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The deflectable nose missile has a longer range by deflecting its nose to improve its aerodynamic feature. Based on detached eddy simulation (DES), the supersonic flow fields of a missile with deflectable nose are simulated numerically and its aerodynamic force coefficients are calculated under the condition of the deflection angles vary from 0° to 8°, angles of attack, 0°–8°, and mach numbers, 2 to 5. Coupling these aerodynamic coefficients with the plumb plane ballistic equations, the extended flight range has been calculated. Furthermore, the genetic algorithm (GA) is employed for the solution of maximum range of the deflected missile.

Deflectable nose missile is a novel supersonic morphing missile with different characteristics from the ordinary tactical missiles. In this paper, the dynamic model is divided into the equivalent pitching equations and the equivalent yawing equations as the roll-channel control system of missile works ideally. Then open-loop stability of both the equivalent pitching equations and the equivalent yawing equations are analyzed respectively. After that, the variable structure control theory is employed to design both the overload direction control loop and overload magnitude control loop for a deflectable nose missile. Simulation result shows that closed-loop overload control system can track both the direction and magnitude of overload signal quickly and accurately.