返回舱再入跨流域气动及配平特性数值研究  

Numerical simulation of aerodynamic and trim characteristics across different flow regimes for reentry module

作　　者：梁杰[1] 李志辉[1] 李齐[2] 杜波强[1] LIANG Jie;LI Zhihui;LI Qi;DU Boqiang(Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China;Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,四川绵阳621000 [2]北京空间飞行器总体设计部,北京100094

出　　处：《空气动力学学报》2018年第5期848-855,共8页Acta Aerodynamica Sinica

基　　金：国家重点基础研究发展计划(2014CB744100);国家自然科学基金(91530319;11325212)

摘　　要：基于直接模拟蒙特卡罗(DSMC)方法,发展流场直角与表面三角形非结构混合网格生成方法和网格自适应技术,构造适于高稀薄流到近连续滑移流多流区共存的变时间步长模拟策略及DSMC区域分解并行计算方案。采用经改进的DSMC方法模拟飞船返回舱再入过程130～70km跨越外层空间自由分子流到稀薄过渡近连续流区热化学非平衡流动,研究分析了跨流域激波过渡带和边界层的强扰动演变规律以及稀薄气体效应、高温真实气体效应对返回舱气动特性和配平特性的影响规律。对比分析了不同壁面反射模型对返回舱配平特性的影响特点,计算的探月试验返回器配平迎角与飞行试验数据一致。计算分析了质心位置偏移对配平迎角的影响机制。计算结果表明:稀薄气体效应和壁面反射模型对90km以上高度的气动力和配平特性影响显著,真实气体效应则对90km以下高度的气动特性影响较大,质心横向偏移对配平迎角影响较大。The direct simulation Monte Carlo(DSMC)method is performed to simulate the thermochemical non-equilibrium flow from 130 km to 70 km across outer space free molecular,rarefied transitional and near-continuum regime during the reentry module entering the atmosphere.The developed hybrid spatial Cartesian and unstructured triangular surface meshes and adaptive refinements are used in the computation.The variable time step simulation strategy for the coexistence of high rarefied flow to near-continuum flow and domain decomposition parallel DSMC algorithm are established to investigate the evolution of shock wave layer and boundary layer across different flow regimes.The effects of rarefied gas and high temperature real gas on module aerodynamic and trim characteristics are simulated and analyzed.The impacts of different surface reflection model and mass center location offsets on the trim property are also computed and analyzed.The calculated trim angles of attack have good agreement with the flight data for lunar explanation test reentry module.The computation results show that the rarefied gas effects and surface reflection model have significantly impact on aerodynamic and trim characteristics above altitude of 90 km.The real gas effects have great impact on aerodynamics below altitude of 90 km.The lateral offset of centroid has a larger impact on the trim angle of attack.

关 键 词：跨流域 配平特性 DSMC 真实气体效应 飞船返回舱 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]