火星是距离地球最近的行星，目前各国的深空探测计划都将火星进入、火星取样返回等任务纳入规划。火星进入探测器面临严峻的气动热环境，须对其设计有效的热防护系统。与地球大气不同，火星大气密度较低且含有高浓度的CO₂，其进入过程存在更为显著的热化学非平衡效应；此外，火星会存在不同程度的沙尘暴，持续时间长且覆盖了探测器的下降高度，对探测器造成额外的侵蚀损伤，给探测器的热防护系统设计带来巨大挑战。为了对飞行器进入过程中含尘流场有更加深入的认识，本文采用数值模拟法方法，针对飞行器含颗粒高速气体来流开展气固耦合问题研究。本文主要研究内容概括如下：

1. 发展了二维轴对称五组分CO₂热化学非平衡计算程序，并针对不同运行工况下的飞行器外流场进行数值模拟计算，与该领域高知名度求解器LUARA(NASA)、LeMANS(UMich)进行了结果的对比与分析。使用力学所JFX激波风洞进行了自由流均匀性以及进入舱模型试验，通过对自由流皮托压力、激波脱体距离进行试验与计算结果对比分析。通过试验验证了低焓(1.3 ~ 1.4 MJ/kg)情况下热非平衡计算的准确性，并分析了喷管出口的流动状态；进一步通过与文献数据对比验证了中高焓(5.6 ~ 12.3 MJ/kg)热化学非平衡计算的准确性，为后续章节发展流固耦合计算程序提供支撑。

2. 基于Euler-Lagrangian框架，建立了非平衡流场与颗粒的单向耦合计算方法，针对颗粒计算的阻力模型以及颗粒—壁面碰撞模型进行相关研究及讨论，选取Henderson阻力模型作为颗粒的阻力计算模型；此外，采用模态半径为0.35 μm的火星大气颗粒分布模型，研究了不同尺寸颗粒在流场中的运动轨迹，并探究了高温相变模型对颗粒运动的影响规律以及不同粒径颗粒的撞击能量分布。

3. 在单向耦合的基础上，建立了双向耦合计算模型，详细介绍了双向耦合假设下的控制方程、颗粒源项具体计算方法、MPI并行条件下颗粒信息储存及传递方式，通过数值模拟方法研究了来流含颗粒前后的激波脱体距离、壁面热流变化结果，针对不同质量浓度的颗粒流条件，对流场结构的影响结果进行讨论与分析。

综上所述，本文的主要意义在于建立了针对火星进入环境下含尘气体与外流场流动的流固耦合计算方法，发展了E-L框架下的单向、双向耦合模型，并完成了数值模拟对含颗粒高速气体与飞行器相互作用的初步分析，为后续深入研究奠定了基础。研究结果有助于理解颗粒—流场—飞行器的多物理场耦合，推动高超声速火星进入飞行器相关研究的发展。

Mars, as the closest planet to the Earth, has been included in the planning of the deep space exploration programmes of various countries, such as Mars entry and Mars sample return missions. The Mars entry probe is faced with severe aerodynamic thermal environments and must be designed with effective thermal protection systems. Different from the Earth's atmospheric reentry, the Martian atmosphere has a low density and high concentration of CO₂, which leads to the existence of a strong thermo-chemical non-equilibrium effect during the process. In addition, Mars will form different degrees of dust storms, lasting for a long time and covering the height of the rover's EDL process, causing additional erosion damage to the probe, and bringing great challenges to the design of the thermal protection system of the probe. In order to have a more accurate and in-depth understanding of the peripheral dusty flow field during the vehicle entry process, this paper adopts a numerical simulation method, which mainly focuses on the particle-containing high-flow gas incoming flow to carry out relevant research work on the gas-solid coupling problem. The main research contents of this paper are summarised as follows:

1. A two-dimensional axisymmetric five-component CO₂ thermochemical non-equilibrium calculation procedure is developed, and numerical simulations are carried out for the external flow field of the aircraft under different operating conditions, and the results are compared and analysed with high-profile solvers LUARA(NASA)、LeMANS(UMich) in this field. Using the JFX surge wind tunnel in the State Key Laboratory of High Temperature Gas Dynamics, the free-stream uniformity test as well as the model test of the entry chamber are carried out, and the comparative analyses of the test and calculation on the free-stream Pitot pressure and the distance of the surge disintegration are carried out. The accuracy of the thermal non-equilibrium calculations for the low enthalpy case (1.3 ~ 1.4 MJ/kg) was verified by the tests and the flow state at the nozzle outlet was analysed; the accuracy of the thermochemical non-equilibrium calculations for the medium and high enthalpy cases (5.6 ~ 12.3 MJ/kg) was further verified by comparing the data with the literature data; and the development of the flow-solid coupling calculation program in the subsequent chapters was supported.

2. Based on the Euler-Lagrangian framework, a unidirectional coupling calculation method between the non-equilibrium flow field and particles is established, and relevant studies and discussions are carried out on the drag model and particle-wall collision model for particle calculations, and the Henderson drag model is selected as the drag calculation model for particles; in addition, a particle distribution model of the Martian atmosphere with a modal radius of 0.35 μm is used. In addition, the particle distribution model of the Martian atmosphere with a modal radius of 0.35 μm is used to study the trajectories of particles of different sizes in the flow field, and the influence of the high-temperature phase transition model on the particle motion and the impact energy distribution of particles of different sizes are investigated.

3. On the basis of one-way coupling, a two-way coupling calculation model is established, and the control equations under the assumption of two-way coupling, the specific calculation method of particle source term, and the particle information storage and transmission mode under the parallel condition of mpi are introduced in detail, and the distance of the surge off-body before and after the incoming flow containing particles and the results of the change of the wall heat flow are investigated through numerical simulation, and the effect on the structure of the flow field under the condition of different particle mass concentration is discussed and analysed. The results are discussed and analysed.

In summary, the main significance of this paper lies in the establishment of a flow-solid coupling calculation method for the flow of dust-containing gas and external flow field in the Mars entry environment, the establishment of one-way and two-way coupling models under the E-L framework, respectively, and the preliminary analysis of the interaction between particle-containing high-flow gas and the vehicle through numerical simulation, which lays the foundation for the subsequent in-depth study. The results help to understand the multi-physics field coupling of particle-fluid field-vehicle and promote the development of hypersonic Mars entry vehicle related research.