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An electric nose wheel steering system for aircrafts was introduced. For high reliability, dual identical RS422 buses are used as well as a dissimilar redundancy feedback strategy incorporating both the screw's linear displacement and the nose wheel output angular displacement. A fork-link mechanism structure is connected with the ball-screw to drive the nose wheel for both a high reduction ratio and a large torque output. A hydraulic damper is embedded in the mechanism to buffer the impact loads. Simulations and tests were finished, showing a good conformity.