李志辉, 梁杰, 李中华, 李海燕, 吴俊林, 戴金雯, 唐志共. 跨流域空气动力学模拟方法与返回舱再入气动研究[J]. 空气动力学学报, 2018, 36(5): 826-847. DOI: 10.7638/kqdlxxb-2018.0121
引用本文: 李志辉, 梁杰, 李中华, 李海燕, 吴俊林, 戴金雯, 唐志共. 跨流域空气动力学模拟方法与返回舱再入气动研究[J]. 空气动力学学报, 2018, 36(5): 826-847. DOI: 10.7638/kqdlxxb-2018.0121
LI Zhihui, LIANG Jie, LI Zhonghua, LI Haiyan, WU Junlin, DAI Jinwen, TANG Zhigong. Simulation methods of aerodynamics covering various flow regimes and applications to aerodynamic characteristics of re-entry spacecraft module[J]. ACTA AERODYNAMICA SINICA, 2018, 36(5): 826-847. DOI: 10.7638/kqdlxxb-2018.0121
Citation: LI Zhihui, LIANG Jie, LI Zhonghua, LI Haiyan, WU Junlin, DAI Jinwen, TANG Zhigong. Simulation methods of aerodynamics covering various flow regimes and applications to aerodynamic characteristics of re-entry spacecraft module[J]. ACTA AERODYNAMICA SINICA, 2018, 36(5): 826-847. DOI: 10.7638/kqdlxxb-2018.0121

跨流域空气动力学模拟方法与返回舱再入气动研究

Simulation methods of aerodynamics covering various flow regimes and applications to aerodynamic characteristics of re-entry spacecraft module

  • 摘要: 针对回收类航天器(返回舱)再入过程所遇跨流域多尺度非平衡绕流问题,综述基于Boltzmann方程碰撞积分物理分析与可计算建模,构造考虑完全气体、转动非平衡、含振动能激发热力学非平衡效应各流域统一Boltzmann模型方程,及由此建立返回舱再入气动力热绕流问题气体动理论统一算法研究进展与算法检验。作为方法兼验证结合,进一步简述了融合再入热化学稀薄气体电离非平衡流动DSMC方法、近连续过渡流区N-S/DSMC耦合算法、经滑移边界修正的N-S方程解算器、低密度风洞实验测试等多种空气动力学模拟手段,建立求解Boltzmann模型方程气体动理论统一算法(GKUA)、DSMC、N-S/DSMC、滑移N-S解算器、低密度风洞实验验证补充,适于返回舱再入从外层空间自由分子流到近地面连续流跨流域空气动力学一体化模拟平台。将此平台用于再入H=110~30 km各流域球体、高超声速尖前缘中空柱裙、返回式卫星球锥体、飞船返回舱稀薄过渡流以至近连续流区气动力/热与姿态配平绕流问题计算与实验分析比较,证实统一算法在高稀薄流区,与DSMC吻合很好;在连续流区,与(滑移)N-S解算器相一致;在中间过渡带,与N-S/DSMC耦合算法相容;具有全飞行流域很好的计算一致收敛性。简述了跨流域空气动力学几种模拟手段的适应性特点与展望,揭示了返回舱再入跨流域复杂高超声速流动变化规律。

     

    Abstract: In view of the multi-scale non-equilibrium flows around the re-entry spacecraft (module) during re-entering process, the physical analysis and computable modelling of the collision integral based on the Boltzmann equation are summarized. The unified Boltzmann model equation is constructed with the consideration of the complete gas, the rotational non-equilibrium, and the thermodynamic non-equilibrium effects involving in vibrational energy excitation. And then, the gas-kinetic unified algorithm (GKUA) and the parallel computing platform for the re-entry aerothermodynamics and flows of spacecraft re-entry module are established. As verification and combination of different methods, the DSMC method for re-entry non-equilibrium flow of thermo-chemical ionized gas, the N-S/DSMC hybrid algorithm in the near-continuum transitional flow regimes, the N-S equation solver modified by the slip boundary flow theory, the low-density wind tunnel experiments and so on are briefly described, and the integrated simulation platform has been established for aerodynamics covering various flow regimes from the outer space free-molecule flow to the near-ground continuum flow based on the verification and supplement of the GKUA, DSMC, N-S/DSMC, slip N-S solver and the low-density wind tunnel test. This platform is used to compute the rarefied transition flows around the sphere during the re-entry from H=110~30 km, the hypersonic tip front edge hollow column skirt, and the comparative analysis of the computation and experiment for the aerothermodynamics and attitude-balance flow problems of the spacecraft capsule. It is proved that the unified algorithm is in good agreement with the DSMC in the high rarefied flow regime, and also consistent with the (slip) N-S solver in the continuum flow regime. And the GKUA is also consistent with the N-S/DSMC algorithm in simulating the flows from the intermediate transition flow regime, and the GKUA has the coincident convergence in solving the flows from the whole flight flow regimes. The adaptability characteristics and prospects of several simulation methods for aerodynamics covering various flow regimes are briefly described, and the varying law of complex hypersonic flows is revealed during the re-entry process of the re-entry module.

     

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