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Low-thrust chemical rocket engine study (Document No: 19810012596)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Shoji, J. M. |
| Copyright Year | 1981 |
| Description | An analytical study evaluating thrust chamber cooling engine cycles and preliminary engine design for low thrust chemical rocket engines for orbit transfer vehicles is described. Oxygen/hydrogen, oxygen/methane, and oxygen/RP-1 engines with thrust levels from 444.8 N to 13345 N, and chamber pressures from 13.8 N/sq cm to 689.5 N/sq cm were evaluated. The physical and thermodynamic properties of the propellant theoretical performance data, and transport properties are documented. The thrust chamber cooling limits for regenerative/radiation and film/radiation cooling are defined and parametric heat transfer data presented. A conceptual evaluation of a number of engine cycles was performed and a 2224.1 N oxygen/hydrogen engine cycle configuration and a 2224.1 N oxygen/methane configuration chosen for preliminary engine design. Updated parametric engine data, engine design drawings, and an assessment of technology required are presented. |
| File Size | 14954942 |
| Page Count | 341 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19810012596 |
| Archival Resource Key | ark:/13960/t56f0p61z |
| Language | English |
| Publisher Date | 1981-03-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Orbit Transfer Vehicles Cooling Propellant Properties Liquid Rocket Propellants Thrust Chambers Low Thrust Rocket Engine Design Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
