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ISRU TECHNOLOGY PROPULSION FOR MISSIONS IN THE SOLAR SYSTEM
Abstract
Following the development of the space electric propulsion, using of various propellants to be collected in the region where the mission is intended has been actively sought. Here we address such a technology for Solar System missions, focusing on the Earth and on the Mars vicinity with nitrogen/oxygen mixtures and CO2 as propellants correspondingly. The adequate Detailed Global Models, 4CDGM in case of using N2, N, O2 and O mixtures as propellant and CO2DGM in case of using CO2 have been extensively applied, allowing for theoretical evaluation of the considered thrusters functioning and for optical emission spectroscopy insuring their diagnostics and monitoring.
... Using of CO2 as Electric Thruster (ET) propellant is of interest to propulsion of satellites and spacecrafts in the vicinity of stellar bodies possessing atmospheres composed mainly of this molecule. Thus, CO2 fueled ETs are considered for propulsion near Mars and Venus following In Situ Resources Utilization (ISRU) technology for satellites and spacecrafts [1]. CO2DGM, a Detailed Global Model (DGM) developed by DEDALOS Ltd specifically for CO2 fed ETs of various types, can be used for theoretical characterization and non-perturbing Optical Emission Spectroscopy (OES) diagnostics of prototypes developed for on ground experiments [2,3] increasing the TRL number prior to the IOD and IOV steps. ...
... Obtained theoretical spectra of O I, O II and C I, C II, necessary for OES diagnostics, are here presented and commented. In order to thoroughly support OES diagnostics, extended sets of data concerning the neutral and the singly, doubly and trebly ionized oxygen species have been specifically included in the DGM basic equations [1]. The latter consist of a "power balance" equation plus the well-known "statistical equations" set addressing the main plasma species. ...
... Description of CO2DGM model is not given here. The model fundamentals, allowing for the important ISRU support of ETs provided by this type of modeling and by the concomitant OES diagnostics, have been described elsewhere [1]. In Section 2 of this contribution, the composition and the properties of plasma created from CO2 in various conditions which are primarily of interest to propulsion in the Mars and Venus vicinities are investigated. ...
The CO2DGM detailed global model is used to characterize electric thrusters breathing CO2. The latter are of interest to Mars and Venus artificial satellites and spacecraft propulsion in their vicinity. CO2DGM results are illustrated by diagrams giving the composition of the plasma components and ionization percentages containing isothermal, isobaric and isoenergetic curves which describe the thruster functioning for various regimes. The model incorporates data concerning detailed structure and reactions involving oxygen and carbon species and molecules composed from them, including their ions. Thus, spectral lines intensity of the main thruster constituents is obtained, allowing for optical emission spectroscopy diagnostics.
... Theoretical spectra obtained by 4CDGM belonging to the quite ionized plasma examined in Section 2 in case of an absorbed power of 2.5 kW belonging to the PCC of the Fig. 1 are presented and discussed in this section. It is possible to choose between neutral oxygen and nitrogen atoms spectra and the spectra of their ions as a basis of OES, as was reported previously [7,[9][10][11]. In general, the best basis choice is the most abundant species in the chosen conditions. According to Fig. 2, for Pabs = 2.5 kW the densities of N and N + are to be preferred for OES than those of O and O + for the addressed pressure values. ...
The use of the Earth atmosphere remnants in various altitudes as electric thruster propellant in an ISRU scheme is addressed, with the well known Four Component {N, N2, O, O2} Detailed Global Model 4CDGM as basic tool. The model is applied in theoretical characterization of various types of electric thrusters fuelled by Earth atmospheric remnants. It also allows to evaluate the necessary O2 / N2 ratios to be used in fuelling of prototype thrusters when seeking simulation of their functioning in space with atmospheric remnants encountered in various altitudes. Moreover, non-intrusive diagnostics of thruster plasma when fed by atmospheric remnants, which is also supported by 4CDGM is also addressed.
... Moreover, to widen the application cases of atmosphere-breathing propulsion, characteristics of inner and of outer planets atmospheres and of natural satellites have been addressed. Towards this aim, the existing DEDALOS proprietary 4 Components Detailed Global Model (4CDGM) code has been used [18], together with an analogous Detailed Global Model (DGM) applicable to the case of Venus and Mars [19][20][21]. ...
The possibility of efficiently exploiting Very Low Earth orbits (VLEO) poses significant technological challenges. One of the most demanding constraints is the need to counteract the drag generated by the interaction of the spacecraft with the surrounding atmosphere. Funded by the European Commission under the H2020 programme, the Air-breathing Electric THrustER (AETHER) project aims at developing the first propulsion system able to maintain a spacecraft at very-low altitudes for an extended time. The main objective of the project is to demonstrate, in a relevant environment, the critical functions of an air-breathing electric propulsion system, and its effectiveness in compensating atmospheric drag. This achievement will involve multiple research activities, among which: (i) the characterization of specific application cases through an extensive market analysis in order to define specific requirements and constraints at different design levels, (ii) fulfilment of pertinent testing conditions of flight conditions on-ground, relevant to the specific mission cases, (iii) the development of critical technologies, in particular those relevant to the collection, the ionization and the acceleration of rarefied atmospheric mixtures and (iv) the testing of the RAM-EP thruster to assess the system performance. In this paper, the main activities foreseen in the AETHER project are described, providing the detailed perspective towards an effective exploitation of the project outcomes for a possible future in-orbit demonstration.
In Situ Resource Utilization (ISRU) propulsion technology aiming to support missions in various regions of the Solar System, avoids or minimizes all of the difficulties related with the propellant transport. CO2, the main constituent of Mars ATMosphere (MATM) and of Venus ATMosphere (VATM) is considered here as Electric Thruster (ET) propellant for satellite propulsion in Low Mars Orbits (LMO), in Very Low Mars Orbits (VLMO) and in Venus Orbits (VO) and also for s/c propulsion in their vicinity. Propulsion of artificial satellites around Phobos and Deimos, the natural satellites of Mars, is also addressed.
CO2DGM is a Detailed Global Model (DGM) leading to characterization of CO2-fed Electric Thrusters (ET). Low pressure values from 1 mTorr to 10 mTorr are tackled, with a standard feed of 40 sccm.
Disruptive In Situ Resource Utilization (ISRU) technology is addressed.-Besides an improved functioning insight, essentials of Optical Emission Spectroscopy (OES) diagnostics and monitoring are provided by CO2DGM.
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 various Solar System (SSys) missions, related e.g. to Mars and Venus.
A Detailed Global Model developed by DEDALOS Ltd for CO2 plasma study in space and laboratory is used here for electric thruster characterization and optical emission spectroscopy diagnostics based on the obtained plasma components composition diagrams, on the functioning diagrams and on the concomitant theoretical first and second oxygen and carbon spectra. Comparison of our theoretical results including theoretical spectra with experimental ones obtained in IRS, is addressed in particular, taking into consideration that the experimental spectra do not come from a thruster but from a IPG run with CO2 for Mars entry investigation.
Nomenclature xTOT = total ionization percentage ABET = Air Breathing Electric Thruster CO2DGM = CO2 Detailed Global Model DEDALOS = Data Evaluation and Diagnostics ALgorithms Of Systems Ltd DGM = Detailed Global Model ET = Electric Thruster FD = Functioning Diagram GM = Global Model HelT = Helicon type Thruster HMO = High Mars Orbit IPG = Inductively heated Plasma Generator IRS = Institut für RaumfahrtSysteme, university of Stuttgart ISRU = in situ Resource Utilization L = cylinder lenght LMO = Low Mars Orbit MATM = Mars ATMosphere ne = electron density 1 Project Manager, berenguer. 1 NMT = Near Mars Trips OES = Optical Emission Spectroscopy p = pressure PABS = absorbed power PCC = Plasma Components Composition QTOT = total flow rate R = cylinder radius Te = electron temperature ThSpec = theoretical spectra VLMO = Very Low Mars Orbit
A thorough study of low density argon plasmas which are not in local thermodynamic equilibrium is made, including evaluation of the necessary data for constituting the Collisional-Radiative model used. A sufficient number of states is considered, allowing for spectroscopic diagnostics of low power argon plasmas and highly excited levels are conveniently simulated.
Detailed properties of O and of O+ species have been included in our CO2 Global Model in order to better characterize CO2 fed electric thrusters. This addition allows also for optical emission spectroscopy diagnostics pertaining to CO2 propellant. The obtained model, CO2GM, is applied to electric thrusters functioning at low pressure values, typically from 1 mTorr to 5 mTorr. The thruster characterization and diagnostics are addressed. CO2+ is found to be the most abundant ionic species, followed by CO+ and O+. Dominant reaction is dissociation of CO2 resulting to CO and O production, leading also to considerable ionization. Obtained theoretical spectra of O and O+ are also presented.
Air-Breathing Electric Thrusters (ABET) diagnostics is addressed, with on-ground prototypes in mind. It is based on detailed volume averaged Global Models and focuses on emission spectroscopy. Notably, the obtained optical emission spectroscopy diagnostics tools give important information about the thruster propellant constitution and also the ionization degree of each constituent. This allows for trade-off between various prototypes on the basis of their characterization and optimization.
Study of atmospheric remnants in the low Earth orbit region (~200 km altitude) using Global Models, with application to electric thrusters of in situ resources utilization type.
Atmospheric Remnants in the Low Earth Orbit Region around 200 km Altitude. Available from: https://www.researchgate.net/publication/283345841_Atmospheric_Remnants_in_the_Low_Earth_Orbit_Region_around_200_km_Altitude [accessed Aug 15, 2017].
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
We developed a Global Model for N2O plasmas valid for applications in various power, gas flow rate, and pressure regimes. Besides energy losses from electron collisions with N2O, it takes into consideration those due to molecular N2 and O2 and to atomic N and O species. Positive atomic N+ and O+ and molecular N2O+, , and have been treated as separate species and also negative O− ions. The latter confer an electronegative character to the discharge, calling for modified plasma sheath and plasma potential formulas. Electron density and temperature and all species densities have been evaluated, hence the ionization and dissociation percentages of N2O, N2, and O2 molecules and the plasma electronegativity. The model is extended to deal with N2/O2 mixtures feedings, notably with air. Rate coefficients and model results are discussed and compared with those from available theoretical and experimental work on ICP and glow discharge devices.
Evaluated atomic data concerning the 4s and 4p configurations of Ar I are averaged in order to simplify their use in various cases of Ar plasma modeling and diagnostics. These data are used here to model a low-power arcjet, running with Argon at low pressure. In so doing, they are explicitly introduced in the chemical processes included in a fluid Navier-Stokes type code, allowing for evaluation of the spectroscopically measurable level populations and of the electronic temperatures. The characteristics of the model are described and the main processes are discussed in view of the results of the calculations.
Particle densities of helium atoms in the ground and excited states were
calculated for non-LTE plasmas on the basis of a collisional-- radiative model in
which singlet aad triplet states were separately taken into account. Distinction
is made between two physical situations: 1) a homogeneous stationary state, 2) a
transient and/or inhomogeneous plasma state. In both cases, the particle
densities were calculated for an optically thin, a slightly optically thick, and
strongly absorbing plasmas. Only the results for the homogeneous stationary
state are presented. Those for the transient and/or inhomogeneous states have
been summarized in numerical tables. The tables are sufficiently complete to
permit a wide application in the field of spectroscopic diagnostics of different
types of non-LTE plasmas. (GE)
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.
A Global (volume averaged) Model (GM) conceived for modeling of discharges fed by N2O and by N2 / O2 mixtures including 4:1 [N2]:[O2] air-like ones, is applied to plasma discharges and to electric propulsion devices in case of pure N2O and of N2 / O2 feeding. The main results obtained by this model allowing to characterize the central “core” region part of Helicon Thrusters (HelT) are presented and discussed. Functioning is restricted in a rather low pressure region, of 3 mTorr up to 30 mTorr. The absorbed power in the “core” region introduced here is varying from 25 W up to 1000 W. Note that both pressure and power ranges have been here enlarged in comparison with previous values treating an Ar fed HelT which spanned only a 2 mTorr to 10 mTorr region for the pressure and 25 W to 150 W for the absorbed power. Various types of thrusters are examined on the basis of Functioning Diagrams (FD) and the plasma composition is given by Plasma Components Composition (PCC) results.
Characterization and Optical Diagnostics of Air -Breathing Electric Thrusters by 4CDGM
- Ch Berenguer
- K Katsonis
Berenguer, Ch. & Katsonis, K. (2018).
Characterization and Optical Diagnostics of
Air -Breathing Electric Thrusters by 4CDGM,
EPIC 2018 Workshop, London, UK
Diagnostics of ABET by optical emission spectroscopy
- Ch Berenguer
- K Katsonis
- J Gonzalez Del Amo
- C Stavrinidis
Berenguer, Ch., Katsonis, K., Gonzalez del
Amo, J. & Stavrinidis, C. (2016). Diagnostics
of ABET by optical emission spectroscopy,
Poster, 5 th Space Propulsion Conference,
Rome, Italy
Characterization and Optical Diagnostics of CO2 Fed Electric Thrusters by Using a Detailed Global Model, 6 th Space Propulsion Conference
- K Katsonis
- Ch Berenguer
Katsonis, K. & Berenguer, Ch. (2018).
Characterization and Optical Diagnostics of
CO2 Fed Electric Thrusters by Using a
Detailed Global Model, 6 th Space Propulsion
Conference, Paper ID SP2018_237, Seville,
Spain
Detailed Global Modeling of Low Pressure Nitrogen Plasmas, 6 th ESA Workshop on Radiation of High Temperature Gases in Atmospheric Entry
- Berenguer Ch
- K Katsonis
Berenguer Ch. & Katsonis, K. (2014). Detailed
Global Modeling of Low Pressure Nitrogen
Plasmas, 6 th ESA Workshop on Radiation of
High Temperature Gases in Atmospheric
Entry, St. Andrews, UK
Using of Detailed Global Models, update of ResearchGate project : ISRU Based Electric Propulsion
- K Katsonis
- Ch Berenguer
Katsonis, K. & Berenguer, Ch. (2016). Using of
Detailed Global Models, update of
ResearchGate project : ISRU Based Electric
Propulsion
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
- K Katsonis
- Ch Berenguer
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
Collisional-Radiative Modeling for Diagnostics and Modeling of Plasma Thrusters, 2 d Space Propulsion Conference
- K Katsonis
- Ch Berenguer
Katsonis, K. & Berenguer, Ch. (2010).
Collisional-Radiative Modeling for Diagnostics
and Modeling of Plasma Thrusters, 2 d Space
Propulsion Conference, San Sebastian, Spain
28. 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
A set of Functioning Diagrams and Plasma Component Compositions for Air Breathing Thrusters Modeling and Diagnostics
- K Katsonis
- Ch Berenguer
Katsonis, K. & Berenguer, Ch. (2014). A set of
Functioning Diagrams and Plasma
Component Compositions for Air Breathing
Thrusters Modeling and Diagnostics, Tech.
Report DEDALOS DE-2014-01, Thessaloniki,
Greece