| タイトル | Hydrazine monopropellant reciprocating engine development |
| 著者（英） | Akkerman, J. W. |
| 著者所属（英） | NASA Johnson Space Center |
| 発行日 | 1979-11-01 |
| 言語 | eng |
| 内容記述 | A hydrazine-fueled piston-type engine for providing 11.2 kW (15 hp) has been developed to satisfy the need for an efficient power supply in the range from 3.7 to 74.6 kW (5 to 100 hp) where existing nonair-breathing power supplies such as fuel cells or turbines are inappropriate. The engine was developed for an aircraft to fly to 21.3 km (70,000 ft) and above and cruise for extended periods. The NASA Hugh L. Dryden Flight Research Center developed a remotely piloted aircraft and the associated flight control techniques for this application. About 20 hr of run time have demonstrated good efficiency and adequate life. One flight test to 6.1 km (20,000 ft) has been made using the engine with a small fixed-pitch four-bladed propeller. The test was successful in demonstrating operational characteristics and future potential. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 80A46548
ASME PAPER 78-WA/AERO-12 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/420676 |
