| タイトル | Development of a PPT for the EO-1 Spacecraft |
| 本文（外部サイト） | http://hdl.handle.net/2060/20000121223 |
| 著者（英） | Benson, Scott W.; Arrington, Lynn A.; Hoskins, W. Andrew; Meckel, Nicole J. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2000-08-01 |
| 言語 | eng |
| 内容記述 | A Pulsed Plasma Thruster (PPT) has been developed for use in a technology demonstration flight experiment on the Earth Observing 1 (EO-1) New Millennium Program mission. The thruster replaces the spacecraft pitch axis momentum wheel for control and momentum management during an experiment of a minimum three-day duration. The EO-1 PPT configuration is a combination of new technology and design heritage from similar systems flown in the 1970's and 1980's. Acceptance testing of the protoflight unit has validated readiness for flight, and integration with the spacecraft, including initial combined testing, has been completed. The thruster provides a range of capability from 90 microN-sec impulse bit at 650 sec specific impulse for 12 W input power, through 860 microN-sec impulse bit at 1400 see specific impulse for 70 W input power. Development of this thruster reinitiates technology research and development and re-establishes an industry base for production of flight hardware. This paper reviews the EO-1 PPT development, including technology selection, design and fabrication, acceptance testing, and initial spacecraft integration and test. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | NASA/TM-2000-210340
NAS 1.15:210340
E-12386
AIAA Paper 99-2276 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/93735 |
