返回舱再入跨流域气动及配平特性数值研究.

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 helow altitude of 90 km. The lateral offset of centroid has a larger impact on the trim angle of attack. [ABSTRACT FROM AUTHOR]