| 摘要 |
FIELD: space.SUBSTANCE: invention relates to aerospace engineering and can be used in engines of space objects. System for withdrawal of fluid in rocket engine comprises tank with lower bottom with pit, flow control valve with additional cavity, intake, fasteners. Pit is made in form of large spherical cover changing into small spherical shell with flange delivery, and comprises support platform with a hollow sphere with welded ribs, brackets, perforated spherical shell. Intake device comprises stacked upper flat ring and lower ring with central holes arranged on a common axis, ribs, sleeves, filtration element made two circuits, comprises circular meshed grid, annular mesh catcher.EFFECT: invention improves reliability of propulsion plant of space object and reducing weight of propulsion plant of space object.2 cl, 4 dwg |
