Fundamentals of Electric Propulsion

Goebel, Dan M.; Katz, Ira

doi:10.1002/9780470436448

Cited by 1,122 publications

(636 citation statements)

References 58 publications

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“…Assuming the ions to be predominantly singly charged, the thrust parameters can be estimated using the standard relations 3) . Taking the case of Config.…”

Section: Experimental Observationsmentioning

confidence: 99%

“…Use of electric propulsion for such operations presents an attractive alternative due to their low fuel requirement and higher specific impulse. [1][2][3] Therefore, the development and understanding of compact low power electric propulsion systems is an active area of research. Among the various electric thrusters currently operational, ion thrusters provide the highest efficiency and specific impulse.…”

Section: Introductionmentioning

confidence: 99%

“…The antenna length (AL) is also variable, and is measured from SB. The overall dimension of the ion thruster is ~ 50 × 50 × 50 mm 3 . For the current experiment, CL ~ 24 mm, and AL ~ 20 mm.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Development of a Low Power Multipole Confined Microwave Plasma Ion Thruster

Dey

Toyoda

Hirano

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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A modified magnetic multipolar plasma source is developed and tested for application as an ion thruster for space propulsion. The configuration consists of eight samarium-cobalt bar-magnets, symmetrically surrounding a cylindrical discharge volume of 21 mm diameter, with their magnetization in the radial direction. A donut magnet is placed at one axial end of the discharge volume with its magnetization along the cylindrical axis. A short monopole antenna, coaxial with the donut magnet is used for launching microwaves in the discharge volume. The resulting magnetic configuration due to the radial and axial magnetic fields, help in generation and sustenance of microwave induced electron cyclotron resonance plasma. Ions are extracted from the plasma by high voltage grids, attached to the end, opposite to the donut magnet. Two different magnetic configurations obtained by reversing the magnetization direction of the donut magnet are compared. Three dimensional magnetic field simulations and ion saturation current measurements at various microwave frequencies are used to determine the optimum magnetic configuration. Ion beam current extraction measurements, using the grids is carried out. Typical ion beam current of 9.9 mA is obtained, with calculated thrust of 0.63 mN at 8 W for 1600 MHz, with a Xenon mass flow rate of 20 g/s.

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“…Assuming the ions to be predominantly singly charged, the thrust parameters can be estimated using the standard relations 3) . Taking the case of Config.…”

Section: Experimental Observationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Development of a Low Power Multipole Confined Microwave Plasma Ion Thruster

Dey

Toyoda

Hirano

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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“…This consideration of mass is outside the scope of this paper but can be found in standard references. 1 Helicons can produce higher plasma density n than most other discharges at the same power and therefore have been suggested for use in thrusters. Since the plasma is not fully ionized, neutral atoms entrained by the ions will also be ejected, thus increasing the effective I sp .…”

Section: Introductionmentioning

confidence: 99%

Ion ejection from a permanent-magnet mini-helicon thruster

Chen

2014

Physics of Plasmas

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A small helicon source, 5 cm in diameter and 5 cm long, using a permanent magnet (PM) to create the DC magnetic field B, is investigated for its possible use as an ion spacecraft thruster. Such ambipolar thrusters do not require a separate electron source for neutralization. The discharge is placed in the far-field of the annular PM, where B is fairly uniform. The plasma is ejected into a large chamber, where the ion energy distribution is measured with a retarding-field energy analyzer. The resulting specific impulse is lower than that of Hall thrusters but can easily be increased to relevant values by applying to the endplate of the discharge a small voltage relative to spacecraft ground. V C 2014 AIP Publishing LLC. [http://dx

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“…The arrival of propulsion devices suitable for small spacecraft, namely micro-propulsion, is awaited. 9) Ion thrusters 10) are promising propulsion devices not only for standard-sized spacecraft but also for small spacecraft. Their characteristics of high specific impulse (3000 s), high thrust efficiency (50%), usage of inert propellant (xenon), and continuously controllable thrust meet the requirements for small spacecraft missions.…”

Section: Introductionmentioning

confidence: 99%

Switching Operation of Ion Beam Extraction and Electron Emission Using the Miniature Ion Thruster μ1

Koizumi

Kuninaka

2010

AEROSPACE TECHNOLOGY JAPAN

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Ion thrusters are promising propulsion devices not only for standard-sized spacecraft but also for small spacecraft. However, difficulty of the development of a miniature neutralizer has been a critical problem for miniature ion thrusters. We have proposed a novel ion thruster system to solve this problem. That is a switching operation, where a plasma source can select ion beam extraction or electron emission by electrical switching. The major challenge of this study is to find the method to effectively performs both functions from one plasma source. To match the system to small spacecraft, the both modes must be conducted using low microwave power and low mass flow as low as 1.0 W and 0.15 sccm. Firstly, fundamental characteristics of electron emission were investigated using an orifice plate. Based on this result, secondly, a special grid system for the switching operation was designed and examined. This grid system has two-different-size apertures for ions and electrons respectively. This grid showed high ion beam extraction performance, that is, 4.1 mA ion beam current at 1.0 W microwave power input. It also showed much higher electron current than the old grid system, although the electron current of 1.0 mA has not reached the targeted current yet. As a result, the experiment showed that the special grid system proposed here is an effective method to realize the switching operation.

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Fundamentals of Electric Propulsion

Cited by 1,122 publications

References 58 publications

Development of a Low Power Multipole Confined Microwave Plasma Ion Thruster

Development of a Low Power Multipole Confined Microwave Plasma Ion Thruster

Ion ejection from a permanent-magnet mini-helicon thruster

Switching Operation of Ion Beam Extraction and Electron Emission Using the Miniature Ion Thruster μ1

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