METHOD FOR FILLING liquid oxygen oxidizer tank carrier rocket Aerospace Systems

摘要

FIELD: rocketry and space engineering. SUBSTANCE: proposed method includes filling of oxidizer tank of launch vehicle positioned horizontally with liquid oxygen at localization of gas volume of oxidizer tank which is in dynamic contact with liquid; prior to delivery of liquid oxygen to oxidizer tank, upper part of oxidizer tank shell is cooled by blowing it with cold nitrogen vapor fed to internal surface of shell to preset final temperature of cooling for reducing loads on structural members of oxidizer tank caused by temperature stresses arising at filling the oxidizer tank with liquid oxygen to magnitude of stresses not exceeding standard operational loads exerted on structural members of oxidizer tank; cold nitrogen vapor used for blowing the oxidizer tank shell are obtained through gasifying of liquid nitrogen at oxidizer tank inlet and removal of nitrogen vapor after blowing is performed from at least one end part of oxidizer tank. Cooling of upper part of oxidizer tank shell to preset temperature makes it possible to considerably reduce thickness of walls of oxidizer tank due to reduction of loads exerted on structural members of oxidizer tank caused by temperature stresses at filling the tank with liquid oxygen. Cold nitrogen vapor introduced at temperature equal to temperature of liquid nitrogen ensures considerable preliminary chilling of entire structure of oxidizer structure, thus considerably reducing losses of liquid oxygen at filling. EFFECT: increased mass of payload to be injected; reduction of loads on structural members of oxidizer tank. 3 dwg