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.
Low-thrust chemical rocket engine study
1981-03-01
Report
Keine Angabe
Englisch
Low-Thrust Chemical Rocket Engine Study
NTIS | 1981
|Low-thrust chemical rocket engine study
NTRS | 1980
|Low-Thrust Chemical Rocket Engine Study
NTIS | 1981
|Low-thrust chemical rocket engine study
NTRS | 1981
|