Abstract
This paper examines the dynamic stability of a notional Mars entry vehicle augmented with an attached supersonic inflatable aerodynamic decelerator (SIAD) deployed at Mach 5. Dynamics of the attached isotensoid and tension cone SIAD configurations are compared using an explicit solution to the planar equations of motion. A current experimental database of flexible isotensoid and tension cone static aerodynamics is employed in the simulation. Pitch-damping data from the Mars Science Laboratory (MSL) ballistic range tests is parameterized and applied to the SIAD-augmented portion of flight. The Mach number at which safe parachute deployment can occur depends on the amplitude of pitch oscillation, so the sensitivity of this metric to the parameterized pitch-damping behavior is determined. Pitch dynamics yielding unacceptable parachute staging conditions are quantified to inform SIAD configuration selection and design. These exploratory results are used to recommend a general strategy for measuring the pitch dynamics of SIAD-augmented blunt vehicles in ground testing facilities.
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