METHOD FOR PROVISION OF THERMAL CONDITIONS OF HEAD UNIT AS PART OF SPACE ROCKET AND DEVICE FOR ITS REALIZATION

FIELD: rocket-space engineering, applicable in the conditions of formation of fire-hazardous gas mixtures in the head unit cavities, for example, at leakages or drainages of propellant components) liquid oxygen and hydrogen). ^ SUBSTANCE: the method consists in supply of the thermostatting neutral gas component to the upper part of the head unit, its ejection from the middle and lower parts of this unit. Prior to ejection, the speed of the neutral gas component is increased to the values making it possible to overcome the tendency of the fire-explosion-hazardous component to oppose the motion of the neutral gas component, entrap the fire-explosion-hazardous components and form with it a mixture with a fire-explosion-proof concentration. The offered device has a filter, flow rate stimulator, gas passages and thermostatting elements of the neutral gas component supplied to the head unit. The head unit has a screen convex towards the accelerating unit and having in annular gap with the nose cone for increasing the speed of the neutral component. The screen assists the motion of the fire-explosion-hazardous component through its release ports to the screen periphery. The mixture of the neutral and fire-explosion-hazardous gas components is evacuated through the drainage devices in the middle and lower parts of the head unit. ^ EFFECT: provided safety of the head unit, for example, at filling of the space vehicle and/or accelerating unit with fire-explosion-hazardous components before launching with simultaneous provision of its thermal conditions as part of the space rocket. ^ 2 cl, 1 dwg