基于不同相变模型的微重力液氢贮箱内压力与温度分布仿真预示
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摘要
受空间热流的作用,相变是低温推进剂在轨压力控制中需要被考虑到的影响因素。为研究液氢贮箱内的流体行为特性,建立了低温流体CFD仿真模型,对于相变过程,基于不同的相变传质理论,建立了四种相变仿真模型。根据NASA开展的AS-203液氢贮箱压力上升试验数据,对封闭贮箱内压力上升和温度分布开展仿真预示,分析了不同相变仿真模型对压力上升和温度分布预示的结果。结果表明,相变模型1和相变模型3得到的压力上升速率和温度场结果与试验结果趋势较为一致。受到算法和适用性的影响,相变模型2和相变模型4对AS-203液氢贮箱的温度预示偏差较大,相变模型4对压力上升的预示偏差较大。
Phase change is an important factor in cryogenic propellant pressure management on-orbit due to the heat flux from space. A cryogenic fluid CFD simulation model was established to study the characteristics of the fluid behavior in the liquid hydrogen tank. In addition,four phase change simulation models were also established according to the different phase change theories. Based on the NASA AS-203 experimental data,simulations were conducted for the self-pressurization and temperature distribution in a closed tank and the simulation results with different models were compared.The results showed that for model 1 and model 3,the predicted self-pressurization rates and ullage temperature at discrete locations were in good agreement with the experimental data. However,model 2 and model 4 underestimated the ullage temperature,and model 4 underestimated the self-pressurization rate due to the algorithm and adaptability reasons.
Phase change is an important factor in cryogenic propellant pressure management on-orbit due to the heat flux from space. A cryogenic fluid CFD simulation model was established to study the characteristics of the fluid behavior in the liquid hydrogen tank. In addition,four phase change simulation models were also established according to the different phase change theories. Based on the NASA AS-203 experimental data,simulations were conducted for the self-pressurization and temperature distribution in a closed tank and the simulation results with different models were compared.The results showed that for model 1 and model 3,the predicted self-pressurization rates and ullage temperature at discrete locations were in good agreement with the experimental data. However,model 2 and model 4 underestimated the ullage temperature,and model 4 underestimated the self-pressurization rate due to the algorithm and adaptability reasons.
引文
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[2]Hasan M M,Lin C S.Tank pressure control experiment:thermal phenomena in microgravity[R].NASA TP 3564,1996.
[3]Ward W D,Tool L E,Ponder C A,et al.Evaluation of AS-203low-gravity orbital experiment[R].NASA CR 94045,1967.
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[5]Aydelott J C.Normal gravity self-pressurization of 9-inch(23cm)diameter spherical liquid hydrogen tankage[R].NASA-TN-D-4171,1967.
[6]Li Z,Xu L,Sun H,et al.Investigation on performances of non-loss storage for cryogenic liquefied gas[J].Cryogenics,2004,44(5):357-362.
[7]Grayson G D,Lopez A,Chandler F.O.Cryogenic tank modeling for the saturn AS-203 experiment[C]//Sacramento:42th AIAA/ASME/SAE/ASEE Joint Propulsion Conference&Exibit,2006.
[8]Barsi S,Kassemi M.Numerical and experimental comparisons of the self-pressurization behavior of an LH2 tank in normal gravity[J].Cryogenics,2008,48(3):122-129.
[9]程向华,厉彦忠,陈二锋,等.新型运载火箭射前预冷液氧贮箱热分层的数值研究[J].低温工程,2008,42(9):1132-1136.Cheng Xianghua,Li Yanzhong,Chen Erfeng,et al.Numerical investigation of thermal stratification in liquid oxygen tank for new-style launch vehicle during ground precooling[J].Journal of Xi’an Jiaotong University,2008,42(9):1132-1136.(in Chinese)
[10]李佳超,梁国柱.地面及微重力条件下低温贮箱内相变和传热的数值仿真[J].空间科学学报,2016,36(4):513-519.Li Jiachao,Liang Guozhu.Numerical simulation of phase change and heat transfer in cryogenic tank under the ground and microgravity condition[J].Chinese Journal of Space Science,2016,36(4):513-519.(in Chinese)
[11]ANYSYS FLUENT 14.0 Theory Guide[M].Canonsburg,PA,2011:501-511.
[12]Tanasawa I.Advances in condensation heat transfer[J].Advances in Heat Transfer,1991,21:55-139.
[13]刘秋生,汪洋,纪岩.蒸发相变与界面流动耦合机理研究[J].工程热物理学报,2010(10):1751-1754.Liu Qiusheng,Wang Yang,Ji Yan.Coupling mechanism of evaporationphase-change and interfacial flow[J].Journal of Engineering Thermophysics,2010(10):1751-1754.(in Chinese)