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Preliminary evaluation of a 10 kw hall thruster
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | McVey, John Jankovsky, Robert S. McLean Sr., Chris |
| Copyright Year | 1999 |
| Description | A 10 kW Hall thruster was characterized over a range of discharge voltages from 300-500 V and a range of discharge currents from 15-23 A. This corresponds to power levels from a low of 4.6 kW to a high of 10.7 kW. Over this range of discharge powers, thrust varied from 278 mN to 524 mN, specific impulse ranged from 1644 to 2392 seconds, and efficiency peaked at approximately 59%. A continuous 40 hour test was also undertaken in an attempt to gain insight with regard to long term operation of the engine. For this portion of the testing the thruster was operated at a discharge voltage of 500 V and a discharge current of 20 A. Steady-state temperatures were achieved after 3-5 hrs and very little variation in performance was detected. |
| File Size | 826914 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19990046494 |
| Archival Resource Key | ark:/13960/t2h75bz2z |
| Language | English |
| Publisher Date | 1999-04-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Electric Propulsion Propulsion System Performance Rocket Propellants Rocket Thrust Flow Velocity Hall Effect Specific Impulse Engine Tests Magnetic Fields Rocket Engine Design Booster Rocket Engines Electric Current Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
