Study on Residual Propellant Vaporized in Tank of Some Launch Vehicle Third Stage
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摘要: 针对某火箭三子级剩余推进剂的汽化过程,建立了一个零维的数学物理模型.在给定太阳辐 射角的工况下,对贮箱中低温液体推进剂汽化时,贮箱内气体温度和压力变化、贮箱内质量 变化、进入贮箱的外界热流的变化及贮箱排放推力的变化等进行了数值计算,并对贮箱保险 活门排放推力对火箭在轨速度的极限影响作了简单分析.计算结果可进一步用于该火箭三子 级钝化技术的研究.Abstract: A zero-dimensional model was proposed to study on residual propellant vaporized in tank of some launch vehicle third stage. The assumptions used in the model and equations were given. By simulating the vaporization of cryogeni c propellant under given solar radiation angel, the variation of gas temperature, pressure and mass in tank, as well as ingoing heat flow and exhaust thrust, were calculated. A brief analysis of the rocket velocity change due to exhaust th rust shows the influence is inconsiderable, and the numerical results might be u seful to study the passivation technology of the launch vehicle further.
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Key words:
- heat transfer /
- passivation /
- vaporization /
- numerical simulation /
- residual pro pellant
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