FIELD: aviation.
SUBSTANCE: invention relates to fuel supply systems in the spacecrafts (SC) in zero-gravity conditions. The device for selection of fuel from SC tanks in zero-gravity conditions for liquid rocket propulsion system comprises tanks of fuel components in the from of rotary body and local system of fuel liquid components selection with capillary intake device of the capacitive type positioned on the axis in each tank near one of its inside walls. Fuel component continuity sensor connected to the control system is mounted at the output of the capillary intake device. Auger is mounted inside the tank for rotation about an axis of the tank. Due to its rotation the auger transmits mechanical impulse to the remnants of the fuel components positioned outside the capillary intake device towards the capillary intake device and provides filling it with fuel before the device trigger time.
EFFECT: increased reliability of device for fuel selection.
3 cl, 1 dwg
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