Dual-Mode Operation of Stationary Plasma Thrusters

Lazurenko, A.; Vial, Vanessa; Bouchoule, A.; Skryl’nikov, A. M.; Козлов, В. І.; Kim, Vladimir

doi:10.2514/1.8279

Cited by 20 publications

(9 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…It implies a better utilization of energy for ionization and/or acceleration purposes at the high power level. This experimental result agrees with the fact that for a given HET design the thrust efficiency tends to increase with the input power [13,28]. Furthermore, the evolution of R TP along with P tells us that the wall temperature, therefore the power losses, depends neither on thermal history of the thruster nor on material surface conditions nor on the magnetic field map as long as differences are not drastic.…”

Section: Temperature To Power Ratiosupporting

confidence: 84%

“…Under standard operating conditions (300 V, 5.42 mg s −1 ), the SPT100-ML engine delivers a thrust of 82 mN [4] and P coils is typically 40 W. Thus the thrust efficiency reaches 44.6%. For modern HET, η F lies between 45% and 65% [23]. In spite of a high efficiency, previous numbers reveal that a non-negligible fraction of the input power is not converted into thrust.…”

Section: Plasma-surface Interaction Inside the Channelmentioning

confidence: 97%

“…In the previous discussion, the role of multiply charged ions as well as UV radiations was disregarded. Multiply charged Xe n+ ions, especially Xe 2+ ions, even if in the minority, might participate in power loss mechanisms inside the channel as they experience a stronger acceleration through the plasma sheath [6,28]. It is worth noticing that the high thruster wall temperature is also due to the fact that the annular channel forms an enclosure in which thermal radiation trapping is favoured.…”

Section: Plasma-surface Interaction Inside the Channelmentioning

confidence: 99%

See 2 more Smart Citations

A calibrated infrared imaging study on the steady state thermal behaviour of Hall effect thrusters

Mazouffre¹,

Echegut²,

Dudeck³

2006

Plasma Sources Sci. Technol.

View full text Add to dashboard Cite

The thermal behaviour of Hall effect thrusters was investigated by means of calibrated infrared thermal imaging performed in the 8-9 µm spectral domain. Study on the variation of the steady state temperature of Hall thruster elements like discharge chamber (channel) walls and anodes along with discharge voltage and propellant (xenon) mass flow rate confirms that energy loss mechanisms, which are responsible for the heating of the thrusters, are a direct consequence of interactions between charged particles and surfaces. In order to obtain new insights into plasma surface interactions inside a thruster, the channel wall temperature was monitored over a broad range of electrical power stretching from 400 W to 5.5 kW for three types of thrusters with different designs, dimensions and operation domains, namely SPT100-ML, PPS ® 1350-G and PPSX000-ML. Note that over the range of thruster operating conditions the facility backpressure varies from 10 −5 to 6 × 10 −5 mbar. In addition, the effect of discharge chamber wall material on temperature field was also investigated using dielectric BN-SiO 2 and AlN walls as well as conducting graphite walls. For a given thruster geometry and material, a simple relationship between the mean wall temperature and the input electrical power can be established, in contradiction to the complex dynamics of such a magnetized plasma medium. Besides, thruster thermal history and degree of wear do not have a strong impact on power losses inside the channel.

show abstract

Section: Temperature To Power Ratiosupporting

confidence: 84%

Section: Plasma-surface Interaction Inside the Channelmentioning

confidence: 97%

Section: Plasma-surface Interaction Inside the Channelmentioning

confidence: 99%

See 1 more Smart Citation

A calibrated infrared imaging study on the steady state thermal behaviour of Hall effect thrusters

Mazouffre¹,

Echegut²,

Dudeck³

2006

Plasma Sources Sci. Technol.

View full text Add to dashboard Cite

show abstract

“…The growth of α is especially connected with the electron temperature that increases with the voltage [23]. Actually, the production of multiply-charged ions must also be dealt for accurately assessing the value of α [24]. The growth of α is connected with both the the electron temperature and the fraction of multiply-charged ions [24].…”

Section: Validity Of the Scaling Lawsmentioning

confidence: 99%

Sizing of Hall effect thrusters with input power and thrust level: An Empirical Approach

Dannenmayer,

Mazouffre

2008

Preprint

View full text Add to dashboard Cite

Sizing methods can be used to get a first estimate of the required Hall thruster dimensions and operating conditions for a given input power and a corresponding thrust level. After a review of the existing methods, a new approach, which considers the three characteristic thruster dimensions, i.e. the channel length, the channel width and the channel mean diameter as well as the magnetic field, is introduced. This approach is based on analytical laws deduced from the physical principles that govern the properties of a Hall effect thruster, relying on a list of simplifying assumptions. In addition, constraints on the channel wall temperature as well as on the propellant atom density inside the channel are taken into account. The validity of the scaling laws is discussed in light of a vast database that comprises 23 single-stage Hall effect thrusters covering a power range from 10 W to 50 kW. Finally, the sizing method is employed to obtain a preliminary geometry and the magnetic field strength for a 20 kW and a 25 kW Hall effect thruster able to deliver a thrust of 1 N, respectively 1.5 N.

show abstract

“…So it is difficult for the SSHT to meet the requirements of long-term deep space exploration in the future. 4 A double stage Hall thruster (DSHT), which is devoted to control the ionization process and the acceleration process independently, is capable of satisfying the new requirements of space mission. As shown in Fig.…”

Section: Introductionmentioning

confidence: 99%

The influence of magnetic field strength in ionization stage on ion transport between two stages of a double stage Hall thruster

Yu,

Song,

et al. 2012

Physics of Plasmas

View full text Add to dashboard Cite

It is futile for a double stage Hall thruster to design a special ionization stage if the ionized ions cannot enter the acceleration stage. Based on this viewpoint, the ion transport under different magnetic field strengths in the ionization stage is investigated, and the physical mechanisms affecting the ion transport are analyzed in this paper. With a combined experimental and particle-in-cell simulation study, it is found that the ion transport between two stages is chiefly affected by the potential well, the potential barrier, and the potential drop at the bottom of potential well. With the increase of magnetic field strength in the ionization stage, there is larger plasma density caused by larger potential well. Furthermore, the potential barrier near the intermediate electrode declines first and then rises up while the potential drop at the bottom of potential well rises up first and then declines as the magnetic field strength increases in the ionization stage. Consequently, both the ion current entering the acceleration stage and the total ion current ejected from the thruster rise up first and then decline as the magnetic field strength increases in the ionization stage. Therefore, there is an optimal magnetic field strength in the ionization stage to guide the ion transport between two stages.

show abstract

Dual-Mode Operation of Stationary Plasma Thrusters

Cited by 20 publications

References 11 publications

A calibrated infrared imaging study on the steady state thermal behaviour of Hall effect thrusters

A calibrated infrared imaging study on the steady state thermal behaviour of Hall effect thrusters

Sizing of Hall effect thrusters with input power and thrust level: An Empirical Approach

The influence of magnetic field strength in ionization stage on ion transport between two stages of a double stage Hall thruster

Contact Info

Product

Resources

About