| タイトル | Test Results of the RS-44 Integrated Component Evaluator Liquid Oxygen/Hydrogen Rocket Engine |
| 本文（外部サイト） | http://hdl.handle.net/2060/19940021728 |
| 著者（英） | Lariviere, B. W.; Sutton, R. F. |
| 著者所属（英） | Rockwell International Corp. |
| 発行日 | 1993-10-12 |
| 言語 | eng |
| 内容記述 | An advanced LOX/LH2 expander cycle rocket engine, producing 15,000 lbf thrust for Orbital Transfer Vehicle missions, was tested to determine ignition, transition, and main stage characteristics. Detail design and fabrication of the pump fed RS44 integrated component evaluator (ICE) was accomplished using company discretionary resources and was tested under this contracted effort. Successful demonstrations were completed to about the 50 percent fuel turbopump power level (87,000 RPM), but during this last test, a high pressure fuel turbopump (HPFTP) bearing failed curtailing the test program. No other hardware were affected by the HPFTP premature shutdown. The ICE operations matched well with the predicted start transient simulations. The tests demonstrated the feasibility of a high performance advanced expander cycle engine. All engine components operated nominally, except for the HPFTP, during the engine hot-fire tests. A failure investigation was completed using company discretionary resources. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 94N26231
AD-A277085
NASA-CR-194443
NAS 1.26:194443
RI/RD92-127
E-8305 |
| 権利 | No Copyright |
|
