Development and Preliminary Characterization of a Low Power Hall Thruster Prototype

Biagioni, L.; Cesari, U.; Saverdi, M.

doi:10.2514/6.2004-3944

Cited by 6 publications

(1 citation statement)

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“…In spite of the simple idea underlying the construction of such a thruster, the description of plasma discharge in this device is a complex problem. Therefore, the optimization in order to maximize its performance is a very diffi cult task [1]. In our case, the HETMAN code designed in our laboratory was used to study the operational characteristics of the thruster and, in particular, the dependence of the effi ciency of the thruster on its parameters.…”

Section: Introductionmentioning

confidence: 99%

Advanced laboratory for testing plasma thrusters and Hall thruster measurement campaign

Szelecka

2016

Nukleonika

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Abstract. Plasma engines are used for space propulsion as an alternative to chemical thrusters. Due to the high exhaust velocity of the propellant, they are more effi cient for long-distance interplanetary space missions than their conventional counterparts. An advanced laboratory of plasma space propulsion (PlaNS) at the Institute of Plasma Physics and Laser Microfusion (IPPLM) specializes in designing and testing various electric propulsion devices. Inside of a special vacuum chamber with three performance pumps, an environment similar to the one that prevails in space is created. An innovative Micro Pulsed Plasma Thruster (LPPT) with liquid propellant was built at the laboratory. Now it is used to test the second prototype of Hall effect thruster (HET) operating on krypton propellant. Meantime, an improved prototype of krypton Hall thruster is constructed.

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Section: Introductionmentioning

confidence: 99%