Review of alternative propellants in Hall thrusters

Tirila, Vlad-George; Demairé, Alain; Ryan, Charles

doi:10.1016/j.actaastro.2023.07.047

Cited by 12 publications

(7 citation statements)

References 92 publications

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“…One of the principal problems raised in plasma technology, such as Hall-effect thrusters, is the validity of the WFA formulas (17) for magnetic fields of tens of mT. Strictly speaking, the calculations for the transitions of the 83 Kr isotope exhibit a difference in the intensity distribution of components between the exact calculation and the WFA for the magnetic field of 22.5 mT and 45 mT.…”

Section: Discussionmentioning

confidence: 99%

“…The probably most relevant current research topic, where xenon and krypton spectra contain invaluable information under magnetic field strengths comparable to those investigated in this study, is spacecraft propulsion [17]. Obtaining high thrust while keeping the associated mass loss low represents a high priority.…”

Section: Introductionmentioning

confidence: 87%

“…Obtaining the correct energy splitting and relative intensities using WFA formulas is essentially a two-step procedure: Firstly, the zero-field splitting is calculated, as shown by the red bars in figure 2(a), via equations ( 9), (11), and (12). Secondly, each hyperfine sub-transition splits into its weak field pattern, where equations ( 15) and ( 16) give the energy splitting, and equation (17) provides their relative intensities.…”

Section: Strong Field Regimementioning

confidence: 99%

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Zeeman effect of isotopes of Kr and Xe investigated at the linear plasma device PSI-2

Sackers,

Marchuk,

Dipti

et al. 2024

Plasma Sources Sci. Technol.

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Laser absorption spectroscopy provides high-resolution spectra of atomic transitions that reveal many often inaccessible features. The line shapes of krypton and xenon measured in magnetized plasmas are strongly affected by the contribution of the odd-numbered isotopes 83Kr, 129Xe and 131Xe due to their hyperfine structure, creating more challenging spectra in comparison to even-numbered ones. The lines originating from metastable levels of krypton and xenon with J = 2 (Kr I 760.4 nm) and J = 0 (Kr I 785.7 nm, Xe I 764.4 nm) were measured and analyzed in the linear plasma device PSI-2 in the field range of 22.5 mT to 90 mT. Evaluating the Hamiltonian, including hyperfine and Zeeman interaction terms for these magnetic field strengths, unveils a deviation from the linear energy shift of the sublevels as a function of the magnetic field and from constant relative intensities that the weak field formulas provide. We prove that modeling the transitions in Xe using the weak field approximation, frequently used in magnetized plasma, becomes inadequate at ≈50 mT. In particular, the spectra of the 131Xe isotope show pronounced deviations from the weak field results. For krypton, however, the situation is less critical compared to xenon due to the low natural abundance of the odd-numbered isotope.

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Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 87%

Section: Strong Field Regimementioning

confidence: 99%

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Zeeman effect of isotopes of Kr and Xe investigated at the linear plasma device PSI-2

Sackers,

Marchuk,

Dipti

et al. 2024

Plasma Sources Sci. Technol.

View full text Add to dashboard Cite

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“…The development and evolution of propulsion systems for space exploration have been well documented in recent decades, with a rich body of literature covering a wide array of propulsion technologies. From the early days of rocketry, characterized by the pioneering work of Goddard, Oberth, and Tsiolkovsky [3][4][5], to the modern era of ion thrusters and Hall effect engines [6][7][8][9], the quest for more efficient and reliable propulsion methods has been a constant theme in aerospace engineering research.…”

Section: Related Workmentioning

confidence: 99%

Optimizing Propellant Distribution for Interorbital Transfers

De Curtò,

De Zarzà

2024

Mathematics

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The advent of space exploration missions, especially those aimed at establishing a sustainable presence on the Moon and beyond, necessitates the development of efficient propulsion and mission planning techniques. This study presents a comprehensive analysis of chemical and electric propulsion systems for spacecraft, focusing on optimizing propellant distribution for missions involving transfers from Low-Earth Orbit (LEO) to Geostationary Orbit (GEO) and the Lunar surface. Using mathematical modeling and optimization algorithms, we calculate the delta-v requirements for key mission segments and determine the propellant mass required for each propulsion method. The results highlight the trade-offs between the high thrust of chemical propulsion and the high specific impulse of electric propulsion. An optimization model is developed to minimize the total propellant mass, considering a hybrid approach that leverages the advantages of both propulsion types. This research contributes to the field of aerospace engineering by providing insights into propulsion system selection and mission planning for future exploration missions to the Moon, Mars, and Venus.

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“…Based on the impulse maneuver theory, he found the inclination boundaries for RAAN reconfiguration of different orbital planes: for high inclination orbits, RAAN separation is achieved by using inclination separation; for medium and low inclination orbits, RAAN separation is achieved by using orbital semi-major axis separation. It is necessary to note that, with the development of space electric propulsion, the thrust of electric propulsion can be up to 3 mN–1 N, and the specific impulse can be up to 800–3000 s [ 20 , 21 ]. using continuous thrust to directly change the satellite orbit plane of the RAAN can save a lot of time, but the corresponding energy consumption is pending to be explored.…”

Section: Introductionmentioning

confidence: 99%

Deployment of Constellation with Different Inclinations Using the Nodal Precession and Thrust

Zhao,

Zhu,

Tao

et al. 2024

Sensors

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Strategy selection is critical for constellation deployment missions, both in terms of energy consumption and time cost. The different effects of impulse thrust and continuous thrust on orbit elements lead to a different choice of strategy. With impulse thrust, constellation types are differentiated according to high and medium-low inclinations. Constellations with high inclination are deployed using a strategy that controls the inclination. Constellations with medium-low inclination are deployed using a strategy that controls the semi-long axis. With continuous thrust, constellations are classified according to high, medium, and low inclination. High inclination constellations are deployed with a strategy of controlling inclination. Medium inclination constellations are deployed with a strategy that controls the semi-long axis. Low inclination constellations are deployed with a strategy of directly applying continuous thrust.

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Review of alternative propellants in Hall thrusters

Cited by 12 publications

References 92 publications

Zeeman effect of isotopes of Kr and Xe investigated at the linear plasma device PSI-2

Zeeman effect of isotopes of Kr and Xe investigated at the linear plasma device PSI-2

Optimizing Propellant Distribution for Interorbital Transfers

Deployment of Constellation with Different Inclinations Using the Nodal Precession and Thrust

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