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Trajectory Optimization of a Deflectable Nose Missile

ZHIYONG ZHANG, XIAOHUI SUN, ZHIHUA CHEN, QIZHONG TANG

Abstract


The deflectable nose missile has a longer range and higher maneuverability 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° to 8°, and mach numbers, 2 to 5. Coupling these aerodynamic coefficients with the 6 degree of freedom (DOF) 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.

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