Abstract: The future propulsion system needs to adapt to large acceleration environment and have the refueling capacity with large filling volume. Therefore, it is very important for the overall design of aircraft to research the propellant management characteristic of spacecraft tank at a large acceleration environment. In this paper, the limit management performance of a vane type surface tension tank is studied by numerical methods. The gas liquid distribution in the tank and the liquid level curves of the propellant are analyzed. The diversion capacity of parallel vanes under a large acceleration is calculated, and the influence of vane width and clearance distance on the diversion performance is studied. The numerical simulation results show that increasing the vane width and decreasing the clearance distance between the vane and tank shell can improve the diversion effect at 10-2 g acceleration. The research results of this paper can provide theoretical reference for the optimal design of vane type surface tension tanks.

Key words: surface tension tank, parallel vanes, gravitational acceleration, numerical simulation, limit diversion capacity