| 王亿明,周柯江,张东东,范书立,李京杰.基于LS-DYNA的火箭发动机喷管流场数值模拟与验证[J].计算力学学报,2025,42(2):285~291 |
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| 基于LS-DYNA的火箭发动机喷管流场数值模拟与验证 |
| Numerical simulation and verification of rocket engine nozzle flow field based on LS-DYNA |
| 投稿时间：2023-09-16 修订日期：2023-12-25 |
| DOI：10.7511/jslx20230916006 |
| 中文关键词: 火箭发动机 喷管流场 数值模拟验证 LS-DYNA软件 CE/SE方法 |
| 英文关键词:rocket engines nozzle flow field numerical simulation verification LS-DYNA CE/SE method |
| 基金项目:国家自然科学基金(92166106)资助项目. |
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| 摘要点击次数: 8 |
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| 中文摘要: |
| 为了探究火箭发动机喷管的流场特性以及速度变化趋势,采用了LS-DYNA软件中CE/SE求解器,验证了来自于NPARC验证与确认算例库中的超声速轴对称喷管(收缩-扩张型喷管)的相关参数。本文试验媒介为空气,在喷管马赫数为2.22完全膨胀的情况下,对喷管中心线速度和中心线上各点处的截面速度进行了数值模拟,并将模拟结果与试验结果对比。结果表明,CE/SE方法能够较好地预测喷管内的流动分布和关键参数,其计算结果和速度变化趋势与试验数据高度吻合,且与实验数据相差10%以内,有效验证了该方法计算火箭发动机喷管流场的可行性,未来可以进一步深入探索和优化该方法。 |
| 英文摘要: |
| n order to investigate the flow field characteristics and velocity variation trend of rocket engine nozzles,the CE/SE solver in LS-DYNA software was used to verify the relevant parameters of supersonic axisymmetric nozzles(shrinking-expanding nozzles) from the NPARC verification and validation example library.In this paper,the test medium is air.Under the condition of perfect expansion at Mach number 2.22,the center line velocity of the nozzle and the cross-section velocity at each point on the center line are numerically determined,and the simulation results are compared with the test results.The results show that LS-DYNA software can accurately predict the flow distribution and key parameters in the nozzle,and the calculated results and the velocity variation trend are highly consistent with the experimental data,and the difference between them and the experimental data is less than 10%,which effectively verifies the feasibility of the LS-DYNA software to calculate the flow field of the rocket engine nozzle and the method can be further explored and optimized in future studies |
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