| タイトル | Combustion performance and heat transfer characterization of LOX/hydrocarbon type propellants. Task 3: Data dump |
| 本文（外部サイト） | http://hdl.handle.net/2060/19820022536 |
| 著者（英） | Hart, S. W. |
| 著者所属（英） | Aerojet Liquid Rocket Co. |
| 発行日 | 1982-07-01 |
| 言語 | eng |
| 内容記述 | A preliminary characterization of Orbital Maneuvering System (OMS) and Reaction Control System (RCS) engine point designs over a range of thrust and chamber pressure for several hydrocarbon fuels is reported. OMS and RCS engine point designs were established in two phases comprising baseline and parametric designs. Interface pressures, performance and operating parameters, combustion chamber cooling and turboprop requirements, component weights and envelopes, and propellant conditioning requirements for liquid to vapor phase engine operation are defined. |
| NASA分類 | PROPELLANTS AND FUELS |
| レポートNO | 82N30412
NAS 1.26:167714
NASA-CR-167714 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/165169 |
