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Carbon monoxide and oxygen combustion experiments: a demonstration of mars in situ propellants
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Linne, Diane L. |
| Copyright Year | 1991 |
| Description | The feasibility of using carbon monoxide and oxygen as rocket propellants was examined both experimentally and theoretically. The steady-state combustion of carbon monoxide and oxygen was demonstrated for the first time in a subscale rocket engine. Measurements of experimental characteristic velocity, vacuum specific impulse, and thrust coefficient efficiency were obtained over a mixture ratio range of 0.30 to 2.0 and a chamber pressures of 1070 and 530 kPa. The theoretical performance of the propellant combination was studied parametrically over the same mixture ratio range. In addition to one dimensional ideal performance predictions, various performance reduction mechanisms were also modeled, including finite-rate kinetic reactions, two-dimensional divergence effects and viscous boundary layer effects. |
| File Size | 8085268 |
| Page Count | 19 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19910014990 |
| Archival Resource Key | ark:/13960/t6f23vw09 |
| Language | English |
| Publisher Date | 1991-01-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Extraterrestrial Resources Propellant Tests Propulsion System Performance Liquid Rocket Propellants Performance Prediction Propulsive Efficiency Mars Atmosphere Propellant Combustion Spacecraft Propulsion Liquid Oxygen Reaction Kinetics Manned Mars Missions Carbon Monoxide Liquid Propellant Rocket Engines Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
