Computation of cryogenic propellant discharge under zero gravity conditions
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摘要: 针对CZ-3A系列运载火箭三子级低温贮箱内剩余推进剂排放问题,分别对排放过程中液氢和液氧低温推进剂沿2种不同排放管的流动进行了一维数值计算和分析.计算中认为在排放时沿管路压强降低,从而引起液体推进剂气化,并在管路的某个位置出现气固两相或者全部气化,在计算中,根据不同位置时推进剂的不同状态,分别采用液相、气液两相、气固两相及气相的物理数学模型和控制方程.计算得出了排放的出口参数及排放性能,认为液氢从通道1排放比较好,液氧从通道2排放比较好.为进一步进行排放研究提供了依据.Abstract: The discharge research of the residual cryogenic propellant used in the CZ-3A third sub class was studied. The liquid hydrogen and liquid oxygen cryogenic propellant flow inside of the two different discharge pipeline was calculated. The liquid propellant will be vaporized, which attributes to the pressure depression along the pipeline. The gas-solid or the pure gas flow appears at a certain location. According to the each case of the flow, the model and the control equations of pure liquid, gas-liquid, gas-solid and pure gas was used respectively. The results show the pipe 1 is better when the liquid hydrogen is discharged and the pipe 2 is better when the liquid oxygen is discharged. The flow parameter at the pipeline exit through calculation is useful for further study.
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Key words:
- launching vehicles /
- cryogenic propellants /
- two-phase mixtures /
- blowdown
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