The Impact of Particle-Laden Flows on Planetary Entry Aerothermodynamics

High velocity flows experienced during planetary reentry pose difficult challenges to both human and robotic spaceflight. The thermal environment experienced in reentry is as dangerous as it is difficult to predict and analyze. Furthermore, analysis challenges such as flows involving particles like dust and spalled thermal protection system (TPS) material lead to further uncertainties in vehicle performance during the entry, descent, and landing (EDL) phase of missions, requiring the use of generous design margins in TPS thicknesses. These particulate-laden flows can be experienced in a number of mission scenarios, such as entry into Mars during or shortly after a global dust storm, or entry into Earth at high velocities experienced in Lunar or Mars return trajectories, where spallation of the TPS material can occur. Existence of dust or spalled particles can significantly alter the shock layer characteristics, through augmentation of the convective and radiative heating in both the fore and afterbody regions of the flowfield, as well as mechanical erosion of the TPS, and increased roughness and turbulent kinetic energy production. These effects may be significant challenges for deployable entry technologies like the Hypersonic Inflatable Aerodynamic Decelerator (HIAD) and Adaptable Deployable Entry and Placement Technology (ADEPT). The interplay of these phenomena is an extremely complex analysis problem, and accurate characterization and uncertainty quantification of these flows will be a crucial step in the journey to human-crewed missions to the Martian surface. The objective of the proposed research is to develop and validate a particle flow simulation tool, with two-way coupling with CFD and Radiation codes of NASA, and perform uncertainty quantification of the effects of particle-laden flows on deployable hypersonic decelerators like HIAD and ADEPT. The methodology of the proposed research include: (1) evaluation and validation of models for particulate dynamics, (2) development, verification, and validation of a particle dynamics simulation tool, (3) coupling of the tool with state-of-the-art CFD and radiation tools, and integration to an existing uncertainty quantification framework, and (4) uncertainty analysis of planetary entry technologies in particulate environments. The proposed research will contribute to the goals specified in several NASA Technology roadmaps as specified in the Technology Area Breakdown Structure (TABS). The improved modeling capabilities will contribute to TABS 9.4.5: Entry, descent and landing (EDL) modeling and simulation, as well as TABS 14.3.2: Thermal Protection Systems modeling and simulation. The proposed research will also seek to improve analysis of both rigid and deployable hypersonic decelerators, contributing to TABS 9.1.3 and 9.1.4: Rigid Hypersonic Decelerators, and Hypersonic Deployable Decelerators, respectively. Furthermore, the particle simulation tool will help quantify uncertainty in particulate ejection due to propulsive landing systems, contributing to TABS 7.6.1: Particulate contamination prevention and mitigation.

The proposed research will contribute to the goals specified in several NASA Technology roadmaps as specified in the Technology Area Breakdown Structure (TABS). The improved modeling capabilities will contribute to TABS 9.4.5: Entry, descent and landing (EDL) modeling and simulation, as well as TABS 14.3.2: Thermal Protection Systems modeling and simulation. The proposed research will also seek to improve analysis of both rigid and deployable hypersonic decelerators, contributing to TABS 9.1.3 and 9.1.4: Rigid Hypersonic Decelerators, and Hypersonic Deployable Decelerators, respectively. Furthermore, the particle simulation tool will help quantify uncertainty in particulate ejection due to propulsive landing systems, contributing to TABS 7.6.1: Particulate contamination prevention and mitigation.

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