Abstract
A Bank-To-Turn (BTT) missile has significant aerodynamic and inertial cross-coupling between the pitch, yaw and roll axes. An effective BTT missile control system must be able to reduce the dynamic interactions, and must also be capable of command tracking, disturbance rejection, and maintaining system stability for all flight conditions. A BTT control system is developed based on concepts of the closed-loop eigenvalue/ eigenvector assignment and the command generator tracking. The eigenvalue assignment results in the required closed-loop damping and frequencies whereas the eigenvector assignment provides the necessary dynamic decoupling. Guidance command is tracked by the BTT missile owing to a feedforward controller which is designed via the command generator tracking concept. Disturbance rejection capability and system's stability for six typical flight conditions for such a BTT missile control system are demonstrated by simulations.
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