ROCKET BOOSTER Russian patent published in 2011 - IPC B64G1/22 

FIELD: transport.

SUBSTANCE: invention relates aerospace engineering, namely, to design of rocket boosters. Proposed booster comprises housing consisting of top adapter, medium adapter and bottom adapter, oxidiser tank with main bulkheads and intake device, fuel tank, intertank frame, sustainer, instrumentation thermostatic control devices, extra self-contained propulsion unit of orientation and launching operated on high-boiling toxic components. Top adapter accommodates instrumentation frame with its top bulkhead supporting spacecraft. Instrumentation frame accommodates control system instruments, chemical current source, instrumentation thermal control devices, telemetry system with feeders. Instrumentation containers are communicated via pipeline with fuel tank. Kerosene is used as heat carrier, while thermal control appliance have their outlet communicated by return pipeline with fuel tank. After thermal control of instruments, kerosene of forced back into fuel tank to be used as propulsion unit fuel, while auxiliary orientation and launching propulsion unit uses main fuel components: kerosene and gaseous oxygen. During flight, charging by gaseous oxygen is carried out via charging pipeline that communicates sustainer with auxiliary propulsion unit. Kerosene flows into extra propulsion unit via fuel pipeline communicating fuel tank with extra propulsion unit. Oxidiser tank inner space, in the area of intake device, has additional bulkheads. Intake device supports hydraulic lock turret to allow oxidiser collection into intake device area to start sustainer at minimum fuel consumption at final stage of booster operation.

EFFECT: improved weight-and-power characteristics of proposed booster.

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