REGENERATIVELY COOLED ROCKET ENGINE FOR SPACE STORABLE PROPELIANTS

摘要

Analysis, design, fabrication, and test efforts were performed for the existing OF2/B2H6 regeneratively cooled 1K (448 N) thrust chamber to illustrate simultaneous B2H6, fuel and OF oxidizer cooling and to provide results for a gaseous propellant condition injected into the combustion chamber.nThe regeneratively cooled mode for the OF2 /B2H6, propellant combination had been explored on previous work with fuel cooling and for the current work the combined cooling mode had been selected for demonstration in an advanced fabrication milled channel construction thrust chamber.nDesign, analysis, and fabrication efforts were completed satisfactorily for the thrust chamber with an integral OF 2cooling jacket and manifolding provided together with the B2H6, cooling circuit. Various start and operating performance projections were made for both the demonstrator hardware and flight design configurations.