| タイトル | Benefits of Low-Power Electrothermal Propulsion |
| 本文（外部サイト） | http://hdl.handle.net/2060/19970010126 |
| 著者（英） | Oleson, Steven R.; Sankovic, John M. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1997-01-01 |
| 言語 | eng |
| 内容記述 | Mission analyses were completed to show the benefits of low-power electrothermal propulsion systems for three classes'of LEO smallsat missions. Three different electrothermal systems were considered: (1) a 40 W ammonia resistojet system, (2) a 600 W hydrazine arcjet system, and (3) a 300 W ammonia resistojet. The benefits of using two 40 W ammonia resistojet systems were analyzed for three months of drag makeup of a Shuttle-launched 100 kg spacecraft in a 297 km orbit. The two 46 W resistojets decreased the propulsion system wet mass by 50% when compared to state-of-art hydrazine monopropellant thrusters. The 600 W arcjet system was used for a 300 km sun synchronous makeup mission of a 1000 kg satellite and was found to decrease the wet propulsion mass by 30%. Finally, the 300 W arcjet system was used on a 200 kg Earth-orbiting spacecraft for both orbit transfer from 300 to 400 km, two years of drag makeup, and a final orbit rise to 700 km. The arcjet system was determined to halve the propulsion system wet mass required for that scenario as compared to hydrazine monopropellant thrusters. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | 97N15358
NASA-TM-107404
NAS 1.15:107404
E-10616 |
| 権利 | No Copyright |
