Definition of the design space in which convergence can occur with a combined cycle propulsion system

Previous papers provided an available energy basis for a Rocket Based Combined Cycle (RBCC) propulsion system analyses. The RBCC concept emerged from the advanced injector ramjet research of the early 1960's, so it is not a new concept. These available energy papers did not provide any insight...

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Bibliographic Details
Published in:Acta astronautica 1995-10, Vol.37, p.179-192
Main Author: Czysz, Paul A.
Format: Article
Language:English
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Summary:Previous papers provided an available energy basis for a Rocket Based Combined Cycle (RBCC) propulsion system analyses. The RBCC concept emerged from the advanced injector ramjet research of the early 1960's, so it is not a new concept. These available energy papers did not provide any insight into design convergence for a specific concept. If a propellant volume, based parametric payload sizing results, is introduced a convergence criteria emerges that can identify the airframe and propulsion parametric combinations that converge. Three principal findings from the previous papers are summarized. The existence of a criterion for determining design convergence is presented. Results from four individual parametric investigations are presented., 1) Configuration Concept Geometry, 2) Payload Weight/Propellant Volume, 3) Propulsion System Configuration and, 4) Conical Configuration Concepts.
ISSN:0094-5765
1879-2030
DOI:10.1016/0094-5765(95)00078-E