Results 261 to 270 of about 8,678 (302)

Kinetic Effects in Hall Thruster Discharge

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2006
Recent analytical studies and particle-in-cell simulations suggested that the electron velocity distribution function in E×B discharge of annular geometry Hall thrusters is non-Maxwellian and anisotropic. The average kinetic energy of electron motion in the direction parallel to the thruster channel walls (across the magnetic field) is several times ...
I. D. Kaganovich, Y. Raitses, D. Sydorenko, A. Smolyakov   +3 more
openaire   +1 more source

Hall current ion-thruster performance

Journal of Propulsion and Power, 1992
A Hall current ion thruster has been developed to investigate its thruster performance and acceleration processes. Thrust was measured by mounting the thruster on a pendulum-type thrust stand, and internal efficiencies such as propellant utilization, acceleration, and beam energy efficiencies were measured with an ion-beam collector and an ion-energy ...
Kimiya Komurasaki, Yoshihiro Arakawa
openaire   +1 more source

A laboratory-scale Hall thruster

31st Joint Propulsion Conference and Exhibit, 1995
Anticipating future Stationary Plasma Thruster (SPT) evaluation programs, we designed, constructed, and tested a 400 Watt class SPT and propellant feed system. This "laboratory-scale" Hall thruster aids in developing advanced plume diagnostics. The SPT's performance was measured by a thrust stand under high vacuum operation.
JR., SZABO, ., JAMES POLLARD
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Performance calculation of Hall thrusters

Acta Astronautica, 1996
Abstract Plasma flows in a Hall thruster are numerically analyzed by using a 2-D calculation code, and the thruster performance is estimated for several thruster configurations. The model presented herein is mainly comprised of an electron diffusion equation, an ion kinetic equation, and an energy conservation equation, which enables one to compute ...
Kimiya Komurasaki, Yoshihiro Arakawa
openaire   +1 more source

Hall thruster with grooved walls

Journal of Applied Physics, 2013
Axial-oriented and azimuthal-distributed grooves are formed on channel walls of a Hall thruster after the engine undergoes a long-term operation. Existing studies have demonstrated the relation between the grooves and the near-wall physics, such as sheath and electron near-wall transport.
Hong Li, Zhongxi Ning, Daren Yu
openaire   +1 more source

Thermal model of Hall thruster

High Power Laser and Particle Beams, 2014
To provide energy loss loading conditions for the thermal analysis of Hall thruster, a thermal model of Hall thruster is developed. Based on the plasma theory, the mechanism of various energy losses in discharge chamber is analyzed, and related functions are established between these energy losses and operation, performance parameters and structural ...
龙建飞 Long Jianfei, 孙明明 Sun Mingming, 张天平 Zhang Tianping, 吴先明 Wu Xianming   +3 more
openaire   +1 more source

Multi-mode Hall thruster development

37th Joint Propulsion Conference and Exhibit, 2001
The BPT-4500 and method of tuning the acceleration by focusing a plasma lens is described. Test results show that overall thruster efficiency and plume shape is improved by adjusting the curvature of magnetic field lines in the acceleration zone. Thrust efficiency is improved to 50% from 21% at 150 V and from 58% to 62.5% at 350 V using this technique.
D. King, K. de Grys, R. Jankovsky
openaire   +1 more source

Ion Current in Hall Thrusters

IEEE Transactions on Plasma Science, 2008
To match the observed thrust and discharge current in Hall thrusters, computer simulations have typically assumed anomalous electron transport mechanisms, such as Bohm diffusion, to enhance electron mobility across magnetic field lines. Without enhanced electron transport, the simulations predict a much lower discharge current than observed, and too ...
Ira Katz, Richard R. Hofer, Dan M. Goebel   +2 more
openaire   +1 more source

Anodic plasma in Hall thrusters

Journal of Applied Physics, 2008
In this paper plasma dynamics and ionization of propellant gas are modeled within the anode holes used for gas injection of a Hall thruster. Under conditions of anode coating with dielectric material, the discharge current should close within these holes, which results in ionization and formation of plasma jets emanating from the openings.
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Anode sheath in Hall thrusters

Applied Physics Letters, 2003
A set of hydrodynamic equations is used to describe quasineutral plasma in ionization and acceleration regions of a Hall thruster. The electron distribution function and Poisson equation are invoked for description of a near-anode region. Numerical solutions suggest that steady-state operation of a Hall thruster can be achieved at different anode ...
L. Dorf, V. Semenov, Y. Raitses
openaire   +1 more source