Implementation and validation of autopilot design for vertical missile systems

high nonlinearity and deficiency in control at boost-phase due to high angle of attack during maneuver and low velocity in the vertical launched missile. The necessity of high maneuverability and vertical launching require thrust vector control additional to aerodynamic control. effectively increasing the alertness of the missile against air defense threats by using That mixture usage of aerodynamic and thrust vector controls. Critical design of guidance and control is difficult and critical due to requirement and the rapidly changing dynamics of this type of missiles. The aim of this paper is to design autopilot with aerodynamics surfaces(fin)and thrust vector control by system characteristics reflection. by using Missile Lebadev Program (MLP) the model is developed based on the configuration of operating missile. Two control systems are aimed, which usages the command trajectory result optimization and the pitch rate controller which tracks real-time guidance command. The guidance and control strategy are developed through an actuation systems and autopilot design in the two channels pitch and roll based on the poles assignment technique. The investigation of the performance of pitch autopilot and its ability to reject disturbances due to cross-coupling between pitch and roll channels showed that, the pitch channel can reject disturbances within average time 3.5 sec.