FIELD: astronautics.
SUBSTANCE: invention relates to rocket fuel (RT) systems of spacecraft (SC). SC RT power supply system comprises airborne device (100) including housing (110) with supply port (112) leading to side tank (120), and valve (134) configured to selectively overlap or open said supply port (112), and ground device (200) comprising pipeline (210) with free end (212), control body (240) surrounding said free end (212) of pipeline (210) and provided with drive (250). Airborne device (100) and ground device (200) are connectable so as to allow the rocket fuel to be pumped from supply line (210) to side tank (120) in the open configuration, and insulate side tank (120) from pipeline in closed configuration (210). Actuator (250) is configured to control the opening and closing of power supply port (112) by valve (134). Actuator (250) surrounds the outer periphery of power pipeline (210).
EFFECT: reduced filling time of the on-board tank with reduced head loss.
9 cl, 2 dwg
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