Aeroelastic Simulation Tool for Inflatable Ballute Aerocapture, Phase I

This project will develop a much-needed multidisciplinary analysis tool for predicting the impact of aeroelastic effects on the functionality of inflatable aeroassist vehicles. High-fidelity computational modules for fluid dynamics, heat transfer, structural dynamics, and dynamic motion will be coupled into a multidisciplinary computing environment. The multi-disciplinary system has been successfully applied for aeroelastic and dynamic simulations of fighter aircraft, hypersonic vehicles and planetary probes. The application range will be extended to the rarefied regime through integration of an existing NASA DSMC flow solver. In Phase I, continuum flow regime sample analyses will be performed for a trailing ballute configuration to demonstrate the capabilities of the software environment. Simulations will demonstrate the insight gained into the aerodynamic, material stress and localized heating effects from various levels of simulation fidelity: steady and unsteady flow, rigid or flexible structure, and static or dynamically moving vehicles. The feasibility of implementing the DSMC flow solver in the multidisciplinary simulation framework will be demonstrated for the case of a steady-state shape deformation prediction. Phase II efforts will focus on fully implementing the DSMC code and other NASA codes in the multidisciplinary environment. Extensive verification and validation studies will be performed, leveraging planned aeroelastic ballute windtunnel tests.

This is a mature technology (TRL 7+) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.

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