摘要
针对推进剂在轨加注任务中,接受贮箱内气液位置不确定,排气和质心控制困难的问题,以NASA的FARE II试验中的贮箱为参考,根据表面张力贮箱相关理论,建立计算模型.采用数值模拟的方法,对不同加注流量条件下,叶片式表面张力贮箱内气液分布进行研究.运用Fluent流体仿真软件,以肼为工质,对叶片式表面张力贮箱在轨加注过程进行数值模拟.仿真结果表明:加注流量越大,贮箱中部气液界面凸起越高;当加注流量超过临界值,流入的推进剂经过排气管排出.研究结果对于叶片式贮箱在轨加注过程中的流量控制具有参考价值.
In the microgravity environment, the position of the ullage bubble is uncertain. It＇ s hard to vent and control the center of mass for the receiver tank on mission of onorbit refilling. The test tank of NASA FARE II is taken as reference. According to the theory of surface tension tank, calculation model is established. Under the conditions of different refill flow rates, the gasliquid distribution in the vane type surfacetension tank is studied with the method of numerical simulation. The hydrazine is chosen as working liquid. Using the CFD（computational fluid dynamics） software Fluent, the process of vanetype tank onorbit refilling is simulated. Simulation results show that the greater the inflow rate is, the higher the gasliquid interface protrudes. When the inflow rate exceeds the critical value, liquid is vented. The results can provide reference for the control of refill flow rate.
出处
《空间控制技术与应用》
2013年第6期17-22,共6页
Aerospace Control and Application
基金
国家重点实验室基础研究资助项目
关键词
在轨加注
表面张力贮箱
叶片
推进剂管理装置
数值模拟
on-orbit refill
surface-tension tank
vane
propellant management device
numerical sim-ulation
