The performance potential of a group of rocket air-breathing hybrid propulsion systems was compared with the performance parameters of simple or pure propulsion systems. A general numerical comparison method which uses a series of subprograms for the various system components was developed. The pure propulsion systems were calculated as limit cases of the general hybrid system with the same programs and assumptions. The emphasis was on the aerothermodynamic design performance analysis of hybrid systems with subsonic internal flow. Typical performance curves are given for a wide range of flight conditions. It is shown that the air-turbo-rocket cycle is probably the most promising for the first phase of the high thrust trajectory single-stage space transporter. The second propulsion phase favors the ramjet mode although the competitive ramjet-rocket mode has to be considered. The final operation mode has to be that of the rocket. The separate propulsion components for these operation modes could be integrated into a single system.
Integrated Turboramjet-Rocket Performance Potential: Project Itustra
1976
27 pages
Report
Keine Angabe
Englisch
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