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A robust, flight control law is investigated to provide fault tolerance for air vehicles experiencing inertial state measurement sensor degredation. The method is particularly useful on low cost, precision weapons pursuing dynamic targets. Observation techniques are facilitated by representing the surface actuator aerodynamic induced hinge moment by a function that is Lipschitz within the actuator sweep angle. A stable output feedback flight control law, requiring only acutator angular positiondoi:10.1109/acc.2008.4586722 dblp:conf/amcc/RatliffP08 fatcat:wrg63oq3brcipkjfmzrpf6fs5m