New Structure for an Aerodynamic Fin Control System for Tail Fin-Controlled STT Missiles

摘要: This paper presents a new design method for an aerodynamic fin-control system tail-fin controlled skid to turn (STT) missiles. The performance of the actuation plays decisive role in determining flight control highly maneuverable missile. To missiles by aerodynamics, surfaces, sometimes called fins, are used. Deflection angles these fins variables but aerodynamicists prefer use analytic aileron, elevator, and rudder instead physical because three dominantly influence roll, pitch, yaw motion missile, respectively; each can be considered linear combination four fin deflection angles. On that basis, autopilots controlling attitudes or lateral acceleration missile designed, commands, respectively, generated as consequence outputs autopilot. In existing fin-actuation scheme typical cruciform missiles, distributed defection commands. After that, actuated controllers so their deflections follow shows such schemes cause significant deterioration when fin-actuators have certain constraints slew rate, voltage, current limit, uncertainty actuator dynamics, proposes alleviates problems. widely applied various systems. But this paper, convenience, is used example, proposed shown give better than one.