Inflatable aerodynamic decelerator for CubeSat reentry and recovery: IAD geometrical effects on the flowfield structure

In this investigation, Direct Simulation Monte Carlo computations were carried out to assess the influence of Inflatable Aerodynamic Decelerator (IAD) geometrical configurations on the flowfield during the atmospheric reentry. The non-reacting hypersonic rarefied flow over three IAD configurations coupled to a CubeSat was simulated considering a 0^∘ angle of attack at an altitude of 105 km. According to the results, it was observed the formation of a strong and diffuse shock wave for all geometries considered in this investigation. However, a lower inflatable aeroshell angle is associated with a thinner shock wave and a maximum shock wave temperature closer to the shield's surface. These differences decrease in the flow expansion over the IAD shoulder. In the rear of the inflatable shields, a low-temperature and low-velocity region is observed, indicating that the IADs geometries successfully mitigate the harsh reentry conditions experienced by the payload. Finally, it was noticed that the wake region is larger for aerodynamic elongated shapes, in contrast to blunt geometries with the expense of slightly higher gas temperature closer to the front surface of the shield. No recirculation zone was observed in any of the simulated IAD configurations considered in this investigation.