随着现代亿亿次计算机发展，建立高效稳定运行于海量处理器核超大规模并行算法，解决航天飞行器离轨再入空气动力学难题，已成为载人航天工程轨控研制迫切希望解决的关键基础问题。项目研究提出描述大型复杂结构航天器再入飞行各流域高超声速流动输运现象统一的Boltzmann模型方程及数值求解格式并行计算数学模型，建立求解多相空间Boltzmann模型方程多层区域分解超大规模并行算法，发展具有高效率数据通信、浮点运算与自动容错功能的众核异构高性能并行计算平台，研制适于数万数十万以上CPU核求解大型航天器再入各流域复杂高超声速绕流问题可扩展并行计算软件及使用环境，结合发展DSMC及其与NS耦合并行算法、隐式GKS与UGKS方法及低密度风洞实验验证评估，研究揭示飞船返回舱再入、大型航天器寿命末期离轨陨落跨流域空气动力特性与复杂流动机理，形成依托国产100PF超级计算机多相空间Boltzmann模型方程高性能计算应用研究体系

With the development of modern billion-flops high-performance computer system, it has become a very important and key basic problem in orbit-control development of the manned space flight project how to establish a large-scale scalable parallel algorithm for efficient and stable operation of hundreds of thousands or more millions of processor cores and to solve the reentry aerodynamics problems around spacecraft covering flow regimes, which it has been being difficult for traditional research methods to compute in the aerospace field. The unified Boltzmann model equation in describing reentry hypersonic flow transport phenomena around large-scale and complex structure spacecrafts will be presented covering the full spectrum of flow regimes from high rarefied free-molecular flow to continuum in this project, and the mathematical model for parallel computation will be set up for the numerical schemes on the Boltzmann model equation. The large-scale parallel algorithm with multilayer domain decomposition for the Boltzmann model equation of multiphase space will be presented for 100PF level heterogeneous supercomputer. The high performance parallel computing platform with high efficient data communication, floating-point operations and automatic fault tolerance will be developed for multi-core heterogeneous CPU/GPU, and the large-scale scalable parallel computing software and application environment will be presented to solve the complex hypersonic aerothermodynamics problems covering the whole of flight regimes from outer space reentry for spacecrafts such as the re-entry module and TianGong craft. The proving and evaluating platform of the low-density wind-tunnel experiment, DSMC and NS coupled parallel algorithm, and implicit GKS and UGKS methods will be established for validation of the extreme-scale parallel computation in solving the Boltzmann model equation. The aerothermodynamics characteristics and complex flow mechanism of the re-entry module and large-scale spacecrafts will be revealed with massively parallel computation. The researching results of this project will form the high-performance computing core competitiveness in solving the Boltzmann model equation of multiphase space relying on our domestic 100P heterogeneous extreme-scale computer with independent innovation research characteristics in the international field.