A single metric for judging between two candidate propellant combinations for a given application is sought. By using the ideal rocket equation, the essential link between propellant density and specific impulse as the two primary performance drivers can be demonstrated.
Rho-Isp Revisited and Basic Stage Mass Estimating for Launch Vehicle Conceptual Sizing Studies
AIAA Propulsion and Energy Forum 2015 ; 2015 ; Orlando, FL, United States
2015-07-27
Conference paper
No indication
English
British Library Conference Proceedings | 2015
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