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Completed TRL 4 (started at 2, targeting 4)
Supersonic retropropulsion (SRP) has been identified as a potentially enabling technology for human-scale Mars landing systems. However, the accurate description of the complex physical processes and uncertainties associated with the coupling of the bow shock with the plume exhaust, multi-nozzle plume interactions, unsteady flow dynamics, and other aerodynamic interferences pose significant challenges for informing the design of future entry, descent, and landing systems that utilize retropropulsion. This research seeks to develop and apply advanced data-analysis methods to extract fundamental plume physics and sensitivities of multi-nozzle SRP. Knowledge extracted from this analysis will be used to develop a hierarchical modeling framework for predicting quantities of interest with quantifiable uncertainties to support Mars lander powered descent aerodynamics databases and to evaluate SRP wind-tunnel test data. The outcome of this research is expected to achieve significant gains in advancing fundamental understanding of plume physics and establishing improved engineering models to inform the design of multi-nozzle SRP systems, to support the analysis of experimental data, and to facilitate the infusion into related product developments.
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