Review of principal issues governing feasibility of resuable launch vehicle systems, i.e., propulsion, structural weights, heat protection, and costs, is presented; dependence on flight Mach number of fuel specific impulse of airbreathing propulsion systems (turbojets, ramjets, and scramjets) is reduced to dependence on staging velocity of effective specific impulse values, including flight losses, to provide performance relations for preliminary design use; configurations of rocket and airbreathing reusable vehicles are selected and structural weights are characterized in terms of specific surface weights.
Reusable space launch vehicle concepts -- Outlook 1965
SAE -- Paper
SAE Meeting ; 1965 Launching
1965
17 pages
Conference paper
English
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