The Aerodynamic Configuration Analysis Of Two-dimension Trajectory Correction Projectile

The use of precision strike munitions occupies more and more proportion in modern warfare, for guided missiles are too expensive to equip the army in large-scale, and inventories of uncontrolled rockets could not achieve the required accuracy, the Trajectory correction projectile with its high benefit-cost ratio has obtained the favor of many countries. Trajectory correction projectile is an intelligent missile, it modify impact coordinate and improve fire intensity targets by changing aerodynamic shape with correcting mechanism in proper position of flight. This article describes the process of canard controlled two-dimension trajectory correction projectile’s aerodynamic research, the results of wind tunnel experiments and numerical simulations were given, aerodynamic characteristics were analyzed.First, a pair of canard controlled two-dimension models of trajectory correction projectiles with different rudder angles were designed, the aerodynamic characteristics of models were studied by wind tunnel test in subsonic, transonic and supersonic. The variation of Models’aerodynamic force and moment coefficients with Mach number, angle of attack and rudder angle were gotten, schlieren photographs were taken in supersonic. Model non-rotating in the experiment mach number and rotating speed10000r/min and15000r/min in supersonic were investigated by the method of numerical simulation, models’flow field distribution in rotating and non-rotating conditions were used to analysis variation of the aerodynamic characteristics.By observing the Schlieren photograph and flow field numerical simulation, original model appeared a shock wave at the head with the circular contact area, which will adversely affect the aerodynamic characteristics of models. To improve the original models, a new pair of canard controlled models were designed. Under the condition of supersonic, the new models non-rotating and rotating speed10000r/min and15000r/min were investigated by the method of numerical simulation, aerodynamic characteristics in non-rotating and rotating were gotten. Comparing aerodynamic characteristics of the two aerodynamic configuration models, the drag coefficient of optimized model reduced, but the reduction of drag effect was not obvious, under rotating conditions the drag coefficient of models all reduced. The lift coefficient of optimized models increased, it illustrated that models’ correction ability increased, under rotating conditions the lift coefficient of models all showed little change. The pitching moment coefficient of optimized models increased and had little change after rotating. The rolling moment coefficient of optimized models also increased, illustrated that models’ change attitude ability increased, under rotating conditions the rolling moment coefficient of models all decreased, decreased with the increased of rotational speed. The pressure center coefficient of optimized models was less than the origin models’.The results of this study on the two kinds of canard controlled two-dimensional trajectory correction projectiles aerodynamic configuration provided basis for the two-dimensional trajectory correction ballistic design and research.