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Completed TRL 5 (started at 3, targeting 5)
Existing test methods for characterizing entry vehicle dynamic stability are limited in number, cannot cover the entire flight regime of interest, and have inherent uncertainties which drive mission risk. A new test platform provides holistic and rich data to reduce uncertainties and mission risk. This project will design, build, and test a flight system prototype to validate an architecture for acquiring supersonic free-flight dynamic stability data.
Free or forced oscillation wind tunnels, ballistic ranges, and vertical spin tunnels are methodologies for characterizing dynamic stability. Each method introduces significant compromises to fully reproducing and understanding the phenomenon of interest. None of these methods can cover the entire transonic range. This work will finalize a preliminary system design, verify and validate the design by performing component level ground testing, and manufacture and assemble an integrated flight system for a system level drop test.
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