Influence Of Rarefied Gas Effect On Aerodynamic Characteristics Of Hypersonic Decelerator

As a type of aircraft model with important application value,the near space decelerator has important strategic significance and practical value in the research of space program and the promotion of near-space high dynamic vehicle.However,due to the complexity of the near space,the flow field parameters in large-scale and inter-basin regions lead to the lack of research on the aerodynamic characteristics of the flow field in this area.The existing researches are mainly based on the traditional N-S method,and the continuous hypotheses failure of the N-S method occurs in this environment,which directly leads to the unreliability of the numerical simulation results.At the same time,we find it difficult to simulate the high-speed flow field structure up to tens of Mach in the real reentry process for reentry decelerator in experimental simulation.Therefore,in this paper,we focus on the aerodynamic characteristics analysis of reentrant decelerator based on DSMC.First of all,in order to verify the reliability of the research method we used,in the second chapter of this paper,we operate four representative examples with experimental results,numerical results and theoretical values,to verify the reliability of the code.Then,in order to have a thorough understanding of reentry decelerator,we use a step by step,from simple to complex ways in the third chapter,the two-dimensional model of the impact of the thin effect of inquiry,obtained a quantitative conclusion,To fill the gaps in the field.Finally,through the analysis of the reentry model,we choose a widely used experimental model to simulate and obtain a series of variation rules of flow field parameters for the reentry decelerator near space.