This paper presents the design of a robust attitude control system for the autonomous recovery of a
flexible launch vehicle fairing, a topic currently absent from the literature. The fairing's aeroelastic
properties introduce significant control challenges, particularly during atmospheric re-entry. To
address these, the study goes beyond controller gain optimization to consider subsystem architecture
selection and integration with real actuators, essential for realistic implementation. A linear
time-invariant (LTI) model is developed to capture the key dynamics, incorporating parametric
uncertainties that reflect aerodynamic variability and structural flexibility. The control architecture
is based on H∞ synthesis, chosen for its robustness and compatibility with gain-scheduling
strategies. A detailed tuning methodology is presented, and the controller is evaluated for both
performance and robustness. Validation is performed in a high-fidelity, nonlinear six-degrees-of-freedom
simulation environment that includes aeroelastic effects, demonstrating reliable behavior
across diverse flight conditions. The resulting controller, combined with simplified navigation
and guidance functions, improves recovery success from nearly 0% to 75% under current mission
requirements. This approach supports reliable, reusable fairing recovery through advanced
guidance, navigation, and control techniques.