| 摘要 |
<p>The invention relates to space rockets and can be used in the production of all-azimuth rockets to put space vehicles onto reference orbits. The booster includes a body which contains tanks for oxidant and for fuel, a shroud for the nose section, an intertank section and a tail section, a rocket engine, an integrally rotatable wing which is directed in the axis of the accelerator during the launching stage and is directed at 90° during re-entry, a three-point landing system and a docking unit for docking with the second stage of the launcher. The booster is provided with air-breathing engines having air intakes and gas pipes with ejection nozzles protruding outside the outline. The fuel system includes tanks in the wing and consumable and balancing tanks in the nose section. The wing is mounted on the upper surface of the booster body, in the region of the intertank section. The horizontal stabilizer has the form of a surface consisting of two rotatable integral outer wings with a low negative V angle, whereby the vertical stabilizer has the form of a fin with a rudder. The cap is provided with a rotary plug for air intake.</p> |
