FIELD: space engineering. SUBSTANCE: proposed method includes filling oxidizer tank with supercooled oxygen fed to lower part of oxidizer tank at localization of vapor-and-gas space in cavity of front part of oxidizer tank; this space is in dynamic contact with liquid oxygen; then, oxygen is drained from oxidizer tank to additional cryogenic reservoir for maintaining excessive pressure in it corresponding to standard pressure in oxidizer tank. Supercooled oxygen is delivered to oxidizer tank in order to obtain temperature at oxidizer tank outlet below preset temperature of liquid oxygen before air start of launch vehicle by magnitude of heating oxygen in oxidizer tank till moment of launch vehicle landing, after which additional cryogenic reservoir is disconnected. In the course of injection of launch vehicle to altitude of air start, helium is periodically fed to cavity of front part of oxidizer tank at bubbling it through liquid oxygen and simultaneous discharge of vapor-and-gas mixture, thus making it possible to obtain temperature state of liquid oxygen in oxidizer tank sufficient for reliable start of liquid propellant engine of launch vehicle. EFFECT: improved operating properties of system; increased mass of payload. 1 dwg
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Authors
Dates
2003-07-20—Published
2001-09-17—Filed