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Löb, Horst; Freisinger, J.

doi:10.1007/978-3-663-07265-2

Cited by 8 publications

(4 citation statements)

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“…A divergence angle of θ g = 60 • can be assumed based on Keller et al [3], and this is supported by the measured divergence angle of 56 • of the DCFT by Matlock [17]. The divergence efficiency can be defined by Löb and Freisinger [18] by…”

Section: Methodsmentioning

confidence: 99%

“…For mass utilization efficiency, the study allows for the presence of 20% doubly charged ions, resulting in a correction factor of α m = 0.9 from Equation (9). The plume divergence efficiency is based on an assumed divergence angle of 60 • [3,18]. The acceleration efficiency requires significant measurement of the CFT, which is beyond the scope of this study.…”

Section: Sensitivity Analysismentioning

confidence: 99%

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High Fidelity Multi-Objective Design Optimization of a Downscaled Cusped Field Thruster

Fahey

Muffatti²,

Ogawa

2017

Aerospace

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The Cusped Field Thruster (CFT) concept has demonstrated significantly improved performance over the Hall Effect Thruster and the Gridded Ion Thruster; however, little is understood about the complexities of the interactions and interdependencies of the geometrical, magnetic and ion beam properties of the thruster. This study applies an advanced design methodology combining a modified power distribution calculation and evolutionary algorithms assisted by surrogate modeling to a multi-objective design optimization for the performance optimization and characterization of the CFT. Optimization is performed for maximization of performance defined by five design parameters (i.e., anode voltage, anode current, mass flow rate, and magnet radii), simultaneously aiming to maximize three objectives; that is, thrust, efficiency and specific impulse. Statistical methods based on global sensitivity analysis are employed to assess the optimization results in conjunction with surrogate models to identify key design factors with respect to the three design objectives and additional performance measures. The research indicates that the anode current and the Outer Magnet Radius have the greatest effect on the performance parameters. An optimal value for the anode current is determined, and a trend towards maximizing anode potential and mass flow rate is observed.

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Section: Methodsmentioning

confidence: 99%

Section: Sensitivity Analysismentioning

confidence: 99%

High Fidelity Multi-Objective Design Optimization of a Downscaled Cusped Field Thruster

Fahey

Muffatti²,

Ogawa

2017

Aerospace

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“…These include the electron-bombardment engines, developed by Kaufman; the radio frequency ion engines, developed by Löb; and the stationary plasma thruster (SPT, also known as Hall Thrusters), developed by Morozov. [27][28][29][30][31][32] The development of space travel has always been and still is a reflection of the technical possibilities of the respective epoch and always is connected with scientific, political, military, and economic objectives. After the race in space had ended with the moon landing of the Americans at the time of the Cold War, civil, i.e., commercial and scientific interests of space travel began to develop in addition to the military one.…”

Section: From the Beginnings Of Space Travel To The All-ep System A B...mentioning

confidence: 99%

“…Here, m d stands for the dry mass of the satellite (without propellant), m 0 stands for the total mass of the satellite (including all propellants), and Δv stands for the change in velocity, which can be achieved by mass ejection with an exhaust velocity vex. According to Löb, the exhaust velocity of chemical fuels depends theoretically only on the energy yield ω, i.e., the ratio of the enthalpy change Hp during combustion and the rest energy of the propellant, 31 ω = Hp mpc 2 .…”

Section: From the Beginnings Of Space Travel To The All-ep System A B...mentioning

confidence: 99%

Ion thrusters for electric propulsion: Scientific issues developing a niche technology into a game changer

Holste

Dietz

Scharmann

et al. 2020

Review of Scientific Instruments

136

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The transition from OLD SPACE to NEW SPACE along with increasing commercialization has a major impact on space flight, in general, and on electric propulsion (EP) by ion thrusters, in particular. Ion thrusters are nowadays used as primary propulsion systems in space. This article describes how these changes related to NEW SPACE affect various aspects that are important for the development of EP systems. Starting with a historical overview of the development of space flight and of the technology of EP systems, a number of important missions with EP and the underlying technologies are presented. The focus of our discussion is the technology of the radio frequency ion thruster as a prominent member of the gridded ion engine family. Based on this discussion, we give an overview of important research topics such as the search for alternative propellants, the development of reliable neutralizer concepts based on novel insert materials, as well as promising neutralizer-free propulsion concepts. In addition, aspects of thruster modeling and requirements for test facilities are discussed. Furthermore, we address aspects of space electronics with regard to the development of highly efficient electronic components as well as aspects of electromagnetic compatibility and radiation hardness. This article concludes with a presentation of the interaction of EP systems with the spacecraft.

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Ionentriebwerke Zukunftsantrieb für Satelliten

1993

Physik in unserer Zeit

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Ionenraketen

Cited by 8 publications

References 0 publications

High Fidelity Multi-Objective Design Optimization of a Downscaled Cusped Field Thruster

High Fidelity Multi-Objective Design Optimization of a Downscaled Cusped Field Thruster

Ion thrusters for electric propulsion: Scientific issues developing a niche technology into a game changer

Ionentriebwerke Zukunftsantrieb für Satelliten

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