The Low Density Supersonic Decelerator (LDSD) project utilizes a 4.4 m maximum diameter ballute as part of a unique parachute deployment architecture to test a new supersonic parachute for Mars entry. This mortar deployed ballute was designed to inflate and operate at the Mach numbers up to 3 and the dynamic pressures between 240 and 1000 Pa. In this paper, the finite element code LS-DYNA was used to obtain the predictions of inflated ballute shape, along with the stresses in the ballute fabric and meridional reinforcements. Specifically, the ballute fabric was loaded with a pressure differential resulting from prescribed internal and external pressure distributions. Both analytical and finite element models showed large structural margins in the ballute fabric and reinforcements. These findings are consistent with the post-test examination of the ballute which revealed no structural damage resulting from the flight test conducted in June of 2014.
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