3 edition of Numerical simulation of self-field MPD thrusters found in the catalog.
Numerical simulation of self-field MPD thrusters
by National Aeronautics and Space Administration, Lewis Research Center, For sale by the National Technical Information Service in [Cleveland, Ohio], [Springfield, Va
Written in English
|Other titles||Numerical simulation of self field MPD thrusters.|
|Statement||Michael R. LaPointe.|
|Series||NASA contractor report -- 187168., NASA contractor report -- NASA CR-187168.|
|Contributions||Lewis Research Center.|
|The Physical Object|
In order to develop of a 1-MW-class radiation-cooled steady-state Self-Field Magnetoplasmadynamic (SF-MPD) thruster head, Kawasaki et al developed a numerical design tool and thermal phenomenon of thruster head were modelized and numerically analyzed. This thruster is called as SF-MPD thruster ISAS model. Get this from a library! Numerical simulation of cylindrical, self-field MPD thrusters with multiple propellants. [Michael R LaPointe; United States. .
C. Boie: Numerical simulation of magnetoplasmadynamic self—field thrusters with high resolution adaptive methods (in German), Ph.D. thesis, Institute of Space Systems, University of Stuttgart, Germany, Google Scholar. thruster types that are presently in use by orbiting spacecraft. The physical regimes created in these thrusters indicate that a variety of numerical methods are required for accurate numerical simulation ranging from continuum formulations to kinetic approaches. Successes of numerical simulation models are demonstrated through specific examples.
We present nonoverlapping domain decomposition methods for the numerical treatment of compressible viscous plasma flows inside a self—field magnetoplasmadynamic (MPD) accelerator. The magneto—plasma flow is modelled by a system of conservation laws extended by partial differential equations describing the electromagnetic field. Book Search tips Selecting this option will search all publications across the Scitation platform Selecting this option will search all publications for the Publisher/Society in context. “ Numerical simulation of cylindrical, self-field MPD thrusters with multiple propellants,” in International Electric Propulsion Conference.
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Numerical Simulation of Geometric Scale Effects in Cylindrical Self-Field 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(NASA-CRZ4) NUMERICAL. Since the beginning of the design and investigation of self-field MPD thrusters at the end of the sixties with the works of Morozov , many efforts have been made by researchers to understand the physics of discharge and to develop appropriate ly, notable numerical studies focussing on the simulation of the plasma flow inside a self-field MPD thruster Author: Charles Chelem Mayigué, Charles Chelem Mayigué, Rodion Groll.
Numerical Simulation of a MW-Class Self Field Magnetoplasmadynamic Thruster using the MACH 2 Code IEPC Presented at the 29 th International Electric Propulsion Conference, Princeton University, October 31 – November 4, Brian L.
Numerical simulation of self-field MPD thrusters book * and Pavlos G. Mikellides.† Arizona State University, Tempe, AZ,United States of. Numerical results of plasma flow simulation in a cylindrical lab-scale 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 of Argon fuelled self-field magnetoplasmadynamic thrusters using the central-upwind scheme flux interpolations European Journal of Mechanics - B/Fluids, Vol.
72 Direct Wave-Drive ThrusterCited by: Proceedings of ISSS-7, March, Numerical Simulation of a Self-Field MPD Thruster using Lax-Friedrich Scheme 1, 2, and 1 1Department of Energy Science, Tokyo Institute of Technology, Yokohama, Kanagawa, Japan 2 Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara, Kanagawa, Japan.
Lapoint, M., Numerical simulation of geometric scale effects in cylindrical self-field MPD thrusters, JulyNASA CR King, D.Q., Magnetoplasmadynamic Channel Flow for Design of Coaxial MPD Thrusters, JunePhD dissertation, Princeton University2. A 2-D, two-temperature, single fluid magnetohydrodynamic code which incorporates classical plasma transport coefficients and Hall effects was developed to predict steady-state, self-field magnetoplasmadynamic (MPD) thruster performance.
The governing equations and numerical methods of solution are outlined and discussed. Experimental comparisons are used to. The performance of the magnetoplasmadynamic thruster is predicted using numerical simulation. The thruster mode is self-induced magnetic field with cylindrical electrodes.
The dependence of the thrust level, specific impulse, and the mass flow rate in different total electric currents is investigated. The AUSM+ scheme is utilized to develop a numerical procedure.
The model developed was tested for various 1D and D cases. These simulations have been carried out for a special case of geometries called Tikhonov fitted geometries for alleviating the instability phenomenon commonly known as onset phenomenon in self-field MPD thrusters. The work was also extended to applied field MPD thrusters.
Numerical Simulation of a Hydrogen MPD Thruster with Temperature Nonequilibrium JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Vol. 60, No. 1 Numerical Study of a Hydrogen Plasma Flow Field in a Self-Field Magnetoplasmadynamic Thruster.
An overview is given on a numerical simulation program for applied field magnetoplasmadynamic (AF-MPD) thrusters, which is currently under development at the Institute of Space Systems (IRS). For the numerical simulation of magnetoplasmadynamic (MPD) self‐field thruster flow, the solution of one of the two dynamical Maxwell equations – Faraday's law – is required.
The Maxwell equations and Ohm's law for plasmas can be summarized in one equation for the stream function so that the two‐dimensional, axisymmetric magnetic field can be.
Kubota K, Funaki I, Okuno Y. Numerical investigation of ionization and acceleration processed in a self-field MPD thruster. 29 th International Electric Propulsion Conference, 1. Michael, R.L. Numerical Simulation of Self-Field MPD Thrusters.
NASA Contractor Rep. AIAA [Google Scholar] Edgar, C. Scaling of Thrust in Self-Field Magnetoplasmadynamic Thrusters. Propul. Power14, – [Google Scholar]. Development and Validation of a Parallel MHD Code for the Simulation of Self-Field MPDT Flows - 27th International Electric Propulsion Conference () A Flux-Limited Numerical Method for the MHD Equations to Simulate Propulsive Plasma Flows - International Journal for Numerical Methods in Enginnering ().
Numerical Simulation of Cylindrical, Self-field MPD Thrusters with Multiple Propellants. By Michael R. Lapointe. Abstract. A two-dimensional, two-temperature, single fluid MHD code was used to predict the performance of cylindrical, self-field magnetoplasmadynamic (MPD) thrusters operated with argon, lithium, and hydrogen propellants.
Anomalous transport effects in an Ar self-field coaxial MPD thruster are presently studied by means of a fully 2D two-fluid numerical code; its calculations are extended to a range of typical operating conditions. An effort is made to compare the spatial distribution of the steady state flow and field properties and thruster power-dissipation values for simulation runs with and.
IN A SELF-FIELD MPD THRUSTER The MPD thruster is promising as a future propulsion system from the viewpoint of high specific impulse. The experiments on MPD thrusters have been performed by numerous workers where the results concerning thrust performance have been obtained .
Algorithm of numerical simulation Results. Abstract: Numerical simulation code for the analyses in the wide operation range of a self-field magnetoplasmadynamic(MPD) thruster is developed. Argon is used as the propellant and non-equilibrium multiple ionization processes are considered for modeling of the high temperature plasma.
To simulate a transition from electrothermal acceleration to. Get this from a library! Numerical simulation of self-field MPD thrusters. [Michael R LaPointe; Lewis Research Center.].J.W.
Barnett and R.G. Jahn Onset Phenomena in MPD Thrusters AIAA Paper September H.L. Kurtz, M. Auweter-Kurtz, and H.O. Schrade Self Field MPD Thruster Design- Experimental and Theoretical Investigations AIAA Paper J.A.
Shercliff Some Engineering Applications of Magnetohydrodynamics Numerical Simulation of Self-Field MPD Thrusters Michael R. LaPointe Sverdrup Technology, Inc.
Lewis Research Center Group Brook Park, Ohio Abstract A fully two dimensional magnetohydrodyanamics code has been developed topredict self-field, steady-state MPD thruster performance.