Analysis, design, fabrication, and test efforts were performed for the existing OF2/B2H6 regeneratively cooled lK (4448 N) thrust chamber to illustrate simultaneous B2H6 fuel and OF2 oxidizer cooling and to provide results for a gaseous propellant condition injected into the combustion chamber. Data derived from performance, thermal and flow measurements confirmed predictions derived from previous test work and from concurrent analytical study. Development data derived from the experimental study were indicated to be sufficient to develop a preflight thrust chamber demonstrator prototype for future space mission objectives.
Regeneratively cooled rocket engine for space storable propellants
1973-07-01
Report
Keine Angabe
Englisch
Methane-fuel corrosion in regeneratively cooled rocket-engine combustors
Tema Archiv | 1989
|Engine system design for space storable propellants
AIAA | 1968
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