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High voltage tal performance
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Jacobson, David T. Rawlin, Vincent K. Jankovsky, Robert S. Manzella, David H. |
| Copyright Year | 2001 |
| Description | The performance of a two-stage, anode layer Hall thruster was evaluated. Experiments were conducted in single and two-stage configurations. In single-stage configuration, the thruster was operated with discharge voltages ranging from 300 to 1700 V. Discharge specific impulses ranged from 1630 to 4140 sec. Thruster investigations were conducted with input power ranging from 1 to 8.7 kW, corresponding to power throttling of nearly 9: 1. An extensive two-stage performance map was generated. Data taken with total voltage (sum of discharge and accelerating voltage) constant revealed a decrease in thruster efficiency as the discharge voltage was increased. Anode specific impulse values were comparable in the single and two-stage configurations showing no strong advantage for two-stage operation. |
| File Size | 1004744 |
| Page Count | 20 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20020006335 |
| Archival Resource Key | ark:/13960/t1kh5j584 |
| Language | English |
| Publisher Date | 2001-11-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Throttling Electric Potential Hall Thrusters Evaluation Performance Tests Specific Impulse High Voltages Anodes Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
