| タイトル | PPT Thrust Stand |
| 本文（外部サイト） | http://hdl.handle.net/2060/19960008159 |
| 著者（英） | Haag, Thomas W. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1995-11-01 |
| 言語 | eng |
| 内容記述 | A torsional-type thrust stand has been designed and built to test Pulsed Plasma Thrusters (PPT's) in both single shot and repetitive operating modes. Using this stand, momentum per pulse was determined strictly as a function of thrust stand deflection, spring constant, and natural frequency. No empirical corrections were required. The accuracy of the method was verified using a swinging impact pendulum. Momentum transfer data between the thrust stand and the pendulum were consistent to within 1%. Following initial calibrations, the stand was used to test a Lincoln Experimental Satellite (LES-8/9) thruster. The LES-8/9 system had a mass of approximately 7.5 kg, with a nominal thrust to weight ratio of 1.3 x 10(exp -5). A total of 34 single shot thruster pulses were individually measured. The average impulse bit per pulse was 266 microN-s, which was slightly less than the value of 300 microN-s published in previous reports on this device. Repetitive pulse measurements were performed similar to ordinary steady-state thrust measurements. The thruster was operated for 30 minutes at a repetition rate of 132 pulses per minute and yielded an average thrust of 573 microN. Using average thrust, the average impulse bit per pulse was estimated to be 260 microN-s, which was in agreement with the single shot data. Zero drift during the repetitive pulse test was found to be approximately 1% of the measured thrust. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 96N15325
NASA-TM-107066
NAS 1.15:107066
E-9927
AIAA PAPER 95-2917
NIPS-95-06256 |
| 権利 | No Copyright |
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