FIELD: transport.
SUBSTANCE: invention relates to control over spacecraft inside medium parametres. Proposed device comprises flow booster feeding has flow with filter arranged on its inlet, gas ducts and thermostatic elements. Nose cone (NC) has two hatches arranged in NC top and bottom. Inner side of said hatches accommodates dissectors with openings made in their casings. Plates are arranged inside said dissectors to direct gas flow towards said openings. NC top dissector has three openings, two of them having their axes directed in opposite directions and perpendicular to NC axis. Third opening axis is directed parallel with HC axis towards rocket booster. HC bottom dissector has two openings with their axes directed similarly to two NC top openings. Ground device feeding gas component into spacecraft has gas ducts connected to NC branch pipes from outside. In compliance with proposed method, gas component is fed simultaneously into said dissectors. NC top plates and openings direct gas component flows into space under NC in three directions: two directions - long HC sides in opposite directions, third direction - towards rocket booster. NC bottom plates and openings direct gas component flow in two directions, similarly to aforesaid two directions. Gas component if ejected from spacecraft through hatches arranged at central and bottom rocket booster adapters.
EFFECT: normal thermal conditions, high purity of components below nose cone and inside rocket booster.
2 cl, 3 dwg
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