| 摘要 |
A device for filling a spacecraft propulsion system with xenon comprises a ground refueling tank connected to a filling tank of a spacecraft by a line, wherein a pumping device is installed with one-way non-return valves at inlet and outlet and a pneumatic actuator connected to a pressure source through an electro-pneumatic valve, pipes, throttles and a weigher. The ground refueling tank and a pumping device are installed on the weigher, wherein the pumping device is designed as two coaxial cylinders, whose pistons are connected by a common rod, which passes through a partition with a seal, which divides the cylinders, each piston divides the cylinder into two corresponding cavities of variable volume, each cavity from both sides of the piston of one cylinder is equipped with inlet and outlet check valves, and each cavity of the second cylinder is connected via electro-pneumatic valves to a pressure source. |
