In this thesis, we present a control algorithm for a hypersonic re-entry vehicle during a Martian aerocapture maneuver. The proposed algorithm utilizes a discrete-time model predictive control technique with a Takagi-Sugeno fuzzy model of the vehicle to control the re-entry vehicle along an arbitrary trajectory using bank angle modulation. Simulations using model parameters and initial conditions from a Martian aerocapture mission demonstrate the stability, performance, and robustness of the proposed controller
