Numerical simulation of geometric scale effects in cylindrical selffield MPD thrusters
 1992
 1.25 MB
 6334 Downloads
 English
National Aeronautics and Space Administration, National Technical Information Service, distributor , [Washington, DC], [Springfield, Va.?
Electric propul
Statement  M. LaPointe. 
Series  NASA contractor report  189224., NASA contractor report  NASA CR189244. 
Contributions  United States. National Aeronautics and Space Administration. 
The Physical Object  

Format  Microform 
Pagination  1 v. 
ID Numbers  
Open Library  OL16952752M 



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165 Pages0.80 MB9354 DownloadsFormat: FB2 
Numerical Simulation of Geometric Scale Effects in Cylindrical SelfField MPD Thrusters M. LaPointe Sverdrup Technology, Inc.
Lewis Research Center Group Brook Park, Ohio T Prepared for the 28th Joint Propulsion Conference and Exhibit cosponsored by the AIAA, SAE, ASME, and ASEE Nashville, Tennessee, July(NASACRZ4) NUMERICALFile Size: 1MB.
Numerical simulation of geometric scale effects in cylindrical selffield MPD thrusters M. LAPOINTE Sverdrup Technology, Inc. A 2D, twotemperature, single fluid MHD code which incorporates classical plasma transport coefficients and Hall effects has been developed to predict steadystate, selffield MPD thruster performance.
The governing equations and numerical methods of solution are outlined and discussed. Experimental comparisons are used to validate model Cited by: A maximum predicted specific impulse of s is obtained for a thruster with an anode radius of cm, a cathode radius of cm, and equal electrode lengths of cm.
A scaling relation is developed to predict, within limits, the onset of cylindrical, selffield thruster instability as a function of geometry and operating by: Get this from a library.
Numerical simulation of geometric scale effects in cylindrical selffield MPD thrusters. [M LaPointe; United States. National Aeronautics and Space Administration.].
Predictions of thrust and flow efficiency are made for a matrix of fifteen cylindrical thruster geometries, assuming a fully ionized argon propellant. A maximum predicted specific impulse of s is obtained for a thruster with an anode radius of cm, a cathode radius of cm, and equal electrode lengths of : M.
Lapointe. Numerical simulation of geometric scale effects in cylindrical selffield MPD thrusters. By M. Lapointe. Abstract. A 2D, twotemperature, single fluid MHD code which incorporates classical plasma transport coefficients and Hall effects has been developed to predict steadystate, selffield MPD thruster performance.
Author: M. Lapointe. predict selffield MPD thruster performance.
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7"19The numerical simulation is based upon a fully ionized, single fluid approximation to the MHD equations, and includes viscous forces, classical plasma transport, and Hall effects.
MaxweU's equations and a generalized Ohm's law are used to couple the electromagnetic equations to the fluid equations.
AFile Size: 1MB. Coaxial MPD Thrusters in the year The current, mass flow, and electrode geometry of selffield, coaxial MPD thrusters are related to terminal characteristics such as voltage, specific impulse and thrust efficiency by both experiment and a simple 1D model.
For high power. In order to clarify the discharge principle of the selffield magnetoplasmadynamic thruster (MPDT), a twodimensional axisymmetric particleincell/Monte Carlo collision (PIC/MCC) model is proposed.
The spatial distribution and the collision characteristics of discharge plasma were calculated using this model. In addition, the influence of the operation parameters on the Author: Jian Li, Yu Zhang, Jianjun Wu, Yuqiang Cheng, Xinru Du.
Recently, notable numerical studies focussing on the simulation of the plasma flow inside a selffield MPD thruster have been carry out. Niewood [3] proposed a finite difference, one dimensional unsteady method dedicated to the selffield MPD thrusters plasma flow : Charles Chelem Mayigué, Charles Chelem Mayigué, Rodion Groll.
nonstationary fullscale model quadcore processors, with integral main memory of 40 GB) simulation model up to 6 degree The resonator model was elements.
Details Numerical simulation of geometric scale effects in cylindrical selffield MPD thrusters FB2
The mathematical model resonator was based on the Navier algorithms. Implicit finitedifference secondorder accuracy in space numerical simulation. 4 internal been solved at each File Size: KB.
NASA, Lewis Research Center, Cleveland; Sverdrup Technology, Inc., Brook Park, OH. Application of a new numerical solver to the simulation of MPD flows.
ric scale effects in cylindrical selfﬁeld MP D. In selffield MPD thrusters, only the magnetic induction is. Lapoint, M., Numerical simulation of geometric scale effects in cylindrical selffield MPD thrusters, JulyNASA CR King, D.Q., Magnetoplasmadynamic Channel Flow for Design of Coaxial MPD Thrusters, JunePhD dissertation, Princeton : T.
Nada. Nowadays numerical codes are indispensable tools for the research and project phase of electric propulsion systems. The application of such codes for the analyses of magnetoplasmadynamic (MPD) thrusters is very important since it allows us to understand relevant flowfield parameters that are quite difficult to visualize and analyse in experiments.
Numerical results of plasma flow simulation in a cylindrical labscale thruster, with mass flow rate of 6 g/s and total discharge current of 8 kA, are presented and comparison with experimental data shows good agreement between the predicted and measured contours of enclosed current and electric by: 6.
NUMERICAL SIMULATION AND EXPERIMENTAL STUDIES ON AFT HULL LOCAL PARAMETERIZED NONGEOSIM DEFORMATION FOR CORRECTING SCALE EFFECTS OF NOMINAL WAKE FIELD UDC Original scientific paper Summary The scale effects of an aft hull wake field pose a great challenge to propeller design and its performance by: 5.
NUMERICAL SIMULATION OF INSTATIONARY MAGNETOPLASMADYNAMIC THRUSTERS, D. D Andrea 1, 2, 3, The corresponding numerical approach is known as the MaxwellLorentz model, which is based on ParticleinCell techniques.
Description Numerical simulation of geometric scale effects in cylindrical selffield MPD thrusters EPUB
A brief review of this model is given i n section 2. However, in order to model the physics of aCited by: 1.
In Section 4 the numerical method is applied to the computation of the twodimensional selffield MPD thrus ter flows. Here the effects due to the geometry of the anode and the cathode, and the influence of mass flow rate are analysed.
performance of steerable thrusters. The numerical simulations based on RANSCFD have been validated with model scale measurements of various thruster geometries. Very good agreement between calculations and measurements has been found.
The Reynolds scaling effect, which makes the difference between model scale. The paper describes a novel mathematical model to study the physics of fully ionized plasma flow through MPD thrusters otherwise known as magnetoplasmadynamic thrusters.
The Author: S Vijai Kumar, S Thanigaiarasu. In the paper we describe in detail a numerical method for the resistive magnetohydrodynamic Numerical simulation of geometric scale effects in cylindrical selffield MPD thrusters.
NASA Lewis Research Centre. Google ScholarAuthor: M XistoCarlos, C PáscoaJosé, J OliveiraPaulo. To predict the thrust of magnetoplasmadynamic thrusters (MPDTs), a modified electromechanical model was proposed and a comparison with experimental results is presented in this paper.
The motion of propellant in the thruster was divided into two portions: the axial motion which was accelerated by the interaction of current and induced selffield, and the Author: Yu Zhang, Jianjun Wu, Yang Ou, Jian Li, Sheng Tan. Numerical Simulation of Plasma Flow in a SelfField MPD Thruster Coupled with Electrode Sheath View Section, Research and Development of SteadyState MPD Thrusters with Permanent Magnets and Multi Hollow Cathodes for InSpace Propulsion.
Electric propulsion (EP) today features a range of mature and wellestablished technologies for moving satellites and spacecraft in space. The development of EP dates back to the s, with the appearance of plasma sources capable of delivering substantial current [].The first inspace demonstrations of EP occurred in and were achieved with an ion engine Cited by: The main objective of this work is the numerical simulation of the Halleffect thruster plume by the combined PICMCC / DSMC (ParticleinCell plus Monte Carlo collisions / Direct Simulation Monte Carlo) method.
This method divides the simulation process into two stages: simulation of the neutral o w by the DSMC method [3] and.
The example of a plane jet flow into a rectangular cavity (“dead end”) is used in comparing the capabilities of different approaches to numerical simulation of selfoscillatory turbulent flows characterized by global quasiperiodic oscillation of all flow parameters.
The calculations are performed for two flow modes, of which the first one is statistically steady Cited by: 6. cylindrical, selffield MPD thrusters operated with a electromagnetic thrust parameter argon. lithium, and hydrogen propellants. A thruster (05cylindrical thruster geometry and (47 x 10 7 H/m) propellant species.
Koyama, "Performance Characteristics of SteadyState MPD Thrusters with Permanent Magnets and Multi Hollow Cathodes for InSpace Propulsion", IEPC M. Kong, "Geometric Effects on the Acceleration Mechanisms in AppliedField Magnetoplasmadynamic Thrusters", IEPC.
MPD Thrusters with Permanent Magnets anode geometry, distance between electrodes and magnet field strength can be changed. The cathode is shown in Fig A cylindrical cathode is made of pure tungsten, which is a heat resistant material. It has a diameter of 10 mm. The shape of the cathode tip is conical one, and the tip angle is 45 deg.This, however, was continuously flanked by numerical modeling in the field4.
For more than two decades IRS has been investigating steady state selffield MPD thrusters at powers of up to 1 MW2, 5. Some ten years ago this was extended to appliedfield MPD thrusters as these devices can also cope with.Numerical modeling and simulations are very powerful tools; their use can drastically reduce the time and resources needed to design, test, and optimize space propulsion thrusters.
Moreover, modeling and numerical simulations have become even more important for miniaturized plasma thrusters, since the reduction of the scale of the device Cited by: 1.



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