Abstract
In this paper an NDI control design for the automated atmospheric re-entry of the Hopper reusable-launch vehicle (RLV) concept is presented. The NDI design is characterized by i) an inversion step where the trim and flight surfaces deflections are independently calculated and ii) by avoiding the standard linearization of the known aerodynamic database. The resulting control design is validated through time simulations using a high-fidelity model of the Hopper RLV in the face of parametric and aerodynamic database uncertainties, sensor noise and realistic atmospheric environment.
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