AERODYNAMIC ANALYSIS OF A FLAP-BASED DEPLOYABLE RE-ENTRY SYSTEM UNDER RAREFIED CONDITIONS

In the present work, an aerodynamic analysis of an umbrella-like deployable heat shield is investigated for satellite reentry and recovery applications. The influence of altitude in the flowfield structure over the satellite coupled with the deployable heat shield is discussed in detail. Due to the gas rarefaction found at 200, 150, and 100 km altitudes, the Direct Simulation Monte Carlo (DSMC) method is employed in all computations. The study covers macroscopic properties such as flow velocity, temperature, mass density, and pressure, with a detailed analysis of the shock wave structure and thermal gradients around the capsule. Results indicate significant differences in flow behavior and thermal effects, comparing the results obtained at different altitudes. A high diffuse shock is formed upstream of the heat shield at high altitudes with significant thermal gradients due to increased rarefaction. These findings provide insights into the design and analysis of reentry vehicles under rarefied conditions.