微重力条件下卫星贮箱中的推进剂管理问题

微重力条件下贮箱中液体管理的主要问题是控制液体推进剂在箱中的位置,保证向发动机输送不含气泡的推进剂.对用于自旋稳定卫星的梨形贮箱,在透明的有机玻璃缩比模型中用去离子水作试验介质进行落塔试验.在弹星分离以后,卫星自旋以前通过落塔试验确定气液界面的形状,排出液体时夹气现象和发生夹气时剩余液体的体积,试验为贮箱设计提供可靠的依据.在长寿命的卫星上将采用一种大型表面张力贮箱,在微重力条件下将要进行相关的液体流动特性试验,如气液界面的平衡位置,挤出效率,液体流动的阻力损失,流体的晃动等,验证设计的合理性.

PROPELLANT MANAGEMENT FOR SATELLITE PROPULSION SYSTEM UNDER MICROGRAVITY

Under microgravity condition, the main problem about liquid propellant management is to control the position of the liquid in the tank,so that the gas-free liquid propellant transfered to the engine is gas-free. For a kind of pear-shaped tank used in a spinnig stabilization satellite,a drop tower test was performed with ionless water as test media in a transparent plexiglass scale model. The interface shape between gas and liquid at the time after satellite saperating from the launcher and before the saellite spinning, the gas ingestion phenomena during liquid draining and the critical volume of the residue liquid when gas ingestion begin, to happen are determined by tests.A kind of large scale surface tension tank will be used in long life time satellite. Some fluid flow characters concerned will be tested under microgravity condition such as equilibrium position of the gas-liquid interface,expulsion efficiency,pressure loss and liquid slosh etc. to verify the design option.