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The pitch rate control of a missile is analyzed by an H ∞ controller. The system dynamics governing the aerodynamic stability derivatives and airframe structure vibration is formulated in a generalized state space realization form. This formulation facilitates the γ-iteration method in solving the associated Ricatti equation of the 4-block H ∞ control problem. It is shown that the H ∞ controller, because of its loop shaping capabilities, can provide improved tracking performance and stability robustness compared with H 2 (linear-quadratic-Gaussian (LQG)) and classical proportional-integral-derivative (PID) controller in the rigid airframe model. When airframe flexibility effect is considered, the H ∞ controller is also shown to be robust under structure natural frequency variations.