A fluid dynamics technique for modelling inflatable shield for re-entry or aerocapture missions

This study presents a novel numerical technique, derived by shock-fitting methods, for computing fluid-structure interactions occurring in hypersonic aerocapture maneuvers. Uncertainties in atmospheric density, due to errors related to atmospheric models or natural events, are a serious challenge when planning aerocapture manouvers. This work proposes a Drag Modulation strategy involving an inflatable shield, the inflation pressure of which is continuously adjusted in order to compensate the density uncertainties and to preserve the nominal deceleration of the capsule in the atmospheric passage. In particular, the proposed technique was applied to design an aerocapture mission on Mars, using an inflatable shield able to achieve a density compensation range from -4.5% to +43%. Alternative solutions to further extend the compensation range are also discussed.