This thesis examines the control deficiencies in a Bank-to-Turne (BTT) cruise missile due to specific impairments at its control surfaces, during the intermediate phase of its mission. For the study of flight control configuration, a linearized mathematical model is developed which simulates the dynamic response of the missile circular airframe. In the development, a classical design and analysis is performed using both longitudinal and lateral channels for the circular airframe. For each channel the control surfaces are split into independence components and the corresponding continuous open loop uncoupled autopilots are analyzed in terms of their transient response. Specific kinds of impairments are then examined and analyzed and,investigated and the robustness of the complete system is analyzed. Keywords: Autopilot; Yaw; Pitch(Motion), Coupled; Split up; Reconfiguration.


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