The large area-ratio nozzles are for a lightweight rocket motor thrust chamber construction such as is disclosed in patent No. 2,943,442. The thrust chamber is composed of a combustion chamber, a throat, and a nozzle portion. The nozzle portion is formed of a compound wall having radially spaced inner and outer surfaces formed from a plurality of elongated compound channel members disposed in contiguous side-by-side relation to define an internal annular chamber.
Rocket Thrust Chamber
1965
1 pages
Report
Keine Angabe
Englisch
NTRS | 1965
|Advanced Rocket Thrust Chamber Technology
NTIS | 1970
|Advanced tube-bundle rocket thrust chamber
NTRS | 1990
|Advanced tube-bundle rocket thrust chamber
NTRS | 1990
|