Experimental investigations of a breadboard model of Hall thruster

Particularities of ignition of the non-self-sustained discharge with a thermoemission cathode in crossed fields

“…Under the operation mass flow rate of xenon, its partial pressure is much higher than the residual one and is determined from the relation P g = 1.48 × 10 -4 Q Torr where Q is the mass flow rate of the gas through the thruster in amperes (1 A = 15 SCCM = 6.25 × 10 18 particles/second). The improved Hall reactive hollow anode thruster (IHRHAT) breadboard model was used as the Hall thruster, that is, the improved variant of the bread board model described in [4]. Use of the carbon-car bon composite pore diaphragm in the gas providing system is a particularity of the given ion thruster model.…”

Acceleration of heavy ions in a thruster

“…DOI: 10.1134/S1064226912020039 2. PARAMETERS OF THE PROBLEM Under the conditions that are close to the real exper imental conditions form [1], we assume that = 6 × 10 18 1/(cm 2 s), the mass flow is = 4 × 10 18 1/(cm 2 s), and the input flow velocity of atoms is V at = 10 4 cm/s. We also assume that Т е = 6 eV.…”

“…Recent interest in the experimental [1] and theo retical [2][3][4][5] study of the Hall thruster has been driven mainly by its application as a low thrust engine in space. The analysis from [2][3][4] under the conditions for the neutrality of the system n i = n e (n i and n e are ion and electron densities, respectively) shows that the stationary hydrodynamic equations describing the behavior of the system yield singularity when the ion flow velocity is equal to the velocity of ion sound.…”

Ensemble of ions and electrons in the electric field

“…A great number of researches dedicated for models examination of slow ion extraction process from plasma is undertaken ( [1][2][3][4][5][6]). This study uses a consecutive kinetic description of ionic and electronic system in case of presence of non zero electron flow.…”