Aerodynamic Shape Optimization System of a Canard-Controlled Missile Using Trajectory-Dependent Aerodynamic Coefficients

Abstract

This paper describes a shape optimization study to maximize the range of a guided missile. To design a guided: missile having maximum range, a shape optimization system is incorporated with a trajectory analysis program and an optimization technique. In particular, trajectory-dependent aerodynamic coefficients are fully considered. In the trajectory analysis step, a component buildup method is directly connected to the equation of motion to calculate aerodynamic coefficients at every time step. In the optimization step, a real-coded adaptive range genetic algorithm is adopted to determine the optimal shape of the global maximum range. The shape optimization system of a guided missile can maximize the range of the missile and yield the optimal shapes of canards and tailfins. Finally, the effects of trajectory-dependent aerodynamic coefficients, guidance, and control on the range of a missile are illustrated.