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- W162858826 abstract "Three primary elements determine launcher size and weight. These are the configuration concept, the propulsion concept and the industrial material/fabrication capability. These three can be represented as a sizing index [P. Czysz, C. Bruno, K. Kato, Interactions between propulsion systems and the configuration concepts defines the design space, AIAA-2001-1924, 10th International Space planes and Hypersonic Systems and Technologies Conference, Kyoto, Japan, April 2001]. For a given industrial materials/fabrication capability, the configuration and propulsion concepts interact directly. One method identifying the solution space for each combination of parameters is discussed in the 10th International Space Planes and Hypersonic Systems and Technologies Conference in Kyoto, Japan in April 2001. A significant number of propulsion system concepts have been studied and reported. This paper focuses on those that are applicable to launch vehicles. Each propulsion system concept is briefly described and accompanied by a sketch. The intent is to show weight ratio and the onboard oxygen carried by the vehicle drive this direct interaction. The lesser the weight ratio and the smaller the oxygen-to-fuel ratio, the smaller is the size and gross weight of the vehicle. D 2003 Lister Science." @default.
- W162858826 created "2016-06-24" @default.
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- W162858826 date "2002-01-01" @default.
- W162858826 modified "2023-09-23" @default.
- W162858826 title "Perspective of Launch Vehicle Size and Weight Based on Propulsion System Concept" @default.
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