大型航天器再入陨落时太阳翼气动力/热模拟分析

采用直接模拟蒙特卡洛（DSMC）方法对大型航天器离轨再入陨落过程中，其太阳翼帆板在稀薄过渡流域的气动力、气动热特性进行数值模拟，计算中采用流场直角与表面三角形非结构混合网格以及网格自适应技术处理这类复杂外形的流动模拟，考虑内能激发和化学反应来准确模拟气动加热，并基于MPI环境的并行算法解决计算量庞大的难题。通过计算分析太阳翼水平和垂直放置时在不同高度、不同攻角下的复杂流动特征，表明在90km以上高空，太阳翼垂直放置时，飞行器头部脱体激波与帆板脱体激波会产生更强烈、更复杂的激波/激波和激波/边界层的干扰，在气动力和气动热的双重作用下要比水平放置时的太阳翼更快地被撕裂并脱离目标航天器。

Modeling and Analysis of Solar Array Aerothermodynamics During Large Scale Spacecraft Reentry

The direct simulation Monte Carlo (DSMC) method is used to simulate aerodynamic force and aero-heating applied on solar array panels in rarefied transitional regime during large-scale spacecraft deorbit and atmospheric reentry. The hybrid Cartesian grids and surface unstructured triangular cells are employed with the self-adaptive technique to deal with the complex configuration flows. Internal energy excitations and chemical reactions are considered to simulate aero-heating precisely. The huge amount of computing memory is resolved by the DSMC parallel algorithm based on MPI environment. The computational analysis of complicated flow properties are performed in different altitudes and angles of attack for solar array horizontally and perpendicularly mounted respectively. Results show that more stronger and complex interactions of shock/shock and shock/boundary layer above 90 km altitude are happened between top bow detached shock wave and solar array detached shock wave when the solar array is perpendicularly mounted. Perpendicularly mounted solar array is more easily torn and separated from the spacecraft than horizontally mounted solar array under the dual aerodynamic force and heating interactions.