СПОСОБ ОБЕСПЕЧЕНИЯ ТЕПЛОВОГО РЕЖИМА ГОЛОВНОГО БЛОКА В СОСТАВЕ РАКЕТЫ КОСМИЧЕСКОГО НАЗНАЧЕНИЯ И УСТРОЙСТВО ДЛЯ ОСУЩЕСТВЛЕНИЯ СПОСОБА

摘要

FIELD: rocketry and space engineering; control of formation of explosive gas mixtures and mixtures presenting fire hazard due to leakage or drainage of propellant components (liquid oxygen and hydrogen). ^ SUBSTANCE: proposed method includes delivery of neutral thermostatting gas component to head module. This component is delivered to upper part of spacecraft simultaneously with discharge from its lower part and to lower part of cryogenic stage at discharge from its upper part. Gas component outlet is closed on side of end section of head module by launch vehicle coupled to it. Device proposed for realization of this method includes filter, flow activator, gas lines for delivery of neutral gas component and thermostatting elements. Head module is provided with partition forming closed cavities of cryogenic stage and spacecraft. Partition is convex towards spacecraft and is brought in contact with head fairing through sealing member. Evacuation of mixture of neutral gas component and explosive components is performed through discharge gas duct communicating the cryogenic stage cavity with atmosphere. ^ EFFECT: enhanced safety of head module at filling the spacecraft and/or cryogenic stage with explosive and combustible components before launch. ^ 3 cl, 1 dwg