Aerodynamic Performance of Flap-Based Deployable Heat Shield for Satellite Reentry and Recovery

The space environment is undergoing rapid changes with the emergence of new commercial capabilities, and the development of new technologies to improve space sustainability is imperative. In this context, a comprehensive numerical analysis has been performed to investigate the aerodynamic behavior of a deployable reentry system. In the present investigation, computational fluid dynamics (CFD) and direct simulation Monte Carlo (DSMC) methods are employed to compute the flowfield structure and forces for altitudes ranging from 200 to 95 km. The results indicate that a diffuse high-temperature shock wave is generated upstream of the shield, exhibiting a significant decrease in thickness between 100 and 95 km altitude. At 100 km altitude, good agreement was found between the CFD and DSMC methods, with a difference of 11% in the drag coefficient. This highlights the reliability of CFD within limited altitude ranges and emphasizes the need for DSMC in the upper atmosphere for more realistic results.