METHOD OF SUPPORT OF THERMAL CONDITIONS AND PURITY OF SPACE ROCKET HEAD MODULE AND DEVICE FOR REALIZATION OF THIS METHOD

摘要

FIELD: control of parameters of surrounding medium for such launch vehicles as SOYUZ, ZENIT-3 SL (sea launch), PROTON.;SUBSTANCE: proposed method includes cyclic delivery of gas to head module and evacuation of gas from head module. Direction of gas flow is changed in torn. At last cycle after obtaining the required purity of gas, it is fed to upper part of head module and is evacuated from its lower part. Excessive pressure of gas is maintained in head module. Device proposed for realization of this method has filters, units for delivery of gas to head module and thermostatting members. It is also provided with unit for control of direction of gas flow which is connected with thermostatting members and with gas discharge valves; devices for monitoring gas purity are mounted on gas lines. Gas discharge valves are connected to upper and lower gas flow splitters by means of gas lines. End face of head module is provided with cover.;EFFECT: enhanced purity of head module; avoidance of penetration of atmospheric air into head module; enhanced fire safety and moisture proofness.;3 cl, 1 dwg