Numerical calculation of nozzle type and cylindrical MPD thrusters

Sleziona, P. C.; Auweter‐Kurtz, Monika; Schrade, H. O.

doi:10.2514/6.1992-3296

Cited by 15 publications

(10 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The electric conductivity of plasma σ is calculated 15) by the use of σ = e 2 n e m e s v es (9) The viscosity of electrons is neglected in this study because it is much smaller than that of heavy particles. The viscosity of heavy particles µ, the thermal conductivity of heavy particles κ h , and the thermal conductivity of electrons κ e are given, 15) respectively, as …”

Section: Fundamental Equationsmentioning

confidence: 99%

“…Also, partially ionized flows in the MPD thrusters have been studied. 9,10) Since the characteristic time of magneto-plasma dynamics is about 10 4 times shorter than that of flow convection, the excessive short time strongly restricts the Courant-FriedrichsLewy (CFL) condition. The equation of magnetic induction c 2002 The Japan Society for Aeronautical and Space Sciences derived from Maxwell's equations and Ohm's law is generally solved separately from the flow equations as an elliptic Poisson equation.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Implicit Time-Marching Solution of Partially Ionized Flows in Self-Field MPD Thruster.

Takeda

Yamamoto

2002

Trans. Japan Soc. Aero. S Sci.

View full text Add to dashboard Cite

Self-filed magneto-plasma dynamic (MPD) viscous flows are numerically investigated. The axisymmetric compressible Navier-Stokes equations with the Lorentz force and Joule heating, the equation of magnetic induction derived from Maxwell's equations with Ohm's law, and the continuity equation of electrons are simultaneously solved with the use of an implicit time-marching method based on the LU-SGS scheme. Partially ionized flows in the experimental MPD thruster are simulated and compared with the experimental results. The calculated current stream lines and the pressure of the cathode tip are found to agree well with the experiments. The values of the pressure of the cathode tip and the thrust are also numerically predicted by changing the distance from the cathode tip to the anode.

show abstract

Section: Fundamental Equationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Implicit Time-Marching Solution of Partially Ionized Flows in Self-Field MPD Thruster.

Takeda

Yamamoto

2002

Trans. Japan Soc. Aero. S Sci.

View full text Add to dashboard Cite

show abstract

“…[17][18][19]. However, these codes do not adequately describe observed data from quasi-steady thruster experiments.…”

mentioning

confidence: 93%

“…The charge densities can be eliminated by combining equations (5)- (9), (17) and (18 So that in equation (22) above the "outer solution" becomes:…”

mentioning

confidence: 99%

Anode sheath contributions in plasma thrusters

Riggs

1993

29th Joint Propulsion Conference and Exhibit

View full text Add to dashboard Cite

“…High power electric propulsion systems offer several potential advantages over chemical engines for each of these mission types, [1][2][3] and the NASA Glenn Research Center (GRC) is working to develop high power (MWclass) electromagnetic thruster technologies to meet these demanding propulsion requirements. Current high power thruster research at NASA GRC is focused on the magnetoplasmadynamic (MPD) thruster, and includes systems analysis, 4 numerical modeling, [7][8][9][10] and experimental thruster testing. This paper provides an overview of MPD thruster operation, describes the GRC high power propulsion test facility, and discusses the experimentally measured performance of a quasi-steady, MW-class baseline MPD thruster operated with argon propellant.…”

Section: Introductionmentioning

confidence: 99%