One technology for a fully reusable and permanently space-based cryogenic upper stage rocket is the use of liquid hydrogen and liquid oxygen propellants in less than atmospheric condition - a 'low vapor pressure' system. This enables lighter-weight tank shells and higher density fluids, two features that can reduce the quantity of costly propellants consumed by the vehicle in performing a payload delivery mission. The fluids must have their saturation conditions lowered from the levels produced today. This paper discusses five conditioning alternatives and assesses important issues relevant to structural design of very-thin-gauge tanks: e.g. fracture mechanics, thin-gauge formability, inspection, and weights. An important conclusion is that significant structural inert weight can be saved with further manufacturing technology development of large-scale, thin-gauge shells.
An analysis of a low-vapor-pressure cryogenic propellant tankage system
Analyse eines Tanksystems fuer Fluessiggastreibstoffe mit niedrigem Dampfdruck
AIAA-Papers ; Jul ; 1-12
1987
12 Seiten, 18 Bilder, 2 Tabellen, 14 Quellen
Aufsatz (Konferenz)
Englisch
NTRS | 1966
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