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Geometric effects in applied-field mpd thrusters
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Myers, R. M. Mantenieks, M. Sovey, James S. |
| Copyright Year | 1990 |
| Description | Three applied-field magnetoplasmadynamic (MPD) thruster geometries were tested with argon propellant to establish the influence of electrode geometry on thruster performance. The thrust increased approximately linearly with anode radius, while the discharge and electrode fall voltages increased quadratically with anode radius. All these parameters increased linearly with applied-field strength. Thrust efficiency, on the other hand, was not significantly influenced by changes in geometry over the operating range studied, though both thrust and thermal efficiencies increased monotonically with applied field strength. The best performance, 1820 sec I(sub sp) at 20 percent efficiency, was obtained with the largest radius anode at the highest discharge current (1500 amps) and applied field strength (0.4 Tesla). |
| File Size | 814399 |
| Page Count | 22 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19900018466 |
| Archival Resource Key | ark:/13960/t18m26t8m |
| Language | English |
| Publisher Date | 1990-01-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Field Strength Electric Potential Propellants Electric Rocket Engines Plasma Propulsion Radii Argon Anodes Magnetoplasmadynamics Thrust Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
