The development and computer simulation is presented for a bending flexible missile with a rigid-body controller system moving in a 2-D coordinate frame. In this thesis, the dynamic model was developed through the Equivalent Rigid Link System (ERLS) using Lagrangian dynamics to obtain a type of system equations of motion suited for the sequential integration method that integrates large motion explicitly and small motion implicitly. The spatial finite element discretization of missile structure and the application of truncated natural modal responses provide an approximate solution. The analysis and simulation were performed to understand the dynamic behavior of a flexible missile using a rigid-body controller. The payload will affect the natural frequency of the missile structure i.e, when the payload is increased, the system fundamental frequency will be decreased. The payload must then be limited to achieve high- speed response. In order to increase the payload and maintain high-speed control response, a flexible-body controller is needed. Keywords: Pitch angle control; Attitude control systems; Two dimensional control systems; Theses.
Naval Postgraduate School
M.S. in Engineering Science
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