Thrust efficiency optimization of the pulsed plasma thruster SIMP-LEX

Nawaz, Anuscheh; Albertoni, Riccardo; Auweter‐Kurtz, Monika

doi:10.1016/j.actaastro.2010.03.006

Cited by 40 publications

(24 citation statements)

References 4 publications

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“…A further amelioration in the studies conducted at IRS found that optimizing the electrical circuit helped increase the total thrust efficiency by a factor of approximately 2 13) , whereas the mean exhaust velocity was raised by nearly 40%. Thus, the amount of propellant needed to fulfill the missions' needs is reduced tremendously.…”

Section: Discussionmentioning

confidence: 99%

“…Especially it could be shown analytically that the thrust efficiency is a function of the characteristic discharge time τ c as well as the basic inductance L 0 of the circuit 3,13) . In order to investigate these effects and based on the results of the geometric optimization, a newly designed thruster engineering model named ADD SIMP-LEX was introduced, as can be seen in Figure 4.…”

Section: Electrical Circuit Design Optimizationmentioning

confidence: 99%

“…Further, it could be investigated that an optimum performance of ADD SIMP-LEX could be achieved at a capacitance of 60 µF, i.e., using only three of the initial four capacitors 13) . The key parameters of selected thruster configurations are presented in Table 3.…”

Section: Electrical Circuit Design Optimizationmentioning

confidence: 99%

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Review of Pulsed Plasma Thruster Development at IRS

Schönherr

Nawaz

Lau

et al. 2010

AEROSPACE TECHNOLOGY JAPAN

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The research and development process of the ablative pulsed plasma thruster SIMP-LEX is summarized. By experiment, the magnetic field in between the electrodes was measured with an induction probe, and a high-speed camera was applied to estimate the propagation of the plasma plume. Further, the optimization process towards higher thrust efficiency by means of geometric and electrical modifications is described. By analysis, the calculation of magnetic field and change in inductance is summarized and the numerical models for the performance simulation of SIMP-LEX introduced. A peak value of 0.7 T was found for the magnetic field created during an 80 J discharge whereas a propagation velocity of 28 km/s was estimated for the first plasma plume. The optimization process towards a new engineering model yielded an increase of 40% in mean exhaust velocity to 26 km/s, and a maximum thrust efficiency of 32% was evaluated respectively. Calculation of magnetic field and change in inductance based on the Biot-Savart law yield input for the slug model, which can then predict the general performance parameters with a good accordance.

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Section: Discussionmentioning

confidence: 99%

Section: Electrical Circuit Design Optimizationmentioning

confidence: 99%

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Review of Pulsed Plasma Thruster Development at IRS

Schönherr

Nawaz

Lau

et al. 2010

AEROSPACE TECHNOLOGY JAPAN

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“…The plasma in vacuum gap discharge is made up of metal ions from cathode material and electrons, and diffuses in different directions under the action of potential hump near the cathode [1][2][3]. If the density, propagation velocity and performance of directional ejection of metal ion plasma jet are improved, it will be better applied to ion implantation technology and pulsed plasma thruster [4][5][6][7][8]. In order to improve properties of plasma jet, a lot of research studies have been carried out [9][10][11][12][13][14][15][16][17][18].…”

Section: Introductionmentioning

confidence: 99%

Generation characteristics of a metal ion plasma jet in vacuum discharge

Tian¹,

Liu²,

Cui³

et al. 2018

Plasma Sci. Technol.

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To improve the performance of a metal ion plasma jet in vacuum discharge, an anode-insulated cone-cylinder electrode with insulating sleeve is proposed in this paper. Discharge characteristics and generation characteristics of plasma of the electrode are investigated, effects of diameter of insulating sleeve, variety of cathode material and length of the insulating sleeve on characteristics of metal ion plasma jet are discussed. Results indicate that a directional and steady plasma jet is formed by using the novel electrode with insulating sleeve under high vacuum conditions. Moreover, the properties of metal ion plasma jet are improved by using the aluminum cathode and thin and long insulating sleeve. The study provides strong support for research of vacuum metal ion plasma thruster and ion implantation technology.

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“…The thruster has been theoretically and experimentally investigated at IRS as part of the project funded by the Deutsches Zentrum f ur Luft und Raumfahrt (DLR) in the past. Recently, extensive development e¨orts by Nawaz et al in the ¦eld of thruster optimization in combination with close cooperation with [6,7].…”

Section: Pulsed Plasma Thrustermentioning

confidence: 99%

Electric propulsion systems for small satellites: the low earth orbit mission perseus

Bock

Herdrich

Lau

et al. 2011

Progress in Propulsion Physics

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The Institute of Space Systems, Universit at Stuttgart, launched a ¤Small Satellite Program¥ in 2002. The ¦rst two of the four planed small satellites, Flying Laptop and PERSEUS, are both Low Earth Orbit (LEO) missions. The third mission Cermit is a reentry satellite and the last of the small satellites ¡ Lunar Mission BW1 ¡ is a mission to the Moon. For this purpose, di¨erent propulsion systems are mandatory. The propulsion system for Lunar Mission BW1 will consist of two different types of thruster systems: a cluster of pulsed magnetoplasmadynamic (MPD) thrusters (SIMP-LEX) using solid polytetra §uoroethy-lene (PTFE) as propellant and a thermal arcjet thruster (TALOS) using gaseous ammonia as propellant. Both thruster systems are currently under development at IRS. They are planned to be tested on board the small satellite mission PERSEUS, one of the precursor missions of Lunar Mission BW1. The thruster systems have been investigated intensely in the past and, furthermore, optimization of the thrusters with respect to the mission requirements of Lunar Mission BW1 has been started. The test procedures for the technology demonstration on the PERSEUS satellite are under development at present.

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Thrust efficiency optimization of the pulsed plasma thruster SIMP-LEX

Cited by 40 publications

References 4 publications

Review of Pulsed Plasma Thruster Development at IRS

Review of Pulsed Plasma Thruster Development at IRS

Generation characteristics of a metal ion plasma jet in vacuum discharge

Electric propulsion systems for small satellites: the low earth orbit mission perseus

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