论文部分内容阅读
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.
The main problem with liquid management in tanks under microgravity conditions is to control the position of the liquid propellant in the tank and to ensure the delivery of a bubble-free propellant to the engine.For pear-shaped tanks for spin-stabilized satellites, In the plexiglass reduction ratio model, deionized water was used as the test medium to conduct the drop test.After the separation of the asteroid, the shape of the gas-liquid interface was confirmed by the satellite spin-down test before the spin-on test, The volume of remaining liquid, the test provides a reliable basis for the design of the tank in the long-lived satellite will use a large surface tension tank, under the conditions of microgravity will be related to the liquid flow characteristics of the test, such as the gas-liquid interface Balance position, extrusion efficiency, resistance loss of liquid flow, fluid sloshing, verify the rationality of the design.