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Lox/lh2 propulsion system for launch vehicle upper stage, test results
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Yuzawa, Y. Imachi, U. Ikeda, T. Higashino, K. Miyoshi, K. Kondo, Y. |
| Copyright Year | 1984 |
| Description | The test results of small LOX/LH2 engines for two propulsion systems, a pump fed system and a pressure fed system are reported. The pump fed system has the advantages of higher performances and higher mass fraction. The pressure fed system has the advantages of higher reliability and relative simplicity. Adoption of these cryogenic propulsion systems for upper stage of launch vehicle increases the payload capability with low cost. The 1,000 kg thrust class engine was selected for this cryogenic stage. A thrust chamber assembly for the pressure fed propulsion system was tested. It is indicated that it has good performance to meet system requirements. |
| File Size | 729306 |
| Page Count | 20 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850003781 |
| Archival Resource Key | ark:/13960/t42r8p43n |
| Language | English |
| Publisher Date | 1984-09-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Launch Vehicles Propulsion System Performance Cryogenic Cooling Upper Stage Rocket Engines Thrust Chambers Hydrogen Oxygen Engines Engine Tests Engine Parts Test Firing Spacecraft Propulsion Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
