2 beams.
♣ Results pertaining to O2 / N2 mixture to be used in
case of preparation, diagnostics and evaluation of on
ground ABET experiments, were presented previously
in [3 - 6].
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
Fig. 1.
Pabs= 500 W
pressure
dependent PCC
AtR feed of 20
sccm, form factor
of
R=2 cm, L=18 cm
throughout
2. Density of
Species PCC
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
Fig. 2.
Pabs= 200 W
pressure
dependent PCC
AtR feed of 20
sccm, form factor
of
R=2 cm, L=18 cm
2. Density of
Species PCC
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
Fig. 3. Concomitant of Fig. 1
2. Density of
Species PCC
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
Fig. 4. Concomitant of Fig. 2
2. Density of
Species PCC
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
Fig. 5.
FD for PABS=
200 W &
400 W
N2, O2, N2/O2,
AtR, Te = 5 eV
& 10 eV,
form factor
as before
3. Functioning
Diagram, FD
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
4. Theoretical spectra, OES
Fig. 6. AtR, theoretical O I spectrum for PABS= 500 W
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
4. Theoretical spectra, OES
Fig. 7. AtR, theoretical O II spectrum for PABS= 500 W
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
4. Theoretical spectra, OES
Fig. 8. AtR, theoretical O I spectrum for PABS= 500 W
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
4. Theoretical spectra, OES
Fig. 9. AtR, theoretical O II spectrum for PABS= 500 W
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
4. Theoretical spectra, OES
Fig. 10. AtR, theoretical O I spectrum for PABS= 1 kW
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
4. Theoretical spectra, OES
Fig. 11. AtR, theoretical O II spectrum for PABS= 1 kW
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
4. Theoretical spectra, OES
Fig. 12. AtR, theoretical N I spectrum for PABS= 500 W
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Data Evaluations and Diagnostics Algorithms Of Systems EPIC Oct '18
5. Conclusions
♣ 4CDGM allows for ET feeding by an adequate O2 / N2
mixture on ground, to replace the cumbersome AtR one. It
leads to experimental results equivalent to those obtainable by
AtR feeding. Such a mixture can be used for preparation and
diagnostics of on ground ABET experiments.
♣ Plasma containing neutral and ionized species created in
case of ETs fed by AtR allow for OES.
♣ After including in 4CDGM extended sets of nitrogen and of
oxygen data, encompassing the main N I – III and O I – III
levels, better description of the atomic and molecular structure
effects and of the chemical reactions was obtained. It allows
for detailed calculation of theoretical spectra to be used in
OES diagnostics.
21
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Characterization of Air Breathing Plasma Thrusters Fuelled by Atmospheric Mixtures Encountered in Earth Atmosphere at an Altitude of About 200 km
Conference Paper
Full-text available
  • Jul 2015
Global modeling is used here to characterize various types of electric plasma thrusters, fuelled mainly by the atmospheric remnants encountered in about 200 km Earth altitude. Ground experimental devices meant to simulate thrusters functioning in space conditions are addressed by this modeling. Considered feeding includes up to five species (O, N2 , O2 , N and Ar) and their mixtures. Nomenclature 4CGM = Four Components Global Model 5CArGM = Five Components Global Model (including Ar) C,X = Collisional energy loss of the electrons, colliding with species X TOT = Total ionization percentage ABET = Air Breathing Electric Thruster ABIE = Air Breathing Ion Engine Aeff = Area for effective losses CDF = Concurrent Design Facility C-RM = Collisional-Radiative Model EP = Electric Propulsion ESA = European Space Agency ET = Electric Thruster FD = Functioning Diagram GIE = Grid Ion Engine GM = Global Model HET = Hall Effect Thruster HHT = Helicon Hall Thruster HPT = Helicon Plasma Thruster ICP = Inductively Coupled Plasma ISRU = In Situ Resources Utilization kj = Rate coefficient of the process j 1 L = Plasma length LEO = Low Earth Orbit met = Metastable component ne = Electron density ni = Density of the species i nions = Total density of positive ions nTOT = Total plasma species density OES = Optical Emission Spectroscopy p = Pressure PaBE = Particle Balance Equation Pabs = Absorbed Power PCC = Plasma Components Composition PiC = Particle in Cell PoBE = Power Balance Equation QTOT = Total flow rate R = Plasma radius RAM-EP = RAM type Electric Propulsion RIT = Radio-frequency Ionization Thruster T e = Electron temperature TGAS = Temperature of neutrals TOF = Time of Flight u B,X+ = (eT e / M) 1/2 , Bohm velocity of the ion X + V = Discharge volume XTOT = Total density of species X including excited ones
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Air Breathing Electric Thrusters Characterization and Diagnostics by a Four Components Detailed Global Model
Conference Paper
  • May 2018
A four components detailed global model, with Earth atmosphere remnants (nitrogen and oxygen mixtures in atomic and molecular form) as initial components, is used to study the functioning of air-breathing electric thrusters. The latter are of interest to both low and high Earth orbit satellites and to space missions. Theoretical characterization of air-breathing thrusters is based here on recent results obtained by our model. They are presented by means of plasma components diagrams giving the plasma composition as a function of pressure or of absorbed power. Functioning diagrams are also presented, containing isothermal, isobaric and iso-energetic curves, obtained by the detailed global model and giving ionization percentages of the plasma components. Results are with pressure or of absorbed power as ordinate. Detailed structure and reaction data of N and O species and of N2 , O2 molecules composed from them, including their ions are contained in the model. These data, besides to the global modeling results of the thruster, lead to evaluation of main spectral lines intensity of neutral, singly and doubly ionized nitrogen and oxygen species and allows for optical emission spectroscopy diagnostics.
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