To improve the aerodynamic ballistic performance of the gliding guided projectiles in the climbing phase and gliding phase and achieve significant range increasement,the gliding guided projectile with conventional fixed shape was designed with variable shape by combining the variable sweep and variable span of tail fins.Missile Datcom was used to calculate the aerodynamic parameters.The shape parameters of canards were adjusted with the span and sweep angle of tail fins deformation.Based on the NSGA-Ⅱ multi-objective optimization algorithm,the multi-objective optimization design of variable shape for the climbing phase and the gliding phase of the gliding guided shell was carried out.Then,the optimal shape schemes for each flight phase were finally obtained.In the climbing phase,the optimization objectives are the zero-lift drag coefficient and static stability margin of the projectile.While in the gliding phase,the optimization objectives are the lift-to-drag ratio and the maneuvering ratio of the projectile.The numerical simulation results show that the optimized variable shape scheme can significantly improve the aerodynamic and ballistic performances of the gliding guided projectile in each flight phase.The drag coefficient in the climbing phase is reduced by 13.3%,the lift-to-drag ratio in the gliding phase is increased by 36.1%.The optimized gliding guided projectile is table during the entire flight process,with good matching of stability,maneuverability,rudder deflection angle,and equilibrium angle of attack.Compared with the baseline fixed shape scheme,the range of the gliding guided shell with variable shape scheme under gliding control conditions is increased by 8.4%.The research provides a reference for the design of variable shape scheme of gliding guided projectile.
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